WO2025102000A1 - Systèmes et procédés pour dispositifs de combustion évolutive - Google Patents

Systèmes et procédés pour dispositifs de combustion évolutive Download PDF

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WO2025102000A1
WO2025102000A1 PCT/US2024/055262 US2024055262W WO2025102000A1 WO 2025102000 A1 WO2025102000 A1 WO 2025102000A1 US 2024055262 W US2024055262 W US 2024055262W WO 2025102000 A1 WO2025102000 A1 WO 2025102000A1
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Prior art keywords
fluid
oxidant
fuel
combustor
combusting
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David Leroy Hagen
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Vast Energy Solutions LLC
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Vast Energy Solutions LLC
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/14—Details thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N1/00—Regulating fuel supply
    • F23N1/002—Regulating fuel supply using electronic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/60—Application making use of surplus or waste energy
    • F05D2220/62—Application making use of surplus or waste energy with energy recovery turbines

Definitions

  • JOINT RESEARCH AGREEMENT [0002] This invention was made with government support under a Cooperative Research and Development Agreement (CRADA) No. TC02380 between the Department of Energy (DOE), Lawrence Livermore National Security LLC, University of Chicago Argonne LLC, and VAST Power Systems, LLC. The government has rights in the invention.
  • TECHNICAL FIELD [0003] The present disclosure relates to combustor or reactor systems, and more specifically, to scalable combustor systems. BACKGROUND OF THE INVENTION [0004] In certain combustion and power generation systems, such as conventional, green, renewable, and/or sustainable energy systems, combustors are used to combust or otherwise react fuels useful in generating thermal energy.
  • a combustor can deliver and mix a fuel fluid comprising a fuel, an oxidizer fluid comprising an oxidizer, and a diluent fluid comprising a diluent, to combust a fluid mixture comprising fuel, oxidant, and a diluent, resulting in a working fluid having useful thermal energy.
  • the working fluid can then be used, for example, to produce heat and/or power via direct and/or indirect energy transfers, such as rotating a gas turbine system, heating, or cooling. It would be beneficial to improve on such combustor systems, processes, and controls.
  • Fig.1A is an elevation view of a transversely elongated vertical Cuboidal “Scalable Combustor” with fluid manifolds feeding opposed combustor walls, according to some examples.
  • Fig. 1B is a schematic detail of an upstream flame authority in the Cuboidal Scalable Combustor, according to some examples.
  • Fig.1C is an elevation view of a combusting chamber and Blend-Trim region in the Cuboidal Scalable Combustor, according to some examples.
  • Fig.1D is an elevation view of upstream diluted oxidant, and downstream diluted oxidant fluid manifolds feeding a first side of an adjacent combusting chamber and Blend-Trim region of the Cuboidal Scalable Combustor, according to some examples.
  • Fig.1E is a detail section of an insulated combusting chamber wall with diluted fuel delivery orifices in the Cuboidal Scalable Combustor, according to some examples.
  • Fig.1F is a detail section of an insulated combusting chamber wall with diluted oxidant delivery orifices in the Cuboidal Scalable Combustor, according to some examples.
  • Fig.1G is a detail section of an insulated wall in a downstream Blend-Trim region with diluted oxidant and diluent delivery orifices in the Cuboidal Scalable Combustor, according to some examples.
  • Fig.1H is an elevation view of upstream diluted fuel and downstream diluted oxidant fluid manifolds in the vertical Cuboidal Scalable Combustor feeding a second side of the adjacent combusting chamber and Blend-Trim region, according to some examples.
  • Fig.1I is a plan view of the vertical Cuboidal Scalable Combustor through plane A-A’, according to some examples.
  • Fig.2A is a schematic of a scalable combustor with a blower and diluent delivery, according to some examples.
  • Fig.2B is a perspective view of a horizontal Cuboidal Scalable Combustor with diluent spray and common ignition authority, according to some examples.
  • Fig.2C is a detailed section view of an insulated combusting chamber wall with fluid delivery orifices, according to some examples.
  • Fig. 2D is a perspective view of a vertically oriented Cuboidal Scalable Combustor section with downstream diluent delivery, according to some examples.
  • Fig.2E is a perspective view of a vertically oriented Cuboidal Scalable Segmented Combustor section with multiple rich combusting delivery, and intermediate diluent delivery, according to some examples.
  • Fig.3A An axial transverse schematic view of a Scalable Gas Turbine Combustor, according to some examples.
  • Fig.3B A perspective upstream view of a cylindrical Scalable Gas Turbine Combustor with a common pilot, according to some examples.
  • Fig.3C Detail of an insulated wall with fluid delivery orifices in a Scalable Gas Turbine Combustor, according to some examples.
  • Fig.3D A Radial Circumferential Outer Cross Section of the Scalable Gas Turbine Combustor, according to some examples.
  • Fig.3E A Circumferential Axial Unrolled Perspective of Symmetric Adjacent Gas Turbine Combusting Shell Sections, according to some examples.
  • Fig.3F Graph of Axial Combustor Temperature, Ammonia Fuel, and NOx, according to some examples.
  • Fig 3G A Circumferential Axial Unrolled Perspective of a Symmetric Gas Turbine Feeder Manifold Section, according to some examples.
  • Fig.3H A Circumferential Axial Unrolled Perspective of Adjacent Asymmetric Gas Turbine Combusting Shell Sections with common adjacent oxidant and Fuel Manifolds, according to some examples.
  • Fig.3I A Circumferential Axial Unrolled Perspective of an Outer Asymmetric Combusting Blend-Trim Feeder, according to some examples.
  • Fig.3J An axial-circumferential detail view of axially and circumferentially offset fuel and oxidant orifices from outer feeders into a combusting chamber, according to some examples.
  • Fig.3K An axial-circumferential detail view of axially and circumferentially offset fuel and oxidant orifices from inner feeders into a combusting chamber axially and/or radially offset from opposed feeder orifices, according to some examples.
  • Fig.3L An axial-circumferential detail view of axially and circumferentially offset diluent and/or oxidant orifices from outer feeder(s) into a downstream combustor Blend-Trim region, according to some examples.
  • Fig.3M An axial-circumferential detail view of axially and circumferentially offset diluent and/or oxidant orifices from inner feeder(s) into a combustor Blend-Trim region axially and/or radially offset from radially opposed feeder orifices, according to some examples.
  • Fig.3N A radial-axial elevation view of a CounterClockWise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig.3O A radial-axial elevation view inwardly adjacent to a CounterClockWise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig.3P A radial-axial elevation view inwardly adjacent to a clockwise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig.3Q A radial-axial elevation view of a clockwise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig.3R An axial-circumferential detail view of Fuel and offset oxidant delivery orifice spacing in fuel and oxidant feeders radially adjacent to a Scalable Combusting Region, according to some examples.
  • Fig.3S An axial-circumferential detail view of fuel and aligned oxidant orifices in feeders adjacent a combusting region, according to some examples.
  • Fig.3T A radial-circumferential detail view of fuel and oxidant orifice orientations into a combusting chamber from adjacent feeders, according to some examples.
  • Fig.3U A radial-axial elevation detail view of fuel and oxidant channels and orifices in outer and inner feeders adjacent a radially outward combusting region, according to some examples.
  • Fig.3V A radial-circumferential detail view of an oxidant orifice in a combusting chamber wall, according to some examples.
  • Fig.3W A radial-circumferential detail view of an angled oxidant orifice in a combusting chamber wall, according to some examples.
  • Fig.3X A radial-circumferential detail view of an oxidant feeder closed end, according to some examples.
  • FIG.3Y A radial-circumferential detail view of a fuel feeder closed end, according to some examples.
  • Fig.4A is an axial radial schematic view of a Gas Turbine System with a Scalable Combustor, according to some examples, according to some examples.
  • Fig.4B is a perspective view of the upstream section of an Annular Scalable Gas Turbine Combustor with a feeder comprising multiple ignition authorities, according to some examples, according to some examples.
  • Fig.4C is a detailed perspective view of an insulated wall with fluid delivery orifices in a Scalable Gas Turbine Combustor, according to some examples, according to some examples. [0047] Fig.
  • Fig. 4D is a Radial Circumferential Outer Cross Section of the Scalable Gas Turbine Combustor, according to some examples, according to some examples.
  • Fig. 4E is a Radial Axial Unrolled Perspective of Symmetric Adjacent Gas Turbine Combusting Shell Sections, according to some examples.
  • Fig.4F is a Graph of Axial Combustor Temperature, Ammonia Fuel, and NOx, according to some examples.
  • Fig. 4G is a Radial Axial view of a Symmetric Gas Turbine Feeder Manifold Section, according to some examples.
  • Fig.4H is a Radial Axial view of Adjacent Asymmetric Gas Turbine Combusting Shell Sections with common adjacent oxidant and Fuel Manifolds, according to some examples.
  • Fig.4I is a Radial Axial view of an Outer Asymmetric Combusting Blend-Trim Feeder, according to some examples.
  • Fig. 4J is a Radial Axial detail view of axially and circumferentially offset fuel and oxidant orifices from outer feeders into a combusting chamber, according to some examples.
  • Fig.4K is a Radial Axial detail view of axially and circumferentially offset fuel and oxidant orifices from inner feeders into a combusting chamber axially and/or radially offset from opposed feeder orifices, according to some examples.
  • Fig.4L is a Radial Axial detail view of axially and circumferentially offset diluent and/or oxidant orifices from outer feeder(s) into a downstream combustor Blend-Trim region, according to some examples.
  • Fig.4K is a Radial Axial detail view of axially and circumferentially offset fuel and oxidant orifices from inner feeders into a combusting chamber axially and/or radially offset from opposed feeder orifices, according to some examples.
  • Fig.4L is a Radial Axial detail view of axially and circumferentially offset diluent and/or oxidant orifices from outer feeder(s
  • Fig.4M is a Radial Axial detail view of axially and circumferentially offset diluent and/or oxidant orifices from inner feeder(s) into a combustor Blend-Trim region axially and/or radially offset from radially opposed feeder orifices, according to some examples.
  • Fig.4N is a Radial Axial elevation view of a CounterClockWise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig.4N is a Radial Axial elevation view of a CounterClockWise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig. 4O is a Radial Axial elevation view inwardly adjacent to a CounterClockWise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig. 4P is a Radial Axial elevation view inwardly adjacent to a clockwise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig. 4Q is a Radial Axial elevation view of a clockwise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.
  • Fig.4R is a Radial Axial detail view of Fuel and offset oXidant delivery orifice spacing in fuel and oxidant feeders radially adjacent to a Scalable Combusting Region, according to some examples.
  • Fig.4S is a Radial Axial detail view of fuel and aligned oxidant orifices in feeders adjacent a combusting region.
  • Fig. 4T is a Radial Circumferential detail view of fuel and oxidant orifice orientations into a combusting chamber from adjacent feeders, according to some examples.
  • Fig.4R is a Radial Axial detail view of Fuel and offset oXidant delivery orifice spacing in fuel and oxidant feeders radially adjacent to a Scalable Combusting Region, according to some examples.
  • Fig.4S is a Radial Axial detail view of fuel and aligned oxidant orifices in feeders adjacent a combusting region.
  • Fig. 4T
  • Fig. 4U is a Radial Circumferential elevation detail view of fuel and oxidant channels and orifices in outer and inner feeders adjacent a radially outward combusting region, according to some examples.
  • Fig. 4V is a Radial Circumferential detail view of an oxidant orifice in a combusting chamber wall, according to some examples.
  • Fig.4W is a Radial Circumferential detail view of an angled oxidant orifice in a combusting chamber wall, according to some examples.
  • Fig.4X is a Radial Axial detail view of an oxidant feeder closed end, according to some examples.
  • Fig.4Y is a Radial Axial detail view of a fuel feeder closed end, according to some examples, according to some examples.
  • Fig.5A is a Circumferential-Radial Cross-section of Combusting Chamber With Radial Combusting Regions, according to some examples.
  • Fig.5B is a Circumferential-Radial Cross-section of Combusting Chamber With Combusting Regions at a Skew Angle to the Radial Axis, according to some examples.
  • Fig.5C is a Close-Up Perspective View of The Combusting Regions at a Skew Angle to the Radial Axis, according to some examples.
  • Fig.5D is a Graph of hot gas temperature T35 versus combustor radius R, from temperature T35i at an inner radius Ri, to temperature T35o at an outer radius Ro, at the downstream end of the fuel delivery region at the axial location CZ35, according to some examples.
  • Fig. 5E is a Graph of hot gas temperature T4 versus combustor radius R, from temperature T4i at inner radius Ri to temperature T4o at outer radius Ro, at the combustor outlet CZ4, according to some examples.
  • Fig.5F is a Graph of hot Wall Temperature TW versus combustor axial length Z, from a wall temperature TW35 at the downstream end of the fuel delivery region CZ35, to a wall temperature TW4 the combustor outlet at CZ4, according to some examples.
  • Fig.5G is a Graph of hot gas mean Velocity V4M versus combustor radius R at the combustor outlet CZ4, from inner velocity V4i at inner radius R4i to outer velocity V4o at outer radius Ro, according to some examples.
  • Fig.5G is a Graph of hot gas mean Velocity V4M versus combustor radius R at the combustor outlet CZ4, from inner velocity V4i at inner radius R4i to outer velocity V4o at outer radius Ro, according to some examples.
  • 5H is a Graph of hot gas temperature T versus combustor circumferential angle Theta ( ⁇ ), cooled near downstream stators, with Inner Temperature Ti at combustor inner radius Ri, and Outer Temperature To at outer radius Ro, from a first combustion section Theta1 ( ⁇ 1) to a second clockwise combustion section Theta2 ( ⁇ 2), according to some examples.
  • Fig. 1 a Graph of hot gas temperature T versus combustor circumferential angle Theta ( ⁇ ), cooled near downstream stators, with Inner Temperature Ti at combustor inner radius Ri, and Outer Temperature To at outer radius Ro, from a first combustion section Theta1 ( ⁇ 1) to a second clockwise combustion section Theta2 ( ⁇ 2), according to some examples.
  • 5I is a Graph of hot gas temperature T versus combustor circumferential angle Theta ( ⁇ ), heated near downstream stators, with Inner Temperature Ti at combustor inner radius Ri, and Outer Temperature To at outer radius Ro, from a first combustion section Theta1 ( ⁇ 1) to a second clockwise combustion section Theta2 ( ⁇ 2), according to some examples.
  • Fig.5J is a Graph of hot gas velocity V versus combustor circumferential angle Theta, for Inner Velocities Vi at combustor inner radius Ri, and Outer Velocities Vo, at outer radius Ro, with a cooled counterclockwise first combustion section at Theta1 ( ⁇ 1) and a clockwise second combustion section at Theta2 ( ⁇ 2), according to some examples.
  • Fig. 5K is a Scalable Omega Combustor Equilibrating Region Radial-Axial Cross-Section Elevation View, according to some examples. [0080] Fig.
  • Fig. 5L is a Premixed Scalable Combustor Premixing of Fuel, Oxidant and Diluent, Radial-Axial Plan View, according to some examples.
  • Fig.5M is a Plan View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.
  • Fig. 5N is a Perspective View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.
  • Fig.5O is a Schematic Plan View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.
  • Fig.5P illustrates Fuel/Oxidant Orifices in Ignition Authority Upper Inner Wall Plan View, according to some examples.
  • Fig. 5Q is a Ignition Authority Mid-Section Plan View, according to some examples.
  • Fig.5R illustrates Fuel/Oxidant Orifices in Ignition Authority Lower Inner Wall Plan View, according to some examples.
  • Fig.5S is a Schematic Plan View of an Ignition Authority Inner Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.
  • Fig.5T is a Close-up schematic of Igniter in Wall of the Pilot Combusting Region, according to some examples.
  • Fig. 5U is a Radial-Axial Cross Section of Combustor Wall Fluid Cooling Capable of Ammonia Cracking, according to some examples.
  • Fig.5V is a Radial Inner to Outer Temperature Profile (T vs R) of Equilibrating Zone Flow Temperature Upstream at CZ39 and Downstream at CZ4, according to some examples.
  • Fig. 6A is a Power Versus Temperature Graph of Brayton Cycle and VAST Cycles, according to some examples.
  • Fig.6B is a Schematic of Control System Configuration of Controller Subsystems, according to some examples.
  • Fig.6C is a Schematic Graph of Control System with Control Sections, according to some examples.
  • Fig.6D is a Schematic Graph of Control System with Sensors, according to some examples.
  • Fig. 6E is a Schematic Graph of Low Pilot and Combustor Temperatures, Expander-Generator Speeds, and Power Generation versus Time Showing Flexible Operations, according to some examples.
  • Fig.6F is a Schematic Graph of High Pilot and Emergency Combustor Temperatures, Expander-Generator Speeds, and Power Generation versus Time Showing Flexible Operations, according to some examples.
  • Fig.6G is a Combined Schematic Graph of Flexible & Emergency Low and High Pilot and Combustor Temperatures, Expander-Generator Speeds, and Power Generation versus Time, according to some examples.
  • a conventional combustor’s delivery of fluids is impacted by the ability of combustor systems and processes used to spatially and/or temporally control the delivery of fuel (or reactant), oxidant (or co-reactant), and diluent fluids.
  • Combustion and emissions (or reaction and byproducts) are often impacted by the distribution and rates of conventional fluid delivery and mixing. These are typically limited by physical, thermal, and temporal apparatus, fluid design, delivery, cooling systems, control processes, and material thermal and strength constraints.
  • Micro- to large Brayton gas turbines nominally use about 420% to 280% excess air to cool combustion to tolerable Turbine Inlet Temperatures (herein “TIT”) over a range of about 1,000°C (1,832°F) to 1,500°C (2,732°F).
  • TIT Turbine Inlet Temperatures
  • Such large excess air flows increase the size and cost of compressors which are typically the most expensive component in Simple Cycle gas turbines. Compressing and re-expanding such large excess air fractions cause system losses in Brayton turbines. Large gas flows cause uncertainties in measuring TIT.
  • Combustor systems or reactor systems deliver fluids through relatively few passageways or orifices. Increasing fluid mixing typically incurs substantial pressure drops with associated power losses to achieve turbulence of injected fluids.
  • gas turbine combustors may have fluid flow pressure drops of 2.5% to 5% of combustor inlet pressures, thus increasing compressor size and cost, while reducing system power and efficiency.
  • Reducing gas turbine emissions to certain levels (e.g., regulatory-imposed levels) in hot lean air diluted flames increases complexity and cost.
  • Brayton gas turbine emissions such as nitrogen oxides (NO, N2O, and NO2, referred to herein collectively as “NOx”) and carbon monoxide (referred to herein as “CO”) are typically substantially higher than international and other jurisdictionally legislated limits. Certain large gas turbines may be limited to operating above 50% of design power to constrain NOx generation, and to enable NOx emission catalytic cleanup to below legislatively prescribed levels.
  • ppmvd Oxygen
  • ppmvd Oxygen
  • NOx legislated limits for example in the state of California in the United States.
  • CH4 Combusting methane
  • UHC Unburned Hydrocarbon
  • NOx emissions generally increasing exponentially with temperature.
  • Some gas turbines are being designed with the TIT approaching 1,700°C (3,092°F) which will likely amplify NOx emissions and increase CO emissions. Reducing NOx and CO emissions typically involves catalytic reduction systems that increase system complexity and may cost from 4% to 7% of installed capital cost.
  • Rising use of renewable (“sustainable” or “green”) fuels such as hydrogen, ammonia (referred to herein as “NH3”), methanol (referred to herein as “CH3OH”), and ethanol (referred to herein as “CH5OH”), may raise combustor design, control, and durability issues.
  • hydrogen use can increase intra-combustion temperatures, extend flammability limits, and increase emissions, such as of CO and NOx.
  • Ammonia (NH3) is generally available for agriculture and is a leading candidate for renewable fuels. However, conventional ammonia combustion commonly generates higher NOx than legislated emission levels. Ammonia low flame speed may further impact combustion operating regimes. Cracking ammonia back to hydrogen and nitrogen typically requires more equipment, heat, catalysts, and operating effort.
  • Increasing non-dispatchable renewable power use is rapidly increasing the frequency of backup power use to sustain grid power frequency, and for minimizing or preventing grid blackouts. Frequent large thermal cycling with high temperatures can lead to lessening the life of insulating tiles in cylindrical “can” combustors and additionally fatigue combustor sides.
  • Increasing ambient temperatures typically reduce conventional gas turbine power. This causes reductions in backup power capacity when it is most needed for cooling in hot climates.
  • Brayton cycle “peaker” gas turbines may lose ⁇ 13% in peak power and a further ⁇ 2.5% in efficiency for a 25 kelvin (Celsius deg) increase in ambient temperature from rated power at 15 deg C up to 40 deg C (59 deg F to 104 deg F) hot ambient conditions.
  • Higher combustion temperature at peak power typically rapidly increases blade creep that reduces a gas turbine’s useful life.
  • just increasing temperature as power increases from 70% to 100% in conventional Brayton “peaker” gas turbines may cause about a 300-fold reduction in life, due to rapidly increasing creep with higher temperature.
  • a ten kelvin increase or decrease in TIT may halve or double the life of some gas turbines.
  • CIASO Besides rapid 15-minute dispatches, CIASO has now added faster 5-minute dispatches. CIASO has even introduced 1 minute interval emergency dispatches to stabilize grid voltage and control grid frequency. Ramp up rates for major combined cycle and industrial gas turbines were up to 8 hours to avoid turbine fatigue. Now, ramp rates may be reduced from 30-minute startups to about 10 minutes for combined cycles, 5 minutes for industrial turbines, and even 2 minutes for aeroderivative turbines. [0121] CAISO’s increasingly frequent dispatches may be causing higher thermal cyclic fatigue that can lead to shortening the life of gas turbines and turbine blades. This requires more frequent inspections, and refurbishments, with a markedly shorter useful life.
  • the techniques described herein include combustors that combust fuel with an oxidant (e.g., air or oxygen), and that may add a diluent such as water, carbon dioxide, nitrogen or excess oxygen, in any phase and/or combination, in ways that are more scalable across broader ranges of commercial combustor pressures, temperatures, and/or power levels, therein improving power system capabilities and economics.
  • oxidant e.g., air or oxygen
  • a diluent such as water, carbon dioxide, nitrogen or excess oxygen
  • Diffusing Region techniques include varying delivery of liquid and/or gaseous diluent through multiple orifices into the upstream fluid delivery region, therein improving fluid delivery rates, liquid evaporation, and/or combustion. Pilot Ignition [0132] Techniques include providing a diluted fuel rich pilot to more cleanly provide ignition of downstream fluid delivery, therein initiating reliable combustion while reducing the generation of NOx emissions.
  • Techniques further include providing an oxidant rich manifold, and a fuel rich manifold transversely adjacent to one or more combusting chambers, therein improving scalability, mixing, combustion, and economics.
  • Techniques include providing a diluent manifold or duct adjacent to an oxidant or fuel manifold, mixing gaseous and/or liquid diluent with oxidant and/or fuel, and delivering mixed fluid through orifices, therein facilitating fluid mixing and delivery.
  • Techniques include providing a diluted oxidant rich manifold between perpendicularly or transversely adjacent combusting chambers, therein reducing the number of oxidant manifolds, and improving manufacturability and economics.
  • Techniques include providing a diluted fuel rich manifold between perpendicularly or transversely adjacent combusting chambers, therein reducing the number of fuel manifolds, and improving manufacturability and economics.
  • Techniques include providing the upstream combusting chamber in a transversely elongated distribution having a transverse width to perpendicular (or radial) depth ratio normal to the flow axis greater than 1.15, and with fuel, oxidant, and diluent fluid delivery through the elongated walls, therein improving fluid mixing into and/or in the combusting chamber.
  • Techniques include adjusting the angle orifices transverse to the fluid flow relative to the combusting chamber wall surface normal, therein improving combusting fluid mixing.
  • Techniques include adjusting the number of transversely distributed fuel and oxidant fluid delivery orifices through opposing shallowly displaced sides of the combustor, as a function of axial distance upstream to downstream, therein improving combusting fluid mixing and combustion reliability.
  • Techniques include transversely offsetting oxidant rich fluid orifices relative to fuel rich fluid orifices, therein improving fluid mixing.
  • Techniques include changing or reducing upstream diluent/oxidant and/or diluent/fuel ratios, relative to hot pilot fluid delivery and/or to downstream combustor orifices, therein improving upstream combustibility and extending combustion delivery limits.
  • Techniques include delivering fuel rich fluid through adjacent transverse fuel feeders, and oxidant rich fluid through separate adjacent transverse oxidant feeders, through respective orifices into the combusting chamber, therein improving combusting fluid mixing, and reducing quenching or flashback risks.
  • Techniques provide configuring combustor upstream transverse width versus axial length profiles, of one or more combusting chambers, within combustion stability, manufacturability, and aerodynamic flow efficiency objectives, therein improving reliability and competitiveness.
  • Blend Trim Region Techniques include controlling remaining diluent delivery and mixing in the blend trim region, to axially control cumulative diluent to fuel mass ratios Omega, therein configuring axial combusting and equilibrating temperature profiles and reducing emissions to below prescribed regulatory levels.
  • Techniques include controlling remaining oxidant delivery and mixing in the blend trim region, to axially and/or transversely control cumulative relative oxidant to fuel mass stoichiometric ratios Lambda, therein configuring axial and/or transverse combusting and equilibrating oxidant profiles and reducing emissions to below prescribed regulatory levels.
  • Techniques further provide controlling upstream pilot combusting region temperature equal to or greater than downstream combusting chamber diluted fuel oxidant mixture standby ignition temperature, therein improving pilot reliability; [0147] Techniques may provide multiple upstream pilot chambers feeding respective scalable combusting chambers or regions, therein improving combustion scalability, range, ramp rate, and/or reliability.
  • Combustor Outlet Temperature Control and Scaling [0148] Techniques may further improve control of Combustor Outlet Temperature (COT), or Turbine inlet Temperature (TIT), reduce outlet temperature variation, and/or reduce outlet temperature uncertainty.
  • COT Combustor Outlet Temperature
  • TIT Turbine inlet Temperature
  • Techniques may include configuring fluid delivery to control diluent to fuel mass ratio Omega with the relative oxidant to fuel ratio Lambda across a plurality of orifices, therein scaling combustor designs across wide temperature ranges, e.g., between about 700°C to 2,500°C for commercial combustors and/or gas turbines.
  • Techniques may control fuel, oxidant, and/or diluent fluid delivery rate per combustor volume, (MW/m3-atm) and provide predominantly axial laminar flow within the combustor, therein improving transverse combustor outlet or turbine inlet temperature (TIT) control, expander durability, and economics.
  • TIT turbine inlet temperature
  • Techniques provide for designing combustor fuel, and/or oxidant spatial fluid delivery rates to substantially reduce NOx and CO emissions relative to conventional combustors. In some configurations these may deliver NOx and CO emissions below legislated emission limits; e.g., NOx and/or CO below 75 ppmvd.
  • Techniques further include reducing NOx and/or CO emissions while controlling combustor outlet temperature within a range from 500°C to 2,500°C, by using thermal diluent spatial fluid delivery rates, therein increasing applications, thermal efficiency, and/or economics; e.g., by controlling the H2O, CO2, N2, O2 and/or other diluent to fuel mass delivery ratio Omega, for an Omega greater than about 1.15, (or the corresponding enthalpy delivery ratio) and with lower catalyst and reductant usage than with Brayton turbines.
  • thermal diluent spatial fluid delivery rates e.g., by controlling the H2O, CO2, N2, O2 and/or other diluent to fuel mass delivery ratio Omega, for an Omega greater than about 1.15, (or the corresponding enthalpy delivery ratio) and with lower catalyst and reductant usage than with Brayton turbines.
  • the techniques described herein include scalable ultraclean combustion (or chemical reaction) and equilibration equipment, configurations, and processes. These may progressively deliver and combust mixtures of fuel, oxidant, and thermal diluent along the axial flow direction. These techniques may deliver fluids via one or more fuel, oxidant, and diluent fluid manifolds, through numerous fuel, oxidant, and/or diluent orifices into one or more upstream combusting chambers, and downstream Blend-Trim regions.
  • Such techniques described herein may comprise one or more upstream transversely elongated combusting chambers with shallowly separated combusting chamber walls relative to the axial flow direction, (referred to herein as “transversely elongated”).
  • Combusting techniques may configure enclosed transverse cross-sectional combusting areas that generally increase along the axial flow direction.
  • Such techniques may configure fluid compositions in combusting regions preferably provide upstream fuel rich conditions, while maintaining combusting temperatures above quench limits.
  • These techniques may distribute numerous fuel fluid (or reactive fluid) orifices and oxidant fluid (such as air, or co-reactant fluid such as oxygen) orifices across the transversely elongated shallowly separated combusting chamber sides.
  • Fuel and/or oxidant fluids may be fed into the fuel and oxidant fluid orifices from respective fuel and/or oxidant manifolds.
  • Further techniques may configure downstream Blend-Trim regions with similar transversely elongated walls with shallow spacing, configured transversely and normal to the axial fluid flow axis.
  • Blend-Trim techniques may similarly configure oxidant and/or diluent delivery through numerous orifices in transversely elongated shallowly spaced walls about the combusting flow. These techniques may further combustion, control combustor axial and outlet temperature(s), and control emissions (or minor products).
  • Techniques may further mix diluent fluid with fuel fluid, oxidant fluid, and/or Blend-Trim oxidant fluids to deliver them into the combusting chamber, and/or Blend- Trim region, through respective fuel, oxidant, and/or Blend-Trim orifices. Similar techniques may use upstream flame authorities comprising fuel, oxidant, and diluent with rich primary combustion and downstream oxidant and diluent trim, wherein similarly constraining combustion temperatures to provide reliable combustion while constraining emissions. [0159] Such techniques may vary the composition of fuel, oxidant, and/or diluent delivered into upstream versus downstream combusting and/or Blend-Trim regions.
  • Such combusting and Blend-Trim regions may be replicated to scale the combustor(or reactor) to provide the combusting power (or reacting rate) desired while achieving improved mixing and low emissions (or byproducts).
  • combusting fluid temperature in an upstream combusting chamber 740 and/or a downstream Blend-Trim region 850 may be controlled by controlling one or more of the ratios of diluent fluid F7 to fuel fluid F1, diluent fluid F7 to oxidant fluid F4, and/or diluent fluid F7 to Blend-Trim oxidant fluid F4, in diluted fuel fluid delivery F2, upstream diluted oxidant fluid delivery F5, and/or downstream Blend-Trim diluted oxidant fluid delivery F15, and diluent fluid F7, and/or liquid diluent fluid F14 delivered into the Blend-Trim region.
  • the transverse cross- sectional area (X-Y axes) of the combusting chamber 740 may be progressively increased along the axial fluid flow direction (Z axis) to progressively increase the combusting chamber volume, and to accommodate gas expansion from increasing temperature. This may beneficially reduce axial fluid acceleration and fluid pressure drop across the combustor.
  • An upstream diluted ignition authority or pilot 720 may be configured to provide a diluted pilot flame F22 to reliably ignite downstream fuel fluid F2 and diluted oxidant fluid F5. This may include controlling a pilot combusting temperature and pilot combusting emissions resulting in pilot fluid F22.
  • a downstream diffuser 429 may be used to reduce an axial combusting fluid pressure drop while providing additional combusting (or reacting) residence time to reduce unburned fuel and combusting (or reacting) emissions such as carbon monoxide and oxides of nitrogen.
  • combusting fluid oxidant concentration (or oxidant to fuel ratio) in the combusting region 740 may be varied between an upstream combusting region 742 and a downstream combusting region 744.
  • the order and magnitude of residual oxidant fluid and/or of residual diluent fluid may be varied in the Blend-Trim region 850.
  • a scalable reactor or scalable combustor 700 are depicted in Fig.1A, as further detailed in Fig.1B through Fig. 1I.
  • These embodiments exhibit one or more transversely elongated shallow combusting chambers 740 in a combustion section 730, disposed between combusting chamber near and far side feeder walls and 737 spaced shallowly apart (along the Y axis), and bounded transversely (along an X axis) to a longitudinal axial flow direction (along a Z axis) by combusting chamber near end walls 734 and far end walls 735 perpendicular to the longitudinal axial flow direction (along the Z axis) from an upstream inlet region 134 to a downstream outlet 136.
  • FIG.2A Further embodiments of a scalable reactor or scalable combustor 706 with a combusting section 730 are shown in Fig.2A as further detailed in Fig.2B through Fig. 2E.
  • a blower 406 may be used to compress an intake air or oxidant mass flow WX2, comprising optional liquid diluent F7, to a pressurized oxidant mass flow WX3 and deliver it to the inlet of a diffuser 420 at axial location CZ31.
  • Such configurations may include an upstream diluent delivery section 710 comprising diluent delivery spray system 24, an ignition section 720 comprising an ignition authority or pilot 100, the combusting region 740, the Blend – Trim region 850 for further oxidant and diluent delivery, and an equilibration zone 750. These may deliver a hot fluid flow W4 exiting the combustor 706 after the end of the equilibrating zone 750 at CZ 394.
  • Transversely Elongated Perforated Combustor Side Walls Certain embodiments of a cuboidal configuration of the scalable reactor or combustor 700 are depicted in Fig.1A, as further detailed in Fig. 1B through Fig.1I.
  • the cuboidal scalable reactor or combustor 700 may be formed by creating one or more transversely elongated shallow reacting regions or combusting chambers 740 in an upstream combustion section 730 of the scalable reactor or combustor.
  • the embodiment of Fig. 1A including detail in Fig. 1B, displays the scalable combustor 700 oriented with an upstream inlet region 134, near an upstream combustor end wall 241, with an upstream pilot chamber 720.
  • Said scalable combustor 700 has a downstream combustor outlet 136 at the downstream combustor end (or top in the Z direction).
  • the scalable combustor 700 is configured with a flow direction from an upstream pilot fluid F22 flow at the upstream inlet 134, to an energetic fluid F20 exiting the combustor outlet 136, along a generally upward vertical direction (similar to the vertical Z axis).
  • the flow axis of the scalable combustor 700 may be oriented horizontally, or downwards, or at some intermediate angle.
  • the upstream combustion section 730 may comprise one or more elongated shallow reacting or combusting chambers 740 generally elongated in a transverse direction (X axis).
  • this is depicted as generally perpendicular to the primary axial flow direction (along the Z direction).
  • such one or more combusting chambers 740 may be generally shallowly displaced in a normal direction (Y axis) perpendicular to the transverse elongation direction, (typically normal to both the axial flow in the Z axis and to the transverse X direction).
  • Figs. 2B, Fig. 2D, and Fig. 2E detail such scalable reactor configurations 706, depicted here in a similar cuboidal configuration.
  • Fig.2B, Fig.2D, and Fig.2E similarly show the combusting section 730 with the combusting chamber 740 bounded by transversely elongated (“far” side) oxidant feeder perforated wall 737, and an opposing combusting chamber transversely elongated (“near” side) fuel feeder perforated wall 736.
  • the combusting chamber 740 may further be configured into an upstream combusting chamber 742, and a downstream combusting chamber 744.
  • Upstream combusting chamber 742 may be bounded by upstream perforated fuel feeder 805 with orifices 81 and upstream perforated oxidant feeders 815 with orifices 82.
  • Downstream combusting chamber 744 may be bounded by downstream perforated fuel feeder 806 with orifices 81 through fuel feeder walls 736, and downstream perforated oxidant feeders 816 with orifices 82 through oxidant feeder walls 737.
  • Combusting Chamber Transverse End Walls [0170] Further per Fig.
  • such transversely elongated shallow combusting chambers 740 may generally be configured between correspondingly sized combusting chamber side fuel feeder walls 736 and oxidant feeder walls 737 similarly transversely elongated along the X direction.
  • the combusting chamber 740 between such elongated combusting side fuel feeder walls 736 and oxidant feeder 737 may be transversely bounded along the transverse X direction by combusting chamber bounding end walls.
  • These transverse end bounds typically include a combusting chamber near end wall 734 (in the negative X direction), and a combusting chamber far end wall 735 (in the positive X direction).
  • transversely elongated shallow combusting chambers 740 with combusting chamber side feeder perforated walls 736 and 737 may be transversely bounded by combusting chamber bounding end walls such as end walls 734, similar to that shown in Fig. 1A, Fig. 1C, and elevation view Fig.1D.
  • Shallowly Separated Combusting Chamber Side Walls [0172] Per Fig.1A, the elongated far side feeder wall 737 and near side feeder wall 736 may be spaced shallowly apart with a shallow spacing depth 748 in the Y direction perpendicular (normal) to both the axial flow and the transverse X direction.
  • Such shallow spacing depth 748 may separate near side feeder walls 736 and far side feeder walls 737 relatively closer, in the perpendicular Y direction, than the transverse elongated width 746 separating the near end wall 734 from the far end wall 735 and bounding the elongated combusting chamber 740 along the transverse X direction.
  • Such shallow separation spacing 748 or perpendicular (normal) combusting chamber depth, between elongated side feeder walls 736 and 737 bounding the combusting chamber 740, may be provided by a corresponding shallow separation depth of the near side bounding walls 734 and far side bounding walls 735 separating elongated nearside feeder walls 736 and elongated far side feeder wall 737 along the Y axis perpendicular to the Z flow axis.
  • a separated fuel-oxidant scalable combustor may be formed having at least one first fluid or fuel manifold 770 configured to deliver first fuel fluid F1, comprising fuel fluid (and/or reactant fluid), to one or more perforated fuel feeders 750 (or first fluid reactant perforated delivery ducts) such as shown in Fig.1D and Fig.1I.
  • this embodiment may comprise at least one second fluid or oxidant manifold 780 configured to deliver second oxidant fluid F4 comprising oxidant fluid (or second co-reactant) through oxidant manifolds 780 to one or more perforated second fluid or oxidant delivery ducts or oxidant feeders 760 having a plurality of oxidant orifices 82 to deliver second oxidant fluid F4 into the combusting chamber 740.
  • second fluid or oxidant manifold 780 configured to deliver second oxidant fluid F4 comprising oxidant fluid (or second co-reactant) through oxidant manifolds 780 to one or more perforated second fluid or oxidant delivery ducts or oxidant feeders 760 having a plurality of oxidant orifices 82 to deliver second oxidant fluid F4 into the combusting chamber 740.
  • the first fuel fluid F1 may be mixed with third diluent fluid F7 to form and deliver a diluted fuel fluid F2 for delivery into fuel manifold 770, and thence into perforated fuel feeders 750 (or perforated reactant delivery duct).
  • the second oxidant fluid F4 comprising oxidant fluid and/or co-reactant fluid may be diluted with diluent fluid F7 to form diluted oxidant (and/or co-reacting) fluid F5 for delivery into oxidant manifold 760.
  • diluted first fluid or fuel fluid F2 may similarly be delivered from fuel manifold 770 into perforated fuel feeders 750 adjacent to the combusting chamber(s) 740.
  • diluted second fluid, diluted oxidant (or co-reactant) fluid F5 may be delivered from oxidant manifold(s) 780 into oxidant fluid feeder (perforated duct(s)) 760 adjacent to combusting chamber(s) 740.
  • a central combusting/feeder region 739 may comprise one or more fuel feeders 750 having perforated near side fuel feeder wall(s) 736, and one or more oxidant feeders 760 (perforated second fluid ducts) having perforated far side oxidant feeder wall(s) 737.
  • These fuel feeders 750 and oxidant feeders 760 may form proximate combusting chambers (or zone(s)) 740 between opposing fuel feeders 750 and oxidant feeders 760, and bounded by perforated fuel feeder walls 736 and oxidant feeder walls 737, and combusting chamber end walls 734 and 735.
  • fuel fluid orifices 81, oxidant fluid orifices 82, and Blend-Trim oxidant ports or orifices 83 in the respective near side fuel feeder walls 736, and far side oxidant feeder walls 737, Blend-Trim oxidant near side feeder walls 856 and Blend-Trim oxidant far side feeder walls 857 may be configured to provide respective distributions of one or more of fluid port diameters and port spacings along the streamwise flow direction. These may be configured to provide desired streamwise distributions of fuel fluid and oxidant fluid delivery to achieve desired streamwise composition distributions in the energetic fluids within a plurality of streamwise reaction zones.
  • fuel fluid orifices 81, and oxidant fluid orifices 82 may be configured in fuel feeder walls 736, and oxidant feeder walls 737. These deliver fuel fluid F2 through diluted fuel feeder 804, and oxidant fluid F5 through diluted oxidant feeder 814 into the combusting chamber or region 740.
  • upstream and downstream fuel and oxidant fluid delivery feeders may be configured to feed fuel and oxidant fluids with different diluent compositions into upstream combusting regions 742 and downstream combusting regions 744.
  • fuel fluid F1 may be delivered through perforated fluid delivery feeder 805 via fuel orifices 81 into upstream combusting chamber(s) 742.
  • diluted fuel fluid F2 may be delivered through downstream fuel fluid delivery feeder 806 via fuel orifices 81 into downstream combusting chamber(s) 744.
  • oxidant fluid F4 may be delivered through upstream perforated oxidant fluid delivery feeder 815 via oxidant orifices 82 into the upstream combusting chamber 742.
  • diluted oxidant fluid F5 may be delivered through downstream oxidant fluid delivery feeder 816 via oxidant orifices 82 into a downstream combusting chamber 744.
  • upstream and downstream fuel fluids F1 and F2 may comprise differing diluent compositions.
  • the diluent to fuel ratio Omega1 and Omega2 of fuel fluids F1 and F2 may be configured differently in the upstream perforated fuel feeder 805 versus the downstream perforated fuel feeder 806. This enables controlling the temperature differently upstream combustion region 742 verses downstream combusting region 744 degrees of diluent to fluid composition.
  • upstream and downstream oxidant fluids F4 and F5 may comprise differing degrees of diluent to oxidant composition.
  • These fluids may be configured to control the relative oxidant to fuel ratio to stoichiometric oxidant to fuel ratio Lambda of F4 in the upstream oxidant feeder 815 into the upstream combusting region 742 differently from the relative oxidant to fuel ratio Lambda of diluted oxidant fluid F5 in the downstream oxidant feeder 816 into the downstream combusting region 744.
  • This enables controlling combusting region richness (relative oxidant to fuel ratio) and thus the fuel combusting or oxidizing rate in the upstream combusting region 742 differently from that the downstream combusting region 744.
  • the separated fuel-oxidant combustor may be configured in generally transversely elongated shallow combusting chambers 740, (such as rectangular-like configurations) between opposed perforated duct sides (or liners) and in an axial direction along the fluid flow.
  • the scalable combustor 700 may be configured with a downstream transversely expanding (or hand “fan”) shape combusting chamber 740, between transversely bounding end walls 734 and 735 (in the X direction), (between shallowly separated side feeder walls 736 and 737) that generally increases transversely (in the X direction) to the fluid flow, along the streamwise flow direction (along the Z axis) and with progressively increasing fluid flow.
  • This scalable combustor may be configured such that the cross-sectional area of the combusting (or reacting) zones increases with increasing axial distance along the flow direction.
  • the opposed fuel fluid and oxidant fluid delivery through perforated fuel and oxidant feeders may comprise individually mixed proportions of diluent as desired to achieve a desired axial temperature distribution.
  • the effectiveness of the Thermal Barrier Coating (TBC) may be adjusted (or the TBC removed) to configure the heat transfer rate from the reaction zone to the fluid within one or both adjacent ducts.
  • Downstream Blend-Trim Region [0186] Per Fig. 1A, and Fig. 1C, a Blend-Trim section 426 comprising a Blend-Trim region 850 may be configured downstream of the combustion section 730 comprising the combusting chamber 740. This Blend-Trim region 860 may deliver one or both of further oxidant fluid F4 and/or further diluent fluid F7.
  • Blend-Trim region may axially begin at an adjacent upstream Blend-Trim manifold bounding wall 248 separating fluid delivery into the upstream combusting chamber (or region) 740 from diluted oxidant fluid delivery into the downstream Blend-Trim region 850.
  • the Blend-Trim region 850 may extend to a downstream Blend-Trim Manifold and Blend-Trim feeder bounding wall 249.
  • 1A further depicts a portion of the transversely elongated downstream Blend-Trim region near side wall 856 and Blend-Trim region far side wall 857 between transversely bounding near end wall 734 and transversely bounding far end wall 735, (or between counterclockwise walls 250 and clockwise walls 251) such as shown in Fig.1D and Fig.1H.
  • the downstream Blend-Trim region side wall 856 and side wall 857 may further extend between axial boundaries of Blend- Trim region upstream wall 248 and Blend-Trim region downstream wall 249.
  • Blend-Trim oxidant ports or orifices 83 in the Blend-Trim oxidant near side feeder walls 856 and equivalent Blend-Trim oxidant farr side feeder walls 857 may be configured to provide respective distributions of one or more of fluid port diameters and port spacings along the streamwise flow direction. These may be configured to provide desired streamwise distributions of oxidant fluid delivery and/or optional diluent fluid delivery to achieve desired streamwise composition distributions in the energetic fluids within a plurality of streamwise reaction zones.
  • the combusting chamber 740 has a transverse width 746 along the transverse X direction, between transverse near end walls 734 and transverse far end walls 735 bounding the combusting chamber 740.
  • Such combusting chamber transverse width 746 may generally increase along the Z axial flow direction in the combustion section 730 from an upstream combustor inlet (or pilot outlet) 134, near an upstream combustor end wall 241, and progressively increasing with downstream distance along the Z flow direction.
  • the Blend-Trim flow region 850 has a transverse bounding separation or combusting transverse width 746 between near bounding end wall 734 and far bounding end wall 735.
  • Such transverse bounding width 746 may further increase in the transverse X direction within the Blend-Trim fluid delivery region 426 between the upstream Blend-Trim region manifold boundary 248 and a corresponding downstream Blend-Trim region boundary 249, and downstream of the combusting chamber 740.
  • the transverse bounding width 746 may be fairly uniform in the Blend-Trim region 426.
  • the transverse end walls 734 and 735 may be configured with an upstream convex wall section 731, providing a non-linearly increasing bounding separation width 746 between those transverse bounding walls.
  • the upstream transverse end walls 734 (and 735 not shown), may be configured with upstream curved convex end wall sections 731 with radial to axial slopes increasing with downstream axial distance.
  • the convex end wall section 731 bounding combustion section 730 may be followed downstream by an end wall section 732 with a maximum slope (or low curvature) of transverse increase with axial distance.
  • the combustion section 740 may be bounded axially midway by an end wall section 732 having a maximum slope of transverse increase with axial distance, or similar section with low radial to axial curvature.
  • Such a maximum slope end wall section 732 in one or both bounding end walls 735 and/or 734 may be configured to provide a low curvature (or fairly linear) increase in the transverse bounding separation between those bounding end walls.
  • Such maximum slope (low curvature or fairly linear) sections may be utilized to accommodate overhang slope limitations in 3D printing manufacturing of such bounding end walls. E.g., such as when 3D printing may be used to form the bounding end walls 735 and/or 735 with the combusting Z axis in the vertical gravitational direction.
  • the bounding end walls 734 (and similarly bounding end walls 735) of the combusting section 740 may similarly have maximum radial to axial slopes 732 with fairly linear radial to axial slopes (or low curvature).
  • the transverse bounding end walls 734 and 735 may further be configured with a downstream concave wall section 733 downstream of the fairly linear bounding end wall section 732.
  • This downstream generally concave transversely bounding end wall section 733 providing a non-linear section with the bounding separation width 746 between those transverse bounding walls further increasing along the axial Z flow direction.
  • Such concave nonlinear bounding end wall sections 733 in one or both bounding end walls 735 and/or 734 may be configured to provide a declining rate of increase along the axial Z flow direction.
  • the bounding end walls 734 (and similar end walls 735) of the combusting section 740 may similarly be configured with downstream concave radial to axial sloped wall sections 733 downstream of the transition bounding end wall section 732 with maximum slope. Radial to axial slopes of bounding sections 733 may decline towards zero curvature bounding the downstream Blend-Trim section 852 and thence to connect with downstream equilibrating section 750.
  • the diluent delivery section 710 near the inlet 134 may comprise delivering oxidant fluid F4 through an upstream oxidant manifold 242 and out through a plurality of perforated oxidant feeders 11 distributed across the upstream region.
  • a distributed fuel delivery system may inject diluent F7 through a downstream fuel manifold 244 and out through distributed perforated oxidant feeders 14 into incoming oxidant fluid F4.
  • the combusting chamber 740 may have an upstream pilot light, ignition source or flame authority 720, such as near the combustor upstream end wall 241. Ignition source 720 may form a diluted hot pilot flow F22 at the pilot outlet flowing into the adjacent combusting chamber 740.
  • the combusting chamber 740 may have an upstream Flame Holder or Ignition Authority 100 comprising a Pilot P with an inlet axially at CZ33 and an outlet axially at CZ34.
  • Combusting diluted pilot fuel may be delivered via hot gas delivery flame tubes 116 to one or more combusting chambers in Combustion Section 730 where the chambers may have Combustion Chamber Radially Outer Side Walls 736.
  • At least one of the scalable combusting region’s transversely elongated near side feeder wall (or “fan” wall) 736 and elongated far side feeder wall 737, bounding the adjacent combusting chamber 740 may comprise a plurality of fuel fluid orifices 81, or oxidant fluid orifices 82.
  • Such orifices may be configured about the one or more perforated combustor side (or liner) far side oxidant feeder walls 737 and near side fuel feeder walls 736 adjacent to at least one combusting chamber 740.
  • Such transversely elongated combustor near side fuel feeder walls 736 and far side oxidant feeder walls 737 may be generally shallowly opposed to each other about reacting or combusting chambers 740.
  • one or more diluted fuel fluids F2 (or fuel fluid F1 not shown) and/or diluted oxidant fluids F5 (or oxidant fluid F4 not shown) may be delivered through a plurality of perforated wall orifices 81 and 82 (in the Y, or negative Y direction) configured in the combusting region side fuel feeder (or liner) walls 736, and oxidant feeder (or liner) walls 737 adjacent to and into transversely flow combusting fluid F12 flowing axially (Z direction) along the combusting chamber 740.
  • Oxidant Wall Section Detail Fig.1F depicts a Diluted Oxidant Delivery Combusting Wall Section 745 having multiple oxidant fluid orifices 82 configured to deliver diluted co-reactant or oxidant fluid F5 (or oxidant fluid F4 not shown), and may be configured about fluid duct feeder wall 737 section of the combusting chamber 740 of Fig. 1A.
  • the near side oxidant fluid duct feeder wall 737 may have an optional thermal barrier coating (TBC) or insulating coating 738 protecting the fluid duct wall 132 from hot reacting or combusting fluid F12 flowing axially (Z direction) along the combusting chamber 740.
  • TBC thermal barrier coating
  • insulating coating 738 protecting the fluid duct wall 132 from hot reacting or combusting fluid F12 flowing axially (Z direction) along the combusting chamber 740.
  • FIG. 1E depicts a Diluted Fuel Delivery Wall Section 743 enlarged from the combusting chamber wall of Fig. 1A.
  • Fig. 1E depicts a portion of the transversely elongated upstream combusting chamber near side fuel feeder wall 736 between axial (Z axis) boundaries of the upstream end wall 241 and the downstream wall 248.
  • Combusting chamber wall section detail Fig.1E is further located between transverse near bounding wall 734 and far bounding wall 735 (along X axis), such as further detailed in Fig.1C, Fig.1D, and Fig.1H. [0206] Fig.
  • fluid duct feeder wall section 736 may optionally have a thermal barrier coating (TBC) or insulating coating 738 adjacent to the hot combusting fluid F12 flowing axially through the combusting chamber 740.
  • TBC thermal barrier coating
  • Blend-Trim Wall Section Detail Fig.1G depicts detail of an enlarged wall section 747 of the Blend-Trim Region 850 in the Blend-Trim section 426 downstream of the combusting chamber 740.
  • This Blend-Trim region wall section 747 of Fig. 1G may comprise one or more Blend-Trim orifices 83.
  • These Blend-Trim orifices 83 may be configured to deliver Blend-Trim diluted oxidant fluid F5 (and/or optionally diluent fluid F7 not shown) into an axially flowing Rich Reacting or Combusting Fluid F12 coming from the upstream combusting chamber into the Blend- Trim region 860 shown in Fig.1A.
  • Blend-Trim Wall Section Detail Fig. 1G such blend-trim orifices 83 may distributed across the Blend-Trim region wall section 856 to deliver Blend-Trim fluid F7 from Blend-Trim feeder 860 into the Blend-Trim region 850 within the downstream Blend-Trim section 426, as depicted in Fig.1A.
  • Such delivery of oxidant F5 in Blend- Trim diluted oxidant fluid F5 may increase the oxidant concentration of transversely flowing fuel rich combusting fluid F12 from the upstream combusting chamber 740.
  • fluid duct wall section 856 may have an optional thermal barrier coating (TBC) or insulating coating 738 protecting the Blend-Trim wall section 856 from the adjacent hot fuel rich (oxidant lean) energetic fluid F12 flowing downstream into the Blend-Trim region 850.
  • TBC thermal barrier coating
  • Fig. 2C details a Diluted Fluid Delivery Wall Section, comprising fluid orifices 80 extending through fluid duct / combusting chamber walls 132, and adjacent thermal insulating coating 150 on combusting chamber wall, to deliver fuel, oxidant, and/or diluent fluids such as further depicted in Fig.2D, and Fig. 2E.
  • fluid orifices 80 extending through fluid duct / combusting chamber walls 132, and adjacent thermal insulating coating 150 on combusting chamber wall, to deliver fuel, oxidant, and/or diluent fluids such as further depicted in Fig.2D, and Fig. 2E.
  • Pilot Fuel Fluid F3 delivery may be controlled by Fuel Control Valve 232 and delivered through Pilot Fuel Fluid Tube or Passage 101 to Flame Holder 100.
  • Pilot Oxidant Fluid F6 may be controlled by Pilot Oxidant Valve 232 and delivered through Pilot Oxidant Fluid Tube or Passage 102 to Flame Holder 100.
  • Pilot Diluent Fluid F8 may be controlled by Pilot Oxidant Valve 232 and delivered through peripheral Diluent Fluid Tube or Passage 103 to Flame Holder 100.
  • pilot Fuel Fluid Tube 101 Pilot Oxidant Fluid Tube 102, and/or Pilot Diluent Fluid Tube 103 may be used as electrical conductors to connect excitation or Ignition Voltage Source(s) 308 to the Ignition Authority 720, along with Ground 302.
  • Pilot Fluid Tubes 101, 102, and/or 103 may be positioned along the Transverse End Walls 734 (and/or 735) and/or Pilot Hot Fluid Feeder Passages 116.
  • the perpendicular (normal) separation distance 748 (along the Y axis) between opposing transversely elongated combustor near side (or liner) fuel feeder walls 736, and combustor far side oxidant feeder wall 737 may be configured together with the size of the fuel fluid orifices 81 and the respective fuel fluid pressure to generally provide a combusting fuel fluid jet (or “fuel jet”) mean penetration distance F71 of the diluted fuel fluid F2 delivered through the combusting chamber side or feeder wall orifices 81 into the inter side wall combusting chamber 740.
  • a combusting fuel fluid jet or “fuel jet” mean penetration distance F71 of the diluted fuel fluid F2 delivered through the combusting chamber side or feeder wall orifices 81 into the inter side wall combusting chamber 740.
  • the perpendicular (normal) separation distance between combustor side walls 746 (along the Y axis) between one or more opposing transversely elongated combustor near side (or liner) feeder walls 736, and combustor far side feeder walls 737 may be configured together with one or both of the size of the oxidant fluid orifices 82 and the respective fluid delivery pressure to generally provide combusting oxidant fluid jet (or “oxidant jet”) mean penetration distance F72 of the diluted oxidant fluid F5 delivered through the combusting chamber side wall orifices 82 into the inter side wall combusting chamber 740.
  • combusting oxidant fluid jet or “oxidant jet” mean penetration distance F72 of the diluted oxidant fluid F5 delivered through the combusting chamber side wall orifices 82 into the inter side wall combusting chamber 740.
  • the perpendicular (normal) Blend Trim perpendicular (normal) separation distance 748 (along the Y axis) between opposing transversely elongated combustor near side (or liner) feeder walls 736, and combustor far side feeder walls 737, may be configured together with one or both of the size of the Blend-Trim diluted oxidant fluid orifices 83, and the respective fluid delivery pressure of Blend-Trim diluted oxidant fluid F15, to generally provide a Blend-Trim Diluted oXidant fluid (or “oxidant jet”) mean penetration distance F73 of the Blend-Trim diluted oxidant fluid F15 delivered through the combusting chamber side wall orifices 83 into the inter side wall Blend-Trim region 850.
  • oxidant jet Blend-Trim Diluted oXidant fluid
  • diluent fluid F7 comprising liquid and/or gaseous diluent
  • reacting fluid F12 may similarly be delivered through orifices 78 into reacting fluid F12 to form diluted combusting (or reacting) fluid F13.
  • side wall separation distance, orifice diameter (or area), and fluid pressure may generally be configured to deliver fuel fluid jets of diluted fuel fluid F2, oxidant fluid jets of diluted oxidant fluid F5, and/or Blend-Trim diluted oxidant fluid fluid jets F15, with about 0.1 to 10 times the equivalent fluid penetration distance under similar conditions without an opposing impinging wall.
  • Such design of the jet penetration distance F72 and/or F71 may use configurations of one or more of the combustor side wall spacing 748, fuel orifice size 81, oxidant orifice size 82, Blend-Trim diluted oxidant fluid orifice size 83, and/or controlling the delivery pressure of fuel fluid F2, oxidant fluid F5 and/or Blend-Trim oxidant fluid F14.
  • This fluid penetration distance F71, oxidant fluid penetration distance F72 and/or Blend- trim diluted oxidant fluid penetration distance F73 may be configured for about 20% to 200% of the shallow combusting wall separation 748.
  • the fuel, oxidant, and trim oxidant fluid penetration distances F71, F72 and/or F73 may further be configured to between 40% to 100% of the shallow combusting wall separation distance 748.
  • the combusting chamber outer (far) side (liner) feeder wall 737 and the shallowly displaced inner (near) side feeder wall 736 adjacent to combusting chambers 740 may be joined or abutted together along their elongated transverse ends along the X axis perpendicular to the axial fluid flow Z axis. This joining may be achieved by forming near end walls 734 and/or far end walls 735 of a fluid delivery duct between adjacent combusting side feeder (or liner) walls 736 and 737.
  • These combusting chamber transverse near end walls 734 and transverse far end walls 735 may be generally convex (outwardly) curved facing downstream. These form one or more reacting or combusting zones between adjacent shallowly opposed near combusting chamber side feeder wall(s) 736 and far side feeder wall(s) 737.
  • the upstream combusting chamber 740 may generally increase in cross sectional area perpendicular to the axial combusting flow direction with increasing axial distance downstream towards the reactor or combustor outlet 136. This increasing combustor cross section may beneficially accommodate an increasing temperature and an increasing volume of the hot combustion gas formed.
  • the transversely elongated and opposed combusting section’s near side feeder wall 736 may comprise a generally increasing number of fuel fluid orifices 81 to deliver fluid comprising fuel fluid F1 into the reacting or combusting chamber 740 between the opposed combusting chamber near side wall 736 and combusting chamber far side wall 737.
  • the transversely elongated combusting chamber far side feeder wall 737 may comprise a generally increasing number of oxidant fluid orifices 82 to deliver fluid comprising oxidant fluid F4 into the reacting or combusting chamber between the opposed combustor side walls.
  • the corresponding configuration of shallowly displaced transversely elongated perforated combustor near and far side feeder walls 736 and 737, with transverse combustor end walls 734 and 735, may form an upstream to downstream expanding combusting chamber 740 having a generally downstream scalable expanding (hand “fan”) shape.
  • the combustor chamber near and far side feeder walls 736 and 737, and combustor chamber transversely bounding near end wall 734 and far end wall 735 may be formed from a high temperature material sufficient to withstand elevated combustion gas temperatures in the reacting or combusting chamber 740.
  • One or more of these combusting chamber near side feeder walls 736, and/or combusting chamber far side feeder walls 737, may be covered by a thermal barrier coating (TBC) or insulating layer 738.
  • TBC thermal barrier coating
  • Such TBC insulating layers 738 may be used to protect the structural material of combustor near and far side feeder walls 736 and 737 from the hot adjacent reacting fluid or energetic fluid and any corresponding radiation.
  • Such TBC insulating layers 738 may comprise chemical protecting materials such as to protect combustor side feeder walls 736 and 737 from elevated steam and/or oxygen with their corrosive or oxidizing characteristics.
  • At least one reactive fluid or fuel fluid F1 may typically be delivered through the fuel fluid duct 770 and through the perforated near side (or liner) feeder walls 736 into the reacting or combusting chamber (or zone) 740.
  • the reactive fluid or fuel fluid F1 may be a premixed fuel fluid comprising a fuel and one or both of oxidant and diluent therein forming a diluted reactive fluid or fuel fluid F2 (not shown).
  • Fuel fluid F2 may comprise a mixture of natural gas, air, and a diluent comprising one or more of water vapor, steam formed from heated water, and/or a water mist.
  • the diluted reactive fluid or diluted fuel F2 may similarly comprise chemical reactants with one or more other diluents such as carbon dioxide (CO2) and/or nitrogen (N2).
  • CO2 carbon dioxide
  • N2 nitrogen
  • the combustor far side (or “liner”) oxidant feeder wall 737, and combustor near side fuel feeder wall 736 may be configured between outermost enclosure walls of the combustor (not shown), similar to unperforated versions of oxidant side feeder wall 737 and fuel side feeder wall 736.
  • numerous fuel fluid ports 81 and oxidant fluid ports 82 supplied with pressurized fluid to form fluid jets may be configured to provide substantial penetration of 33% to 67% into the shallow combusting chamber depth under a substantial combustion power level.
  • the fuel and oxidant fluid jet orifices 81 and 82 and corresponding fluid delivery pressures may similarly be configured to provide major penetration of 40% to 100% of the distance across the shallow combusting chamber while achieving major portion of combustion power. This generally provides good mixing of the injected fluid(s) F2 and F5 with the transverse distribution of axially flowing combusting (or reacting) fluid F12 in the transversely extended shallow combusting chamber 740 between the combustor fuel side feeder wall 736 and oxidant side feeder walls 737.
  • the scalable configurations may be operated as a chemical reactor.
  • numerous jets may form an effective mixing system to mix reacting fluid with co-reacting fluid to form a product fluid or energetic fluid.
  • Such configurations may facilitate bringing injected reactive and co-reactive fluid rapidly up to a desired reacting temperature and to begin reacting.
  • thermal diluent may be delivered with one or both of the reacting fluid and/or co-reacting fluid to form first diluted reacting fluid F2 and second diluted co-reacting fluid F5 for delivery through ports 81 and/or ports 82 respectively.
  • a premixed humid fuel F2 and air- mist oxidant fluid F5 may be injected into axially flowing reacting or combusting fluid F22 or into hot or energetic fluid.
  • diluent fluid F7 may be delivered separately through diluent orifices 78 into reacting fluid F12.
  • multiple fuel orifices 81 and oxidant orifices 82 may be configured to provide an axial distribution of net orifice area sufficient to deliver the flow rate of reactive or fuel fluid F1 and co-reactive or oxidant fluid F4 with the desired axial flow rate distribution.
  • this may include an increasing number of orifices of similar size about the reaction zone transverse to the combustor flow axis.
  • Downstream Transition or Diffuser Region a downstream end transition or end diffuser 428 may be provided downstream of the combustion section 730, and the blend-trim equilibration region 426 where present. This may provide further fluid residence time which may beneficially increase the degree of reaction or combustion. Such an end diffuser 428 may reduce the pressure drop of delivering the energetic fluid F20 out from the downstream combustor outlet 136 of the scalable combustor 700.
  • Ignition System or Flame Authority [0232] With reference to Fig.
  • an ignition system or flame authority 720 may be provided near the upstream end wall 241 of the combusting chamber 740. This flame authority 720 may deliver hot igniting fluid F22 into an upstream reacting zone or pilot region or chamber 720 between one or more of the perforated opposed pilot chamber side walls 722. Pilot Igniter [0233] With further reference to Fig. 1B, an igniter 124 may be provided near the upstream end of the flame authority 720.
  • the igniter 124 may comprise one or more of a spark igniter, a pilot light, a hot gas jet, a plasma jet, a laser beam, a light pipe, a glow plug, a heated surface, a microwave heater, or other igniters such as may be used to ignite combustion or initiate chemical reactions.
  • Combustion may also be initiated by providing a starter fuel or reactant fluid flow F3 and second reactant or oxidant fluid flow F6, which together may comprise two or more hypergolic fluids that ignite on mutual contact.
  • Pilot Diluent Delivery [0235] With reference to Figure 1B, in some embodiments, further diluent F8 may be delivered through a pilot thermal diluent delivery system 373.
  • an outlet of the Pilot diluent delivery system 373 may be positioned downstream of a pilot reactant or fuel delivery system 372 outlet delivering pilot reactive fluid or fuel fluid F3 to an upstream Combustor Inlet (or pilot outlet) 134 to the combusting chamber 740.
  • Pilot diluent delivery system 373 may be located downstream of a co-reactant or oxidant pilot fluid F6 delivery through an Oxidant Pilot Delivery port 371. Such configurations may reduce the likely hood of quenching the pilot reaction or flame.
  • the energetic pilot fluid F22 formed by the pilot reaction may be cooled by using one or both of more pilot diluent fluid, and/or cooler pilot diluent fluid F8 through pilot fluid delivery port 373.
  • pilot fluid delivery port 373 For example, this enables conducting an upstream primary reaction at a hotter temperature and/or with less oxidant fluid F6 present. e.g., with fuel rich, (and oxygen or air lean) fluid mixture of Pilot Fuel/First Fluid F3 and Pilot oXidant/Second Fluid F6.
  • Such diluent delivery cooling the pilot may beneficially lower byproduct combustion emissions such as NOx. It may further enable operating the reaction or combustion at hotter temperatures.
  • one or more perforated direct contactor perforated wall sections such as depicted in Fig.1E, Fig.1G, and/or Fig.1F, may be used to deliver one or more diluent fluids comprising one or more of cold water, hot water, superheated water, saturated steam, superheated steam, air, carbon dioxide, nitrogen, an inert gas, or one or more reacted fluids.
  • VAST Patent Applications appended or incorporated by reference. i.e., the VAST.001 (Direct Contactor), VAST.002 (Trifluid), VAST.003 (Cycle), and/or the Campbell (VAST.014) patent.
  • VAST.001 Direct Contactor
  • VAST.002 Trifluid
  • VAST.003 Cycle
  • VAST.014 the Campbell
  • Fig. 1I, Fig. 1E, Fig.1G, (and correspondingly to Fig. 1F) orifices 81 and/or 82 in such perforated wall sections may be further configured to orient the diluent jets at an angle transverse to the fuel-rich combusting fluid flow such as F12 in the upstream combusting chamber 740 generally flowing axially along the Z axial direction.
  • orifices 83 may be oriented at an angle transverse to the Blend- Trim fuel rich (oxidant lean) fluid flow F12, and/or fuel lean (oxidant rich) fluid flow such as F13, that generally flows axially along the Z axial direction.
  • one or more fluid delivery ducts may be formed between the combustor side walls (or liners) to deliver one or more such fluids through the orifices in those side walls. This can help improve one or more of mixing, increase the residence time within the fluid, and increase the time for liquid diluent evaporation as needed.
  • Fig.1I depicts a transverse X-Y cross-section through the combusting chamber (or region) 740 perpendicular to the axial flow in the Z axial direction. This cross- sectional view is in the A-A’ plane noted in the elevation views Fig. 1C, Fig.1D, and Fig.1H.
  • the combusting chamber 740 is bounded along the shallow depth in the Y perpendicular direction by combusting chamber near side feeder wall 736 and combusting chamber far side feeder wall 737.
  • Combusting chamber 740 is further bounded by combusting chamber transverse oXidant-Diluent end wall 734 along the elongated transverse width in the positive X transverse direction.
  • Combusting chamber 740 is further bounded by combusting chamber transverse Fuel-Diluent end wall 735 in the negative X direction.
  • the combusting chamber near side feeder walls 736 and far side feeder walls 737 may be protected by a thermal barrier coating or insulation layer 738.
  • the combusting chamber end walls 735 and 734 may similarly be protected by a combusting end wall thermal barrier coating or (TBC) insulation layer 738 in the positive and negative X axial sides.
  • TBC thermal barrier coating or
  • One or more of fuel orifices 81, and/or oXidant orifices 82 may be slant oriented at a transverse angle to the transverse X direction.
  • Diluted Fuel /Reactant Fluid Delivery [0246] Reactant and/or Fuel fluid F1 may be delivered into fuel feeders 750, as depicted in the elevation view Fig.1D, in perspective view Fig.1A, and in the plan view Fig.1I. As shown in perspective view Fig.1E and plan view Fig.1I, fuel fluid orifices 81 may be angled transversely to the axial fluid flow F12 through combusting chamber side feeder wall 736 and thermal barrier coating (TBC) 738.
  • TBC thermal barrier coating
  • Co-reactant and/or Oxidant fluid F4 may be delivered into oXidant manifold 760, as depicted in elevation view Fig. 1H, in perspective view Fig. 1A, and in plan view Fig. 1I.
  • oxidant fluid orifices 82 may be angled transversely to the axial fluid flow F12 through combusting chamber far side oxidant feeder wall 737 and thermal barrier coating (TBC) 738.
  • the fuel fluid orifices 81 and oxidant fluid orifices 82 may be circumferentially oriented about the axial flow axis in the same clockwise (CW) orientation as shown in Fig. 1I. Similarly, they may be equivalently oriented counterclockwise (CCW) about the fluid flow axis (about the normal to the plane of Fig.1I). In further embodiments (not shown), the fuel fluid orifices 81 may be oriented clockwise (CW) and opposed to the opposite counterclockwise (CCW) orientation of oxidant fluid orifices 82 about the fluid flow axis (normal to the plane of Fig.1I).
  • the fuel fluid orifices 81 may be oriented counterclockwise (CCW) to oppose the clockwise (CW) orientation of the oxidant fluid orifices 82 about the fluid flow axis.
  • Blend Trim Region Downstream Oxidant and Diluent Delivery [0249] With reference to Fig. 1D, Fig. 1F, and Fig. 1H, in context of Fig. 1A, in some embodiments, further diluent and oxidant containing fluid F5 may be delivered into the energetic fluid into Blend-Trim region 850 downstream of the combusting chamber 740.
  • This oxidant fluid F5 may be delivered through diluted oxidant fluid duct 860 and/or diluted oxidant fluid duct 870 into the downstream Blend-Trim region 860.
  • diluted oxidant fluid ducts 860 and/or 870 may have perforated walls comprising multiple orifices 83, to deliver diluted oxidant fluid F5.
  • upstream fuel feeders 750 and oxidant feeders 760 may be similar to upstream fuel feeders 750 and oxidant feeders 760 in the upstream combustion section 730 adjacent to the upstream combustor side (or liner) walls. E.g., with suitable thermal barrier coating 738 to protect the walls as needed.
  • suitable thermal barrier coating 738 to protect the walls as needed.
  • downstream diluted oxidant duct 860 and/or diluted oxidant duct 870 may have a thermal barrier coating (TBC) 738 protecting the Blend-Trim duct wall 856 from high reaction or combustion temperatures.
  • TBC thermal barrier coating
  • a fluid duct with feeder walls 856 may be used, similar to the perforated direct contactor combustor side feeder walls 736, and/or 737.
  • the diluted oxidant fluid delivery orifices 83 may be configured at a Clockwise (CW) and/or CounterClockWise (CCW) angle to the reacting or combusting flow fluid flow axis, similar to the fuel fluid orifices 81 and/or oxidant fluid orifices 82, therein improving fluid mixing of injected diluted oxidant fluid F5 with incoming reacting fluid F12 and Blend-Trim fluid F13.
  • the number and size of diluted oxidant orifices 83 and relative delivery pressure of diluted oxidant fluid F5 may be configured to achieve effective jet penetration into the energetic fluid F12.
  • Blend-Trim diluted oxidant fluid F5 may be accomplished with a modest differential pressure compared to conventional combustors. Such downstream oxidant fluid may assist in reducing the oxygen concentration during most of the combustion and thus reducing the NOx emissions. Yet the downstream oxidant delivery may provide sufficient excess oxidant to enable efficient conversion of fuel, unburned hydrocarbons and carbon monoxide to carbon dioxide.
  • the downstream Blend-Trim combustor region 850 may be differentiated into an upstream Blend-Trim region 852 and downstream Blend-Trim region 854. Fig.
  • 2D depicts delivery of diluted oxidant F5 through diluted oxidant delivery perforated feeders 856 into upstream Blend-Trim region 852.
  • diluent fluid F7 may be delivered via downstream perforated Thermal Diluent Tube 106 through Diluent Orifices 78 into downstream Blend-Trim region 854.
  • Fig.2E depicts delivery of diluent fluid F44 through perforated Thermal Diluent Tubes 106 via diluent orifices 78 into the upstream Blend-Trim region 852.
  • Perforated Thermal Diluent Tubes 106 may similarly deliver diluent fluid F44 through diluent orifices 78 into downstream Blend-Trim Region Duct 858.
  • the upstream Blend-Trim Region Duct 858 may deliver Diluent Fluid F44 into downstream Blend-Trim Region Duct 858.
  • Such Diluent Fluid F44 together with Blend-Trim Oxidant Fluid F42 may thence be delivered via orifices 83 into downstream Blend-Trim Region 854.
  • Fig. 2E similarly depicts delivery of diluent fluid F46 through perforated Thermal Diluent Ducts or Tubes 107 via diluent orifices 78 into the upstream Blend- Trim region 852.
  • Perforated Thermal Diluent Tubes 107 may similarly deliver Diluent Fluid F46 through orifices 78 into downstream Blend-Trim Region Duct 857.
  • the upstream Blend-Trim Region Duct 857 may deliver Diluent Fluid F46 into downstream Blend-Trim Region Duct 857.
  • Diluent Fluid F46 together with Blend-Trim Oxidant Fluid F45 may thence be delivered through downstream Blend-Trim Region Duct 859, and thence via diluted oxidant orifices 83 into downstream Blend-Trim region 854.
  • the methods of fluid delivery into the Blend-Trim region depicted in Fig. 2D and Fig. 2E may be combined and adapted.
  • This scalable combustor invention is designed to achieve ultra-clean combustion for gas turbines, combined heat and power systems, industrial heating, cooling, and other applications requiring clean controlled combustion and/or chemical reaction.
  • multiple fluid jets may be configured with shallower spacing between walls to improve relative jet penetration.
  • the rate of diluted oxidant and fuel delivery to upstream combusting flow may be configured to increase operating range and operational robustness.
  • Rapidly Changing Gas Turbine Power Market [0260] Power demand is increasing from rising population, economic growth, and growing electric vehicle fleets. Rapidly growing solar and wind power requires correspondingly greater rapid backup power. Rapidly growing Artificial Intelligence (AI) use is increasing data center power usage, which requires ultra-high reliability.
  • AI Artificial Intelligence
  • the EIA (AEO 2022) projects global electrical power capacity to grow ⁇ 55%-108% by 2050. (i.e., much faster than power generation growth at 30% to 76%.) [0263] The EIA expects natural gas turbines to supply 15% to 20% of total global power. This indicates global power gas turbines will likely grow by 982 GW to 1,938 GW by 2050. This indicates a likely $1,100 billion to $2,150 billion global gas turbine growth market. This suggests potential global market share of $550 billion to $1,070 billion market for applicant’s ultra clean gas turbine power innovations as described herein.
  • CAISO power grid already has a ⁇ 24 GW “duck curve” demand power rise from no demand (excess mid-day solar and wind) to the evening peak demand after sunset under calm conditions.
  • Ensuring reliable power with increasing solar and wind power requires greater installed dispatchable backup power (or expensive storage) than the maximum demand, to ensure grid reliability at night with low wind. This is especially stringent considering power transmission limits during peak winter or summer loads.
  • Existing grids cannot now support interstate or national Real Zero renewable energy goals without CO2 emissions (herein “Real-Zero”, or “Net-Zero” without CO2 credits) power distribution demands. Such pressures form a strategic power system fragility.
  • Such techniques enable features and methods that are more scalable than conventional gas turbine combustors, across broader ranges of commercial combustor pressures, temperatures, power levels, and/or power ramping rates, therein improving power system capabilities and economics.
  • the techniques described herein further address designing scalable combustor methods and systems for gas turbine systems, with fuel, oxidant, and diluent types, combinations, and mechanical, electrical, and/or thermal loads, therein enabling more reliable grid operation and backup, and offering major intermittent non-dispatchable renewable power penetration and growth rates.
  • the techniques described herein further offer breakthrough ultra-clean methane combustion without catalysts. Some configurations were modeled using Reactive Computational Fluid Dynamics (herein “RCFD”) by the U.S.
  • RCFD Reactive Computational Fluid Dynamics
  • the results from modeling these techniques indicate a high probability that the present scalable combustor innovation will achieve best-in-class combustion in a VAST cycle gas turbine with ultra-clean emissions relative to other commercial power turbines.
  • the techniques in this invention offer ultra-clean best-in-class emissions on current fuels, sustainable fuels, and combinations of such fuels.
  • NH3 Power with Stringent NOx and NH3 “slip” Emission Rules may be applied to ultra-clean combustion of sustainable fuels such as hydrogen, ammonia, ethanol, and methanol. Such techniques may combust ammonia (NH3) with far lower NOx emissions than conventionally formed by burning NH3, methane, or hydrogen etc. E.g., much cleaner than burning NH3 in General Electric’s (GE’s) lean turbine combustors which form ultra-high NOx.
  • GE General Electric’s
  • These techniques may include reliably combusting hydrogen, which burns 33 times faster than ammonia, with much wider combustion boundaries, and with dangers of flash back and catastrophic explosion. [0298] Such techniques may similarly be used to crack NH3, and to combust cracked NH3. Cracking NH3 may include heat and/or catalysts, externally, or in situ within the combustor system. Combustion may include using combinations of NH3, and cracked ammonia (3H2 + N2). [0299] The techniques herein may be applied to achieve the US EPA’s (EPA Part 60 Subpart KKKK) requirement of 98% (60 times) lower gas turbine NOx emissions than conventional lean NH3 combustion.
  • Such techniques may further be used to develop dual fuel or multi-fuel use combustors, such as to use gaseous and/or liquid NH3, cracked NH3, hydrogen, and/or natural gas in various combinations.
  • Ultra-Clean Power Bidding Priority The techniques may be used to achieve ultra-clean emissions sufficient to avoid emission cleanup costs. Industry personnel estimate that such NOx emission cleanup can cost 7%-10% of total Capital Expenditure (herein “CapEx”). Applying such techniques to achieve ultra-clean emission ratings would likely eliminate such cleanup.
  • CapEx total Capital Expenditure
  • These techniques may further eliminate ongoing catalyst and NH3 cleanup operating costs.
  • the techniques may be used for quieter distributed scalable combustion and to avoid consequent high frequency fatigue. Such techniques may be used to reduce combustor turbine destroying noise by 30 dB or more. Using such independent temperature design and control techniques in scalable combustors may substantially reduce high temperature metal creep, cyclic thermal fatigue, maintenance, repair, downtime, and operating costs. [0311] The techniques for scalable combustors combined with “wet” cycle VAST power cycle turbines may offer cleaner, cheaper, faster, more efficient, and more durable intermediate power than both conventional Brayton “peaker” turbines and combined cycle turbines. The techniques may be used to increase combustor and turbine life, profitability, and revenue. [0312] The techniques include developing scalable dual-fuel ammonia and natural gas combustors.
  • NH3 gaseous and/or liquid ammonia
  • the techniques may enable flexible provision of more cost- effective practical intermediate gas turbine systems with conventional and/or sustainable fuels, including with higher efficiency and profitability than peaker turbines.
  • Such techniques may be used to design and construct ultra-clean combustion systems from 1,100oC to 1,500oC Combustor Outlet Temperatures, or Turbine Inlet Temperatures (TIT). Scalable combustor outlet temperatures may further extend to 700oC to 1,700oC, or from lower quenching temperatures, or up to combustion wall thermal limits.
  • TIT Turbine Inlet Temperatures
  • Such techniques may be used to design and construct combustors with specific power over industrial ranges from ⁇ 50% turndown to maximum power, such as from 30-60 MW/bar/m3 specific power.
  • Such techniques may similarly be used to extend such scalable combustion down to 10 MW/bar/m3 or lower, and up to 120 MW/bar/m3 or higher.
  • Such scalable techniques may be used to design and construct combustors with typical gas turbine combustion pressures ranging from 10 bar to 40 bar. These techniques may further be used to extend scalable combustion down to 1.1 bar or lower, and up to 100 bar or higher.
  • Such techniques may be used to cool walls of scalable combusting sections, including flowing liquid and/or oxidant, fuel, and/or diluent or combinations thereof, past or through scalable combustor walls. They may similarly provide cooling by flowing such fluids through multiple feeders about one or more walls of scalable combusting sections.
  • Such techniques may be used with scalable combustor walls for mean wall temperatures greater than or equal to about 1000oC, and up to or great than about 1500oC. Such techniques may similarly be used with scalable combustor wall temperatures down to about 500oC or lower, and/or up to 2500 oC or higher, with suitable materials and/or cooling. [0323] Such techniques may be used to preheat and/or crack a portion of ammonia by flowing it past scalable combustor walls. These may similarly be used to preheat and/or crack a portion of liquid and/or gaseous ammonia by flowing it through feeders distributed across such scalable combustor walls.
  • Scalable combustor techniques may be used for combustion with about 0.75-0.83 overall range of relative Fuel/Air Equivalence mass to stoichiometric mass ratio Phi ( ⁇ ) (or 1.33 to 1.20 Air/Fuel Equivalence mass to stoichiometric mass ratio Lambda), and independently control temperatures by the diluent (or water)/fuel mass ratio Omega ( ⁇ ).
  • Such scalability techniques may similarly be extended to Fuel/Air equivalence mass ratio Phi ( ⁇ ) to 0.67 or lower, and 0.97 or higher (or equivalently for Air/Fuel equivalence ratio Lambda up to 1.50 or higher, and down to 1.03 or lower.) with corresponding independent control of temperature by diluent/fuel ratio Omega.
  • Such scalable combustor techniques may be used to displace 50% to 100% stoichiometric air (or oxidant) delivered as cooling fluid, by using recycled diluent such as steam and/or hot water. Such techniques may further help displace between 10% and 170% of stoichiometric air.
  • Scalable combustor techniques may configure combusting and equilibration residence times from 100 ms to 700 ms. They may further extend combusting and equilibration residence time down to 30 ms and up to 3 seconds.
  • Scalable combustor techniques may correspondingly vary the combusting and/or equilibration system lengths relative to the specific fluid delivery rate of volumetric flow per combusting section outlet cross-sectional area. Adjusting such combustion system length may facilitate combustion of difficult fuels with slow flame speed such as ammonia.
  • Scalable combustor configuration techniques may configure the combusting system with lengths from 100 mm to 500 mm. They may extend down to 10 mm, or increase to 5 m in length. Blend-Trim regions may range from 20 mm to 100 mm. They may be varied from 5 mm to 5 m. Equilibrating system lengths may similarly extend from 0.2 m to 2m. Equilibrating system lengths may extend down to 0.04 m, and up to 10 m.
  • FIG.3A schematically shows a VAST Cycle Power System with a VAST Combustion System (herein “CMB”) receiving compressed oxidant fluid from an upstream Compressor (herein “CPR”) axially at CZ3 to feed a downstream gas turbine expander (herein “EXP”) axially at CZ4.
  • CMB VAST Combustion System
  • EXP gas turbine expander
  • This VAST Cycle Power System depicts a Compressor (CPR) with a Compressor Inlet CZ2 and a Compressor Outlet CZ3.
  • Compressed fluid flow may flow into a Diffuser (herein “DIF”).
  • DIF Diffuser
  • a portion of compressed oxidant (herein “WX31”) may flow into an upstream ignition system or Pilot 100 (herein “P”) at a Pilot or combustor inlet plane CZ31.
  • P pilot or combustor inlet plane CZ31.
  • WX34 Another portion of compressed oxidant fluid (herein “WX34”) may be delivered upstream into the combustor such as at plane CZ32.
  • Diluent fluid may be delivered upstream to CZ32, such as liquid water as a spray WDL32 into oxidant flow WX34.
  • a portion of diluent WDL32 may be delivered into an upstream typically fuel rich combusting region 730 from a combusting region inlet at CZ34 up to a Blend-Trim region inlet and combusting region outlet plane CZ35 (marked here as a combustor reference plane CBQ).
  • Fig.3A further schematically shows a “Blend-Trim” Region 850 extending from an upstream Blend-Trim inlet plane CZ35 (or combusting region outlet plane) through to a downstream Equilibrating Region inlet plane CZ39 (or Blend-Trim Region outlet plane).
  • an Equilibrating Region 900 may be provided downstream of the Blend-Trim region 850. This Equilibrating Region 900 may extend from the Blend-Trim region outlet at plane CZ39 to a Transition Zone Inlet plane CZ394 (or an Equilibrating Region outlet plane) to provide residence time to further complete the reaction or combustion.
  • Transition Region Per Fig.3A, a Transition Region or Zone 980 may follow the equilibrating region 900 to accelerate the hot flow to the combustor outlet.
  • the equilibration region at plane CZ394 may extend from the end of the equilibration region at plane CZ394 to a combustor outlet at CZ4 and into an expander (herein “EXP”) or Turbine Inlet, with an expander outlet at an outlet plane CZ5.
  • EXP expander
  • Turbine Inlet with an expander outlet at an outlet plane CZ5.
  • the equilibrating and transition regions may be aerodynamically configured to reduce flow pressure losses.
  • the Turbine Inlet mass flow (herein “W4”) flows into the Expander EXP at axial plane CZ4 from the Combustor outlet.
  • Cooling diluent liquid mass flow herein “WDL45” may be delivered into the expander to cool hot components such as blades, stators and/or walls.
  • Expanded fluid mass flow may flow from the expander EXP at axial plane CZ5 into a downstream heat exchanger, here depicted as a Once Through Steam Generator (herein “OTSG”).
  • OTSG Once Through Steam Generator
  • W51 cooled mass flow
  • HX downstream heat exchanger
  • a cooled heat exchanger outlet mass flow or exhaust flow (herein “W52”) (at an axial flow stage CZ52 downstream of the heat exchanger HX not shown) may be further cooled downstream as desired to further condense diluent vapor and/or to further cool diluent liquid and non-condensable flue gas, such as by using water- or air-cooled heat exchangers (not shown).
  • W52 cooled heat exchanger outlet mass flow or exhaust flow
  • vapor may be condensed, forming sub-atmospheric pressure with a recompressor compressing the cooled expanded excess oxidant and non-condensed combustion products back to atmospheric pressure discharge as detailed in prior patents (not shown).
  • Fig.3A further depicts upstream gas combusting temperatures being controlled by thermal diluent flows such as water and/or steam relative to fuel fluid delivery.
  • thermal diluent flows such as water and/or steam relative to fuel fluid delivery.
  • Such diluent fluids may be delivered into multiple upstream combusting regions.
  • C1 Combusting regions
  • Fig.3G Combusting regions
  • FIG.3I Combusting regions
  • C1- C8 implied, not labeled
  • Fig.3A shows further mass flow of oxidant fluid (herein “MX”) and mass flow of diluent fluid (herein “MD”) may be delivered into the Blend-Trim region.
  • MX oxidant fluid
  • MD diluent fluid
  • further oxidant such as air, and diluent such as water and/or steam may be delivered into one or more Blend regions (herein shown as a first Blend Region One “B1” and a second Blend Region Two “B2”), and into one or more Trim regions (herein shown as a First Upstream Trim Region “T1” and a Second Downstream Trim Region “T2”).
  • the cooled exhaust mass flow (W52) at Heat Exchanger (HX) outlet may be further cooling as needed.
  • Fig.3A shows further oxidant and diluent may be delivered into a Blend-Trim region.
  • further oxidant such as air
  • diluent such as water and/or steam
  • the one or more Blend regions e.g., B1 and B2
  • the one or more Trim regions e.g. Upstream T1 and downstream T2.
  • Fig.3A shows an inlet mass flow of oxidant (or air) (herein “WX2”) with an optional compressor inlet mass flow of liquid diluent (such as liquid water spray mass flow) (herein “WDL2”) into the inlet CZ2 of the compressor CPR, with an optional compressor cooling liquid spray mass flow (herein “WDL25”) into the compressor CPR itself.
  • WX2 oxidant
  • WDL25 liquid water spray mass flow
  • the compressor CPR may feed a mass flow of compressed oxidant fluid flow (or air) (with optional vaporized diluent) (herein “WX3”) into the upstream inlet of a VAST scalable combustor CMB at an upstream flow location CZ3.
  • the downstream combustor outlet at flow location CZ4 may flow into an expander EXP.
  • the scalable combustor CMB may include an upstream diffuser, DIF, that expands and slows the oxidant (or air) from the compressor outlet / diffuser inlet CZ3 to feed an upstream combusting section from CZ34 to CZ5 a VAST combustor (CMB) extending from a combustor pilot inlet plane CZ31 to the downstream outlet plane CZ4.
  • Fig.3A further depicts an upstream ignition authority or Pilot 100 (P).
  • Pilot P may be fed with a pilot fuel mass flow (herein “WF31”), a pilot oxidant mass flow (herein “WX31”), and optionally pilot diluent (herein “WDL31”) such as pilot liquid water.
  • Further fuel fluid (herein “WF32”), and further diluent fluid (herein “WDS32”) such as steam, may be mixed and delivered as a diluted fuel fluid mass flow (herein “MF”) into a diluted fuel manifold, to feed transverse fuel feeders into combusting regions (such as C1 to C7).
  • MF diluted fuel fluid mass flow
  • WX34 Further oxidant fluid
  • WDL32 upstream diluent fluid
  • WDL32 upstream diluent fluid
  • MD diluent fluid
  • Fig.3A depicts stoichiometric diluted oxidant and/or diluent mass flows being then fed into a Blend-Trim region 850 thru one or more transverse Blend region feeders (B1 and B2), with the remaining oxidant and/or diluent fluids delivered through one or more Trim region feeders, (upstream T1, and optional downstream T2 Trim regions etc., not shown) between combustor axial planes CZ35 and CZ39.
  • Fig.3A further shows mass flows of liquid diluent (herein “WDL42”) into a heat exchanger HX.
  • WDL42 liquid diluent
  • WDL41 Heated liquid from HX flows (herein “WDL41”) into the Once Through Steam Generator (herein “OTSG”), and upstream into the upstream combustor (herein “WDL32”), into the Blend-Trim region (herein “WDL35”), and into the downstream combustor walls in the equilibrating region and transition region, (herein “WDL398”).
  • Fig.3A shows a portion of heated liquid diluent WDL41 further recovering heat in the OTSG to form steam (herein “WDS4”).
  • This vaporized diluent may be delivered back into the Blend Trim region as WDS35, and into the upstream region as WDS32 such as into the upstream fuel mass flow MF at CZ32.
  • an upstream premix region may be provided between the compressor outlet / diffuser inlet CZ3 and the combusting region outlet at CZ35. This may deliver liquid diluent WDL32 into the oxidant mass flow MX feeding one or more combusting regions C1 through C7.
  • This premix region may similarly be located between an upstream combustor inlet plane CZ31 near the inlet 100 pilot P and the combusting region inlet near CZ34.
  • the premix region may comprise perforated direct contact tubes 14 connected to a liquid diluent supply flow WDL31 to deliver diluent spray into the upstream oxidant fluid WX34.
  • Valves may be configured to control delivery of one or more flows of fuel and/or diluent into one or more of the diffuser DIF, the pilot P, combusting region 730, and Blend-Trim region 850, etc.
  • Valve VDL42 may control the return flow of diluent liquid through the heat exchanger HX.
  • Valve VDL35 may control flow of heated liquid diluent WDL35 into the Blend-Trim region 850.
  • Valve VDL32 may control liquid diluent WDL32 to the combusting region manifold 730.
  • VF32 may control fuel fluid flow WF32 into the combusting system.
  • Valve VF31 may control fuel fluid flow WF31 to the pilot P.
  • some scalable combustor embodiments may comprise a streamwise flow axis with transversely extended combusting sections 732 relative to shallowly separated opposed combustor walls 736.
  • Such transversely extended walls 736 of extended combusting sections 732 may be bounded with side walls 734.
  • the relative circumferential transverse wall elongation may be greater than 1.15 times the shallow spacing by radial depth of side walls 734.
  • FIG.3B a portion of the Scalable Combustor, CMB is depicted extending from a flame authority 100 or pilot P at axial flow location CZ31 about the outlet of the upstream diffuser DIF through a combusting section 730 and a downstream Blend-Trim region 850 opening into the downstream equilibrating region 900.
  • Fig.3B shows an embodiment of a Cylindrical-Axial (circumferentially-radially stacked) combustor 702 shown in cylindrical coordinates with a Radial axis (“R”) perpendicular to an Axial flow axis (Z) with a circumferential direction Theta ( ⁇ ).
  • R Radial axis
  • scalable combustors may use a curvilinear flow axis with non- cylindrical walls.
  • Such embodiments may include multiple scalable (“fan”) combusting shells (or burners) configured generally about Radial - Circumferential Theta (R - ⁇ ) cylindrical surfaces. These cylindrical combusting shells may be stacked radially, and generally perpendicularly, to the primary streamwise flow axis of oxidant fluid F5 through the scalable combustor, oriented along the axial (Z) flow direction, from an upstream fluid inlet 134 to a fluid flow outlet 136 for heated pressurized hot combusted fluid F20.
  • fan combusting shells
  • R - ⁇ Radial - Circumferential Theta
  • such scalable circumferential combustor embodiments 702 may be configured within an outer Pressure Vessel Wall 172.
  • a pilot fuel fluid flow F3, and a pilot oxidant fluid flow F6, may be delivered to an upstream Igniter, flame authority or Pilot 100, configured to combust these fluids and to form a hot pilot fluid flow F22.
  • Pilot diluent fluid F8 flow may be separately delivered to the Pilot 100, and/or mixed in with pilot fuel fluid F3, and/or pilot oxidant fluid F6 flowing into the Pilot 100 in an upstream pilot region 720.
  • pilot fluid flow F22 from Pilot 100 may be distributed in upstream pilot region 720 to an upstream end of a pilot fluid distribution system 722 comprising one or more scalable pilot fluid delivery ducts (or “fan” burner ducts) 728.
  • pilot fluid delivery ducts (or “fan” burners) 728 may be configured circumferentially around the cylindrically stacked scalable combustor 702.
  • Pilot fluid delivery ducts 728 may deliver hot pilot fluid into one or more combusting systems (or mid-fan burners) 732 in an axially intermediate combusting region 730.
  • each combusting system 732 generally comprises two radially opposing circumferential combusting radially outward side walls 736 (with corresponding radially inward side walls). These combusting radially outward side walls 736 may be bounded and connected by corresponding combusting (mid-fan) (circumferentially) end walls 734. In other configurations, radial side walls 736 may be curved around to radially meet and transversely or circumferentially bound the combusting region. [0022] Each combusting system radial side wall 736 may comprise numerous fluid delivery orifices 80 such as schematically depicted in Fig.3C.
  • Pressurized oxidant fluid F5 may be delivered into the Cylindrical-Axial combusting system 702 and delivered into combusting system 732 through orifices 80 configured in combusting system radial side walls 736.
  • diluted fuel fluid F2 may be delivered through a similar axial Fuel Manifold 770 between circumferentially adjacent combusting regions on alternating sides of the combusting regions from the oxidant fluid F5 delivery.
  • premixed reactive fuel-oxidant mixture with optional diluent may be delivered into the cylindrical-axial combustor 702, and delivered through perforated combustor radial side walls 736 in combusting systems 732 within the combusting region 730.
  • energetic fluid from one or more combusting systems 732 in combusting region 730 may be delivered to circumferential downstream Blend-Trim region 850 comprising Blend-Trim oxidant-diluent delivery and reacting region manifold walls 857 feeding related Blend-Trim reacting regions.
  • Each Blend-Trim reacting region 850 may comprise opposing circumferential Blend-Trim perforated side walls 857 to bound combustion within that region.
  • Blend-Trim region side walls 857 may generally be connected by one or more far-fan end walls 746.
  • the Blend-Trim side walls 857 may also be configured to join at their circumferentially transverse ends.
  • Multiple sets of circumferential combustors 732 and Blend-Trim Regions 850 may be configured within combustor outer wall or pressure vessel 172.
  • Fig.3C depicts an expanded view of a combustor wall section radial side wall 736 showing orifices 80 through a combustor fluid duct wall 132 protected by a thermal insulating barrier 150.
  • Fig.3D depicts a sample radial circumferential (R Theta) cross section of a portion of a comBusting region extending circumferentially by a Combusting section angle THC.
  • This example shows an oXidant Manifold on the CCW side feeding oxidant fluid F5 with the THBMX CW portion shown as feeding two CW adjacent combusting regions.
  • Fig.3D depicts a fuel manifold encompassing a THBMF CW portion correspondingly feeding the two radially adjacent combusting regions including a combusting feeder radial depth (Thickness) CR15T.
  • Fig.3D further depicts an outer oxidant fluid feeder extending radially with a radial depth (Thickness) CR12T inside of an outer circumferential wall having an inner radius CR12. That outer oxidant fluid feeder extends circumferentially over an included angle THBFX4 and feeds oxidant fluid through multiple orifices into a combusting region extending radially with a radial depth (or Thickness) CR15T from outer wall inner radius CR15 to inner wall outer radius CR16.
  • Thickness radial depth
  • Oxidant fluid F5 optionally with diluent may flow along the oXidant fluid feeder and through oXidant orifices with a typical diameter DXO into a radially adjacent outer combusting region extending radially with a depth (or Thickness) CR15T between combusting chamber outer radius CR15 and combusting chamber inner radius CR16.
  • oxidant orifices may be offset from the CCW manifold by a circumferential angle THBXO, and spaced apart by a circumferential angle THBXS, with an Jth orifice in an Ith oxidant feeder positioned at a circumferential angle THBXIJ.
  • Fig.3D further depicts Fuel fluid flow F2 optionally diluted with diluent fluid, flowing though a CW comBusting region manifold extending through circumferential Theta angle THBMF.
  • This CW fuel fluid manifold delivers fuel fluid through a fuel complementary feeder extending radially with a depth (Thickness) CR18T, and feeding fuel fluid through fuel fluid orifices with typical fuel orifice diameter DFO into the outer combusting region between CR15 and CR16 extending radially with a depth (Thickness) CR15T and circumferentially about an angle THBFF4.
  • This fuel feeder with a depth CR18T may similarly feed fluid into an inwards combusting region extending radially between CR25 and CR26, and circumferentially across THBFF4.
  • oxidant fluid F5 may similarly be delivered radially (and longitudinally) through the CCW manifold angle THBQX into a CCW combusting region.
  • diluent fluid F7 may be delivered through a CW diluent manifold extending circumferentially by THMDS for each of the central and CW combusting regions and axially along the combusting region.
  • Fig.3E depicts an axial circumferential (Z Theta) “unrolled” plan view of two adjacent symmetric combusting and Blend-Trim regions with circumferentially CCW bounding end walls 734 and CW bounding end walls 735.
  • Such combusting regions may extend axially from an upstream Pilot 100 outlet or combusting inlet CZ34 to downstream axial boundary CZ35.
  • the downstream Blend Trim region may extend from CZ35 to CZ39.
  • adjacent symmetric combusting regions are shown here as having adjacent CCW oxidant fluid manifold regions ducting oxidant fluid F5 per combusting region. They may have adjacent CW fuel manifold regions ducting diluted fuel fluid F2.
  • Such CCW oxidant manifolds and adjacent CW fuel manifolds may be commonly bounded and divided by a sigmoidally curved longitudinal (radial) manifold divider 250 between upstream CZ34 and combusting downstream CZ35 bounds, and thence to the Blend-Trim region axially between planes CZ35 and the downstream CZ39.
  • Fig.3E further depicts an upstream circumferentially increasing width region 731 with axial flow distance, downstream of the Pilot 100, having an increasing width with an outward wall curvature along the axial direction. This may beneficially accommodate an axially increasing volumetric flow from increasing mass flow and from rising temperature with combustion, thereby reducing fluid acceleration and pressure drop losses.
  • Fig.3A and 3E similarly depict a configuration with a downstream circumferentially decreasing combusting region 733 with a circumferentially axially declining width wall curvature. This may beneficially provide an aerodynamically smoother junction with an equilibrating region extending downstream from planes CZ39 to CZ394.
  • Fig.3E further depicts an axially intermediate combusting transition region 732. This combusting intermediate transition region 732 may change with axial distance, from an axially increasing width wall curvature like in combusting upstream section 731, to an axially decreasing width wall curvature like combusting downstream section 733.
  • Fig.3E depicts distributions of fuel fluid delivery orifices 81, and distributions of oxidant fluid delivery orifices 82 opening into the combusting region from CZ34 to CZ35. Further distributions of oxidant and/or diluent delivery orifices 83 may be configured to open downstream in the Blend-Trim region from planes CZ35 to CZ39.
  • a downstream Blend-Trim manifold region may be provided to deliver oxidant fluid (F4 not shown) or diluted oxidant fluid F5 axially between axial planes CZ35 and CZ39, and bounded by circumferential manifold CCW wall 250 and manifold CW wall 734, with an axially upstream bounding wall 249 between the upstream delivery of diluted fuel flow F2 (or fuel fluid flow F1 not shown) and the downstream delivery of Blend-Trim diluted oxidant fluid F5.
  • Fig.3G depicts a corresponding outward (or inward) axial circumferential (Z Theta) “unrolled” plan view of a symmetric combustor fluid feeder region. This extends axially in the flow direction from an upstream Pilot 100, with a CCW axial diluted oxidant fluid manifold region 244 ducting upstream diluted oxidant fluid F4 to upstream oxidant feeders.
  • the fluid feeder region of Fig.3G may include a second CCW axial oxidant manifold 245 ducting diluted oxidant fluid F5 further downstream.
  • the Fig.3G configuration similarly depicts a CW inward upstream first fuel manifold region 242 ducting first fuel fluid F1 comprising a fuel to upstream feeders. This may be divided by Upstream/Downstream Fuel Fluid Manifold Dividing wall 252 from a second intermediate CW outward fuel fluid manifold region 243, such as ducting a Diluted Fuel Fluid flow F2 (or another flow of Fuel Fluid) further downstream.
  • an upstream to Downstream Fuel Feeder to Blend- Trim Dividing Wall 253 may divide and separate upstream diluted fuel fluid F2, flowing through the intermediate fuel fluid manifold region 243 between CZ34 and CZ35, from Blend-Trim diluent flow F7 flowing downstream to the Blend-Trim region 850 between planes CZ35 and CZ39.
  • Manifold bounding wall 253 may adjoin the downstream diluted oxidant or diluent fluid feeder extending down to plane CZ39.
  • the CCW oxidant fluid manifolds and CW fuel fluid manifolds may be separated by a sigmoidally curved longitudinal radial manifold divider 250 that colds the downstream transverse Trim feeder ending axially at plane CZ39.
  • Downstream Combusting-oxidant fluid manifold divider 248 may be similarly curved and configured parallel to the manifold divider 250 and aerodynamically curved as it connects with the upstream of the transverse Blend-Trim feeder opening at CZ35.
  • An axial-radial manifold divider 253 bounding between diluted fuel fluid flow F2 and diluent fluid flow F7 may be curved or sigmoidal from upstream CZ34 to downstream at CZ35 where it adjoins oxidant feeder delivering oxidant fluid X7 (or optionally diluted oxidant fluid).
  • axial radial mid Upstream Combusting oXidant Manifold Dividing wall 247 may divide Diluted Rich oXidant Upstream Fluid Manifold 244 from second Diluted Rich oXidant Downstream Fluid Manifold 245.
  • downstream axial radial oXidant-Blend-Trim manifold wall 248 may divide midstream second oxidant fluid manifold 245 from diluted oxidant Blend-Trim manifold 246.
  • a first fuel fluid F1 (optionally diluted) may be delivered into fuel fluid manifold 242 bounded by Fuel Feeder Upstream/Downstream Manifold Dividing Wall 252, and be delivered as multiple fuel fluids, such as U1, U2, and U3, flowing through respective multiple transverse fluid fuel fluid feeders.
  • These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that range.
  • a second diluted fuel fluid F2 (or a second fuel fluid flow not shown) may be delivered into downstream fuel fluid manifold 243 and be delivered as multiple fuel fluid flows U4, U5, U6 and U7 flowing into multiple transverse fluid fuel fluid feeders and thence into the adjacent combusting region via fuel fluid orifices 81A.
  • These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that axial range.
  • oxidant fluid F4 may be delivered via Diluted Oxidant Fluid Upstream Manifold 244 as oxidant fluid flows X1, X2, and X3 through multiple transverse oxidant fluid feeders and thence through oxidant fluid orifices 82A. Such oxidant fluid F4 delivery may interleave with delivery of first fuel fluid F1, such as through U1 to U3, through respective upstream transverse fuel fluid feeders.
  • oxidant fluid F5 may be delivered via Diluted oXidant Fluid Downstream Manifold 245 as oxidant fluid flows such as X4, X5, X6, and X7 (or optionally diluted oxidant fluid) through multiple respective transverse oxidant fluid feeders, and thence into the adjacent combusting region via multiple oxidant fluid orifices 82B.
  • Such oxidant fluid delivery through oxidant feeders may interleave fuel fluid delivery flows, such as U4 to U7, through respective transverse fuel fluid feeders in the upstream combusting region from CZ34 to CZ35
  • diluted oxidant fluid F6 may be delivered via CCW Diluted Oxidant Blend-Trim Manifold 246 to downstream Blend-Trim feeders.
  • Blend fluids such as B1 and B2
  • Upstream Blend-Trim orifices 83A, and Midstream Blend-Trim Orifices 83B into the radially adjacent Blend-Trim region downstream of the combusting region.
  • a portion of diluted oxidant fluid F6 may be delivered as one or more Trim fluid flows, such as T1, through a transverse trim feeder and thence through Downstream Blend-Trim orifices 83C into the radially adjacent Blend-Trim region between planes CZ35 and CZ39, axially downstream of the combusting region.
  • Trim fluid flows such as T1
  • Blend-Trim diluent fluid F7 may be delivered via CW Diluent-Trim manifold 238 downstream into Diluent-Trim region 850 between CZ35 and CZ39.
  • Blend-Trim diluent fluid F7 may be delivered as one or more diluent fluids D1, D2, and D3 through transverse diluent feeders and thence through diluent fluid orifices 86A, 86B, and 86C, into the radially adjacent downstream Blend-Trim region of the combustor.
  • walls 253 and 250 of CW diluent trim manifold 238 to the Blend-Trim feeder region may be outwardly curved in an axially upstream section 731. They may similarly be inwardly curved in axially downstream section 733.
  • the intermediate combusting region 732 may be sigmoidally curved section to aerodynamically connect upstream section 731 and downstream section 733. (In other configurations intermediate combusting region 732 may be linearly configured.) Downstream section 850 of bounding wall 250 may transition from inwardly curved section 733 to connect aerodynamically with the downstream equilibrating region axial slope.
  • Asymmetric Combusting Systems [0056] Per Fig.3H, and Fig.3I, some combustor configurations may use an asymmetric combustor about a longitudinal oxidant manifold feeding transverse circumferential oxidant fluid feeders on the CCW and CW sides of the oxidant manifold.
  • FIG.3H depicts a circumferentially (Z Theta) “unrolled” plan view of two adjacent asymmetric combusting regions with an axial fluid flow axis Z, and circumferential axis Theta perpendicular to a radial axis R. This may have combustor walls radially adjacent to the combusting region, with fuel fluid orifices 81, oxidant fluid orifices 82, and/or Blend-Trim region diluent fluid delivery orifices such as 83.
  • such asymmetric combusting region configurations may have circumferentially adjacent oxidant fluid manifold bounding Combustion Chamber Transverse CCW side End Wall 734 directing oxidant fluid F5 between upstream combusting region inlet CZ34 and combusting fluid downstream end CZ35. They may similarly have circumferentially adjacent bounding fuel fluid Combustion Chaber Transverse CW side End Wall 735 delivering fuel fluid F2 between CZ34 and combusting region Downstream Manifold End Dividing Wall 249.
  • diluted oxidant fluid F7 may be delivered into the downstream Blend-Trim manifold region 850 bounded by side bounding manifold walls 735 and axially bounding Downstream Manifold End Dividing Wall 249, extending axially from planes CZ35 to CZ39.
  • Some asymmetric combusting region configurations may include a common upstream Pilot 100 feeding adjacent combusting shells. This Pilot 100 may be fed by Pilot Fuel Fluid F3, Pilot Oxidant Fluid F6, and Pilot Diluent Fluid F8.
  • the asymmetric combustor configuration of Fig.3H may have a sigmoidally curved oxidant fluid boundary such as described in Fig.3H and adapted to such an asymmetric configuration. This may have a circumferentially (Theta) outwardly curving upstream manifold-combusting region bounding wall section 731 with axially increasing distance Z.
  • the asymmetric combustor may have a correspondingly circumferentially (Theta) inwardly curving downstream manifold with bounding Combustion Chamber Downstream Transverse End Wall section 733 with axially increasing distance Z.
  • the asymmetric combustor configuration of Fig.3H may have a connecting intermediate Combusting Chamber Midstream Transverse End Wall 732 transitioning from the outward to the inward circumferential-axial curvature.
  • the oxidant fluid manifold of Fig.3H may further have a downstream Blend- Trim region 850 with a Blend-Trim diluent/oxidant fluid manifold wall 734 that may have an aerodynamically varying curvature between the axially upstream adjacent combusting region downstream transverse end wall 733 and the downstream equilibrating region wall beginning at CZ39 and extending into equilibrating region 900 per Fig.3A.
  • Fig.3I depicts an example of a circumferentially “unrolled” circumferentially- axially (Z Theta) asymmetric combustor fluid feeder configuration.
  • first fuel fluid flow F1 may be delivered into an upstream transverse fuel fluid feeder as fuel fluid U1 and thence into the combusting region through one or more fuel fluid orifices 81A.
  • further portions of first fuel fluid F1 may be delivered into progressively downstream transverse fuel fluid feeders as to feed fuel fluids U2 and U3. These may be delivered from the transverse fuel fluid feeders through similar or increasing number of fuel fluid orifices 81A into the radially adjacent combusting region.
  • Fig.3I similarly depicts an oxidant fluid manifold axially feeding oxidant fluid F4 flows X1, X2 and X3 progressively axially into respective transverse oxidant fluid feeders and thence into oxidant fluid orifices 82A into the radially adjacent combusting chamber.
  • the size, (or area) and number of the respective fuel fluid orifices 81 and oxidant fluid orifices 82 may be configured to provide a desired range of relative fuel to oxidant composition relative to stoichiometric composition (PHI) (Or equivalently, the relative oxidant to fuel ratio LAMBDA).
  • PHI stoichiometric composition
  • first fuel fluid F1 and/or oxidant fluid F4 may comprise gaseous and/or liquid diluent, such as steam, water vapor, and/or liquid water as delivered through transverse feeders and orifices into the combusting chamber.
  • diluted fuel fluid F2 may be axially delivered through a fuel fluid manifold and thence into one or more transverse fuel fluid feeders as fuel fluid flows U4, U5, U6 and/or U7.
  • oxidant fluid flow F5 may be delivered through the outer axial oxidant fluid manifold and then as one or more oxidant fluid feeder flows, such as X4, X5, X6, into respective transverse oxidant fluid feeders and thence through oxidant fluid orifices 82B into the radially adjacent combusting region.
  • diluent fluid F14 such as liquid water
  • diluent fluid flows D1 and D2 may be delivered to downstream Blend-Trim region through one or more transverse feeders such as diluent fluid flows D1 and D2, and thence through orifices 86A into radially adjacent Blend-Trim region 850 in the combustor axially between planes CZ35 and CZ39.
  • further oxidant fluid optionally with diluent fluid may be delivered through transverse Blend-Trim feeders as Blend-Trim fluids B1 and/or T1 and thence through Blend-Trim orifices 83A and 83C into the downstream Blend-Trim region 850 of the combusting chamber axially between planes CZ35 and CZ39.
  • Cooling Upstream Combustion [0075]
  • the embodiments depicted herein enable further flexibility in configuring diluent delivery separately from oxidant and fluid delivery. This may be beneficially used to reduce combusting temperatures independently of relative fuel to oxidant composition (Phi) (or relative oxidant to fuel composition Lambda).
  • some to all of the gaseous and/or liquid diluent fluid D1 and D2 may be delivered with one or more fuel fluid flows U5 to U7.
  • some to all of such gaseous and/or liquid diluent fluid D1 and D2 may be delivered with oxidant fluids X4, X5, and/or X6.
  • Such increases in diluent fluid with the combusting fuel and oxidant fluid flows may be used to reduce the combusting temperatures and thence reduce emission formation such as NOx.
  • this may be delivered with rich to stoichiometric portion of oxidant delivery to form associated rich to stoichiometric combusting regions.
  • one or more of axially upstream to downstream manifold walls may be fairly aligned axially between the upstream combusting region at CZ34, and the downstream connection with related transverse fluid delivery feeders. Such alignment may beneficially reduce the rate of change in axial fluid flow cross sectional area (expansion) and delivery flow rate, and thereby reduce related fluid pressure drops.
  • Fig.3J depicts a schematic circumferentially (Z Theta) “unrolled” combusting section of a radially inward (or outward) wall configuration, depicting larger and more numerous upstream oxidant fluid delivery orifices 82 and downstream smaller and fewer fuel fluid delivery orifices 81. E.g., in a 2:1 ratio. Oxidant fluid orifices may be circumferentially offset from fuel fluid orifices to improve mixing and reduce quenching.
  • Fig.3K depicts a schematic circumferentially (Z Theta) “unrolled” combusting section radially inward (or outward) wall configuration with fewer upstream fuel fluid delivery orifices 81, and more numerous downstream oxidant fluid delivery orifices 82. E.g., in a 1:2 ratio. Fuel fluid orifices may be circumferentially offset from oxidant fluid orifices to improve mixing and reduce quenching probabilities.
  • Fig.3L depicts a schematic circumferentially (Z Theta) “unrolled” configuration a downstream Blend-Trim region section having oxidant fluid orifices 83A and 83C in a radially outward (or inward) Blend-Trim region wall.
  • Upstream Blend-Trim orifices 83A may be offset ClockWise (CW) from downstream Blend-Trim region orifices 83C.
  • Fig.3M depicts a sample schematic configuration of a downstream Blend-Trim region section having oxidant fluid delivery orifices 83A and 83C in a radially inward (or outward) Blend-Trim region wall.
  • Blend-Trim orifices 83A may be offset CounterClockWise (CCW) from ClockWise (CW) downstream Blend-Trim orifices 83C.
  • CCW CounterClockWise
  • Blend-Trim orifices 83A and 83C configured radially outward of a combusting region may be offset ClockWise (CW) and CounterClockWise (CCW) from Blend-Trim orifices 83A and 83C configured radially inward of the combusting shell.
  • Fig.3N depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut through a CounterClockWise (CCW) circumferentially outward combusting region wall 734.
  • CCW CounterClockWise
  • This sample configuration Fig.3N shows eight radially outward oxidant fluid delivery openings X1 through X8 for radially outward oxidant fluid feeders (or diluted oxidant fluid feeders).
  • FIG.3O depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut inward of the CCW circumferentially outward end wall (734) having eight radially outward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in outward transverse oxidant feeders.
  • Fig.3O further shows these outwardly oxidant fluid openings (X1-X8) may be complemented with eight interspersed radially inward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in inward transverse oxidant feeders.
  • These oxidant fluid passages (X1-X8 and X1-X8) may be interspersed with narrower fuel fluid delivery passages (unmarked).
  • Fig.3Q depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region through a Clockwise (CW) circumferentially outward side bounding combusting region end wall 735 having eight radially outward fuel fluid delivery openings U1 through U8. These may be complemented by and interspersed with eight radially inward fuel fluid passage openings U1 through U8.
  • FIG.3P depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region inward of the CW circumferentially outward end wall (735) having eight oxidant fluid feeder delivery passage openings (U1 through U8) interspersed with eight oxidant fluid feeder delivery passage openings (e.g., X1-X8 not labeled).
  • Figures 3N through 3Q further depict combustor radial height (or length) parameters labeled from the first outward combusting shell towards the next inward combusting shell.
  • CR12 labels the radially outward oxidant fluid feeder wall outer radius.
  • Figures 3N through 3Q further depict combustor radial inner height parameters labeled from the first outward combusting shell towards the next inward combusting shell along the radial R axis.
  • CR12T labels the radially inner depth (height or Thickness) of the outer oxidant fluid transverse feeders shown in Fig.3N and Fig.3O.
  • CR12T similarly labels the radially inner height of the outer fuel fluid transverse feeders shown in Fig.3P and Fig.3Q.
  • the radial parameter CR15T labels the combusting region radially inner height (Thickness) between CR15 and CR16 shown in Fig.3O and Fig.3P.
  • CR18T similarly labels the radial thickness of the radially inner oxidant and fuel transverse feeders between CR16 and CR24 shown in Fig.3N through Fig.3Q.
  • Figures 3N though 3Q further depict the combustor axial boundaries from the upstream combusting region boundary at CZ34 to the downstream combusting fluid delivery boundary at CZ35 (at a reference plane CBQ) along the axial flow Z axis.
  • Fig.3O further depicts typical Axially Inner Inlet Widths 810 of radially outer transverse oXidant fluid feeders X1 to X8 supplying the central combusting region near the outer open side (e.g., CounterClockWise CCW side near the oxidant fluid feeder opening from the adjacent oxidant manifold).
  • axially inner axial widths of radially inner transverse oxidant fluid feeders X1 to X8 supplying oxidant fluid into the central combusting region in Fig.3O may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis.
  • Fig.3O further depicts the corresponding Axially Inner Far End Widths 809 of radially outer transverse Fuel Fluid feeders U1 to U8 near the transversely closed end of the fuel fluid feeders near the adjacent oxidant fluid manifold (e.g., the CCW side).
  • Fig.3P further depicts typical Axially Inner Inlet Widths 808 of radially outer transverse Fuel Fluid feeders U1 to U8 supplying the central combusting region near the outer open side (e.g., the Clockwise CW side near the fuel fluid feeder opening from the adjacent fluid manifold).
  • the inner axial widths of radially inner transverse fuel fluid feeders U1 to U8 supplying fuel fluid into the central combusting region in Fig.3P may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis.
  • Fig.3P further depicts the corresponding axially inner widths 811 of outer transverse oxidant fluid feeders (X1-X8 not labeled) near the transversely closed end of the oxidant fluid feeders near the adjacent fuel fluid manifold (e.g., the CW side).
  • Fig.3P similarly shows the inner transverse oxidant fluid feeders (X1-X8 not labeled) between CR16 and CR24, with corresponding inner widths (811 not labeled) between fluid feeder walls.
  • Fig.3R schematically depicts an axial circumferential (Z Theta) plan view perspective of a pair of transverse fluid feeders delivering oxidant fluid X into multiple oxidant fluid orifices 82 with typical oxidant fluid orifice diameters DXO, and delivering fluid F into multiple fuel fluid orifices 81 with typical fuel fluid orifice diameters DFO.
  • the fuel fluid feeder is depicted with an axial width DFF compared to the wider Oxidant Fluid Feeder with an axial width DFX.
  • diluent feeders may be utilized with a Diluent Fluid Feeder width DFD (not shown).
  • fuel fluid orifices 81 in the fuel fluid feeder may be circumferentially displaced by a circumferential angle THF from the vertical plane, ClockWise (CW) positive.
  • oxidant fluid orifices 82 may be configured in pairs circumferentially positioned about fuel fluid orifices 81, with a narrower circumferential separation angle THXN between oxidant fluid between nearest centers of oxidant fluid orifices 82 of separated orifice pairs.
  • Oxidant fluid orifices 82 may have a wider adjacent orifice circumferential separation angle THXW between oxidant orifice centers of wider separated orifice pairs.
  • oxidant orifices may be spaced further apart, or may be spaced uniformly apart.
  • circumferential spacing of orifices about the combustor may be further varied along axially differing fluid feeders. These may use one or both of circumferentially even spacing, and circumferentially asymmetric spacing.
  • circumferential spacing may be closer near one and/or both inner and outer combusting chamber boundaries than in circumferentially inner regions. Other configurations may provide more space between orifices near circumferential boundaries.
  • Fig.3S shows another axial circumferential plan view of a fuel feeder feeding fuel fluid F through fuel fluid orifices 81 and an axially adjacent oxidant fluid feeder feeding oxidant fluid X through a multiplicity of oxidant fluid orifices 82.
  • This configuration depicts the oxidant fluid orifices 82 as axially (Z) separated and radially (Theta) aligned.
  • Oxidant fluid orifices 82 may similarly be circumferentially aligned with fuel fluid orifices 82 as depicted here. Such configurations may improve jet penetration into the combusting fluid flow.
  • Fig.3T depicts a schematic radial circumferential (R Theta) cross section “elevation view” of an outer combusting region wall 736 with an insulating liner 738 bounding the combusting region with an outer radius CR15.
  • Outer fuel fluid orifices 87 may be configured at a positive angle PhiX (or a negative angle -PhiX) from the radial axis R to deliver fuel fluid in the negative CCW direction.
  • Fig.3T further shows an inner combusting region boundary wall at CR16 radially displaced by a radial thickness CR15T from the outer combusting region wall.
  • the radially inner combusting wall may have an outer insulating liner 738 protecting a radially inner structural wall 737.
  • Inner oxidant fluid orifices 88 may be configured at an opposing negative angle -PhiX (or an opposing positive angle PhiX) from the radial axis R to delivery oxidant fluid in the negative CCW direction.
  • Fig.3T may similarly be configured with fuel fluid orifices 87 oriented with a negative angle -PhiX, and oxidant fluid orifices 88 oriented in the opposite direction with a positive angle PhiX. Further configurations may comprise both fuel fluid orifices 87 and oxidant fluid orifices 88 configured with the same positive angle PhiX. Similar configurations may comprise fuel fluid orifices 87 and oxidant fluid orifices 88 configured with a similar negative angle -PhiX (or positive angle PhiX).
  • some fuel fluid delivery orifices 87 and oxidant fluid delivery orifices 88 in axially offset fluid feeders may be circumferentially oriented with similar positive angle PhiX (or negative angle -PhiX).
  • upstream fluid delivery orifices 87 (or 88) and downstream fluid delivery orifices 88 (or 87) may be configured with opposing positive angles PhiX and negative angles -PhiX) oxidant (not shown).
  • upstream fuel fluid orifices 81A may be circumferentially offset from (or aligned with) downstream oxidant fluid orifices 82B.
  • upstream oxidant fluid orifices 82A may be circumferentially offset to (or aligned with) downstream oxidant fluid orifices 82B.
  • Fig.3U depicts a radial circumferential (R Theta) “elevation” view of a sample configuration of outer transverse Fuel feeders marked F, and alternating outer oXidant transverse feeders marked X.
  • These fuel and oxidant feeders may have a radially outer wall 802 bounded by an outer radius CR11.
  • These feeders may have a radially inner wall 801 bounded by a feeder inner radius CR15, forming a radially outer surface of the inner first combusting region.
  • the outer feeder inner wall 801 may comprise a radially outward (structural) side wall 736 covered on the inner combusting region side by a protective thermal insulating coating 738.
  • Fig.3U further depicts fuel feeders F comprising fuel fluid orifices 87 to deliver fuel fluid into the adjacent inner combusting region.
  • oxidant feeders X may comprise orifices 88 delivering oxidant fluid into the adjacent combusting region radially inwards of the feeder inner 801 wall at CR15. As shown, oxidant feeders X may be circumferentially wider in the transverse (Theta) direction than fuel feeders F to accommodate the larger volumetric oxidant fluid flows versus smaller fuel fluid flows. [0112] Per Fig.3U in some configurations, outer fuel fluid orifices 87 and oxidant fluid orifices 88 may both be angled circumferentially with a negative angle (-PhiX) from the radial axis R.
  • Other configurations may use fuel fluid orifices 87 and oxidant fluid orifices 88 with the opposite circumferential positive angle (PhiX) from the radial axis R.
  • Further configurations may alternate angles of fuel fluid orifices and oxidant fluid orifices positive (PhiX) and negative (-PhiX) angles between radially inward and outward orifices.
  • FIG.3U shows a radially inward (“lower”) feeder array portion from the outer feeder wall radius CR16 (or radially inner combusting region boundary) with outer insulating layer 738 protecting combusting chamber radially inner wall 737, to radially inner feeder wall radius CR20.
  • Joint fluid width widths of fluid feeder pairs shown in Fig.3U may include a first oxidant-fuel fluid pair width (FP1) and a second oxidant-fuel fluid pair width (FP2).
  • inner oxidant (X) fluid feeders may be configured opposite outer fuel (F) fluid feeders
  • inner fuel (F) fluid feeders may be configured opposite to outer oxidant (X) fluid feeders.
  • common circumferentially transverse (outer) walls 133 may be used for opposite outer CounterClockWise (CCW) (“transverse”) and ClockWise (CW) boundaries.
  • CCW CounterClockWise
  • fuel (F) fluid orifices 87 may be configured circumferentially about the middle of fuel fluid feeder (F) with a circumferential offset of about PWF/2 from the fuel -oxidant feeder dividing wall 133.
  • the oxidant orifices 88 may be configured about midway (transversely) across the oxidant feeder displaced by a distance of about PWX/2 from the fuel- oxidant feeder dividing wall 133 (such as circumferentially aligned oxidant fluid orifices 82 as shown in Fig.3S).
  • Fig.3U depicts a configuration where the radially inward (“lower”) oxidant feeders (X) may have two oxidant orifices 88 transversely configured within the oxidant feeder (X).
  • these two orifices 88 may be positioned transversely at about a distance PWX/3 of about one third the passage Width of oXidant feeder from the oxidant feeder walls (similar to configurations of oxidant fluid orifices 82 of diameter DXO as shown in Fig.3R.)
  • orifices may be aerodynamically configured to reduce combustor pressure drop and to improve efficiency.
  • Fig.3V depicts a detailed view of a fluid orifice in the Radial Circumferential (R Theta) plane with fluid flow F through an outer combustor wall.
  • fluid F may flow in through an oxidant fluid orifice of diameter DXO through a feeder structural wall of thickness CR13T protected by a feeder wall insulating coating of thickness CR14T.
  • the fluid inlet and outlet may have rounded corners.
  • the upper orifice inlet may have a smaller radius ROI while the lower orifice outlet may have a larger orifice outlet ROO.
  • Fig.3W depicts a detailed view of an angled orifice in the Radial Circumferential (R Theta) plane through the outer combustor wall of thickness CR13T with an insulation layer of thickness CR14T.
  • the angled oxidant fluid orifice may be configured with a flow axis at an angle THM relative to the Radial axis R with a diameter DXO perpendicular to the orifice flow axis.
  • Inlet corners of such angled orifices may be configured about an acute angle with a smaller radius ROIA and about an obtuse angle with a larger radius ROIB.
  • Corresponding outlets of such angled orifices may have smaller radius ROOA for an acute angled outlet radius and a larger radius ROOB for an obtuse angled outlet radius.
  • Fig. 3X depicts a closed end of an oxidant feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold fuel fluid flow FFM flowing axially past the closed end, and a fuel feeder flow portion FFF flowing around the closed end.
  • the oxidant fluid manifold may have an outer oxidant feeder axial width PXWO, and an inner oxidant feeder axial width PXWI with feeder wall thickness FWT.
  • the oxidant feeder axially upstream radius RXU may be configured smaller than the downstream oxidant radius RXD. E.g., the downstream radius RXD may be twice that of the upstream radius RXU or more.
  • Fig.3Y depicts a closed end of a fuel fluid feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold oxidant fluid flow FXM flowing axially past the closed end, and an oxidant feeder flow portion FXF flowing around the closed end.
  • such fuel fluid feeders may have an outer fuel feeder axial width PFWO, and an inner fuel feeder axial width PFWI, with feeder wall thickness FWT.
  • the oxidant feeder axially upstream radius RFU may be configured smaller than the downstream oxidant radius RFD. E.g., the downstream radius RFD may be twice that of the upstream radius RFU or more.
  • Numerous Orifices to Improve Mixing [0127] In some configurations, fuel, oxidant, and/or diluent orifices may be used. Orifice size may be correspondingly reduced, such as to maintain overall cumulative orifice area within a desired range of the downstream combusting system cross sectional area.
  • each combusting shell may use 50 to 100 oxidant orifices. In other configurations this may be increased to 101 to 200 oxidant orifices. Similarly, 201 to 400 oxidant orifices may be used. Further combustors may use 401 to 800 orifices or more, such as for difficult fuels like ammonia.
  • Such changes may beneficially be used to facilitate combustion of fuels with higher ignition energy, higher combusting temperature, slower flame speed, and/or slower combusting rates.
  • Modeling Combustion and Emissions [0131] The applicant won two US Department of Energy High Performance For Computing Manufacturing supercomputer grants. Simplified scalable combustors (such as using an asymmetric combusting region and a cylindrical equilibrating region), were modeled using more than 110 independent parameters.
  • RCFD reactive computational fluid dynamic modeling
  • LLNL Lawrence Livermore National Labs
  • Those methods and resulting software enabled the applicant to configure its scalable gas turbine combustor configurations so as to probably achieve less than 1 ppmvd each for UHC, Nox and CO emissions over commercial gas turbine operating conditions. This predicts emissions below the strictest California county emission requirements of 2.3 ppmvd Nox and CO without using catalysts.
  • Such very low emissions provide major advantages with typically 7% to 10% lower CapEx for commercial gas turbines operating on natural gas.
  • Fig.3F depicts an example of modeling combusting ammonia (NH3) fuel with air, and diluent water and steam, along a flow axis from the upstream combusting inlet CZ34 to the downstream combustor outlet at CZ4.
  • This exploratory reactive RCFD modeling of diluted NH3 air combustion was conducted in applicant’s prior simplified scalable combustor.
  • the left axis shows the mean cross-sectional temperature
  • the right axis the outlet NOx and NH3 emissions in PPMVD (parts per million diluted to 15% O2).
  • the mean upstream combusting hot gas temperature peaks near 1,830K ( ⁇ 1,557oC) about the end of the Blend-Trim region T1.
  • an assumed combustor wall cooling rate is prescribed, reducing the combustor outlet temperature at CZ4 to a prescribed 1,527K (1,300oC) typical of a mid-range gas Turbine Inlet Temperature (TIT).
  • Cooling Combustion In some configurations, remaining undelivered diluent may be moved from the downstream Trim region feeders T1 to be delivered up into the Blend region feeders (e.g., B1 and B2). A major portion of this remaining diluent may be delivered to the upstream Blend feeder B1 to provide cooler rich (sub stoichiometric) combustion, with temperature being controlled independently of the relative local fuel to oxidant ratio Phi (or the relative local oxidant to fuel ratio Lambda).
  • part of this diluent may further be delivered further upstream into the downstream end of the combusting region, such as to delivering with fuel U7 and/or oxidant fluid X7 (or optionally diluted oxidant fluid) in the axially downstream (or last) combusting region axial 733.
  • Such diluent may further be delivered into the last two to last seven combusting regions upstream of CZ35.
  • Excess oxidant (or air) T1 may similarly be delivered in through the downstream Trim region. Such a combination of upstream diluent and downstream excess oxidant may achieve the coolest Blend region rich combustion with the least oxidant up to stoichiometric combustion.
  • ammonia may be delivered upstream under hot fuel rich (excess fuel, sub-stoichiometric oxygen) conditions (with Phi ( ⁇ ) > 1 or Lambda ⁇ 1). Upstream combusting temperatures may be increased by reducing upstream diluent. Such conditions may increase upstream ammonia cracking to hydrogen and nitrogen. Such in situ rich cracking of ammonia to hydrogen and nitrogen may facilitate downstream rich combustion, thereby reducing overall NOx formation.
  • Some configurations may configure the temperature of transverse feeders adjacent to the combusting region, and/or in the upstream combusting region sufficient to thermally crack a portion of ammonia fuel to hydrogen and nitrogen. Catalysts may similarly be used within transverse fluid feeders to crack ammonia.
  • Thermally Igniting Flows In some configurations, an energetic fluid may be formed by heating one or more delivered fluids to temperatures such that the temperature and flow rate of the delivered energetic reactant and co-reactant mixture gas is sufficient to ignite the reactive fluid in the primary reaction zone.
  • Manufacturing Methods [0151] One or more of such scalable parametric combustor configurations depicted may be constructed using additive manufacturing (or “3D printing”) techniques.
  • Such manufacturing techniques may facilitate forming the numerous oxidant fluid, fuel fluid, and diluent fluid transverse feeders with the corresponding orifices delivering fluid from the transverse feeders into the combusting chambers.
  • scalable shell combustors may be formed in two halves with inner insulating coatings over outer structural walls. These may then be assembled and be suitably held, bonded or fastened together.
  • orifices may be formed by laser ablation, chemical etching, mechanical or fluid jet drilling, or similar material removal techniques.
  • Turbulence generators may be configured along one or both surfaces bounding a combustion region within the scalable combustor.
  • duct, tube or array configurations are provided, similar two- or three- dimensional configurations or combinations of those configurations may be efficaciously utilized, including varying the nominal thicknesses, diameters, cross sectional shapes, spacings, orientations, and other dimensions and parameters for perforated ducts, perforated tubes, manifolds, sub-manifolds, feeders, combusting, blend, trim, equilibrating and transition regions, and tube arrays.
  • Fig.4A schematically shows a Scalable Gas Turbine Power System 1 with a Scalable ComBustion System (herein “CMB”) as used in a VAST Power Cycle.
  • CMB Scalable ComBustion System
  • This Scalable Gas Turbine Power System 1 is shown receiving compressed oxidant fluid from an upstream Compressor 407 (herein “CPR”) axially to axially feed a downstream gas turbine expander 440 (herein “EXP”).
  • CPR upstream Compressor 407
  • EXP downstream gas turbine expander 440
  • ASME American Society of Mechanical Engineers
  • CZ Combustor axial flow Z direction
  • a portion of compressed oxidant may flow into an upstream ignition system or Pilot 100 (herein “P”) at a Pilot or combustor inlet plane CZ31.
  • Another portion of compressed oxidant fluid (herein “WX34”) may be delivered upstream into a hot ignitor fluid delivery at CZ31 into the combusting section such as at plane CZ32.
  • Diluent fluid may be delivered upstream to CZ32, such as liquid water as a spray WDL32 into upstream inlet oxidant flow WX34.
  • a portion of diluent WDL32 may be delivered into an upstream typically fuel rich combusting region 730 from a combusting region inlet at CZ34 up to a Blend- Trim region inlet and combusting region outlet plane CZ35 (marked here as a combustor reference plane CBQ).
  • Fig.4A further schematically shows a “Blend-Trim” Region 850 extending from an upstream Blend-Trim inlet plane CZ35 (or combusting region outlet plane) through to a downstream Equilibrating Region inlet plane CZ39 (or Blend-Trim Region outlet plane). Equilibrating Region [0164] With reference to Fig.
  • an Equilibrating Region 900 may be provided downstream of the Blend-Trim region 850.
  • This Equilibrating Region 900 may extend from the Blend-Trim region outlet at plane CZ39 to a Transition Zone Inlet plane CZ394 (or an Equilibrating Region outlet plane) to provide residence time to further complete the reaction or combustion.
  • Transition Region [0165] Per Fig.4A, a Transition Region or Zone 980 may follow the equilibrating region 900 to accelerate the hot flow to the combustor outlet.
  • the equilibrating and transition regions may be aerodynamically configured to reduce flow pressure losses.
  • the Turbine Inlet mass flow (or Combustor Outlet mass flow), (herein “W4”) flows into the Expander EXP from the Combustor outlet at axial plane CZ4.
  • Cooling diluent liquid mass flow (herein “WDL45”) may be delivered into the expander to cool hot components such as blades, stators and/or walls.
  • Expanded fluid mass flow may flow from the expander EXP at axial plane CZ5 into a downstream heat exchanger, here depicted as a Once Through Steam Generator (herein “OTSG”).
  • OTSG Once Through Steam Generator
  • W51 cooled mass flow
  • HX downstream heat exchanger
  • a cooled heat exchanger outlet mass flow or exhaust flow (herein “W52”) (at an axial flow stage CZ52 downstream of the heat exchanger HX not shown) may be further cooled downstream as desired to further condense diluent vapor and/or to further cool diluent liquid and non-condensable flue gas, such as by using water- or air-cooled heat exchangers (not shown).
  • W52 cooled heat exchanger outlet mass flow or exhaust flow
  • diluent vapor may be condensed, forming sub-atmospheric pressure, together with a recompressor compressing the cooled expanded excess oxidant and non-condensed combustion products back to atmospheric pressure discharge as detailed in prior patents (not shown).
  • Fig.4A further depicts upstream gas combusting temperatures being controlled by thermal diluent flows such as water and/or steam (or similarly CO 2 ) relative to fuel fluid delivery.
  • thermal diluent flows such as water and/or steam (or similarly CO 2 ) relative to fuel fluid delivery.
  • Such diluent fluids may be delivered into multiple upstream combusting regions (from CZ34 to CZ35).
  • C1 Combusting regions
  • Fig.4G Combusting regions
  • C1- C6 not labeled
  • Fig.4I Combusting regions
  • C1-C8 implied, not labeled
  • Fig.4A shows further mass flow of oxidant fluid (herein “MX”) and mass flow of diluent fluid (herein “MD”) may be delivered into the Blend-Trim region (from CZ35 to CZ39).
  • MX mass flow of oxidant fluid
  • MD mass flow of diluent fluid
  • further oxidant such as air
  • diluent such as water and/or steam
  • may be delivered into one or more Blend regions herein shown as a first Blend Region One “B1” and a second Blend Region Two “B2”
  • Trim regions herein shown as a First Upstream Trim Region “T1” and optionally a Second Downstream Trim Region “T2”.
  • Fig.4A shows further oxidant and/or diluent may be delivered into a Blend-Trim region.
  • further oxidant such as air
  • diluent such as water and/or steam
  • the one or more Blend regions e.g., B1 and B2
  • Trim regions e.g. Upstream T1 and downstream T2
  • Fig.4A shows an inlet mass flow of oxidant (or air) (herein “WX2”) with an optional compressor inlet mass flow of liquid diluent (such as liquid water spray mass flow) (herein “WDL2”) into the inlet CZ2 of the compressor 407 (CPR).
  • WX2 oxidant
  • WDL2 liquid water spray mass flow
  • WDL25 compressor cooling liquid spray mass flow
  • the compressor 407 may feed a mass flow of compressed oxidant fluid flow (or air) (with optional vaporized diluent) (herein “WX3”) into the upstream inlet of a VAST scalable combustor CMB at an upstream flow location CZ3.
  • WX3 compressed oxidant fluid flow
  • the downstream combustor outlet may feed equilibrated and accelerated hot gas flow W4 at flow location CZ4 into an expander EXP.
  • the scalable combustor CMB may include an upstream diffuser, DIF, that expands and slows the oxidant (or air) from the compressor outlet / diffuser inlet CZ3 to feed an upstream combusting section from CZ34 to CZ5 a VAST combustor (CMB) that extends from the upstream diffuser (DIF) inlet at CZ3 (to a combustor pilot inlet plane CZ31) (to the transition zone at CZ394), and to the downstream outlet plane CZ4.
  • Fig.4A further depicts an upstream ignition authority or Pilot 100 (P).
  • Pilot P may be fed with a pilot fuel mass flow (herein “WF31”), a pilot oxidant mass flow (herein “WX31”), and optionally pilot diluent (herein “WDL31”) such as pilot liquid water.
  • Further fuel fluid (herein “WF32”), and further diluent fluid (herein “WDS32”) such as steam, may be mixed and delivered as a diluted fuel fluid mass flow (herein “MF”) into a diluted fuel manifold, to feed transverse fuel feeders into combusting regions (such as C1 to C7).
  • MF diluted fuel fluid mass flow
  • WX34 Further oxidant fluid (herein “WX34”) may be delivered together with various flows of upstream diluent fluid (herein “WDL32”) and/or mixtures may then be progressively fed into the combustor via multiple feeders (C1 through C7), delivering one or more mass flows of fuel fluid (MF), oxidant fluid (MX), and diluent fluid (MD) oriented generally across or transverse to the axial flow.
  • WDL32 upstream diluent fluid
  • MD diluent fluid
  • Fig.4A depicts stoichiometric diluted oxidant and/or diluent mass flows being then fed into a Blend-Trim region 850 thru one or more transverse Blend region feeders (B1 and B2), with the remaining oxidant and/or diluent fluids delivered through one or more Trim region feeders, (upstream T1, and optional downstream T2 Trim regions etc., not shown) between combustor axial planes CZ35 and CZ39.
  • Fig.4A further shows mass flows of liquid diluent (herein “WDL42”) into a heat exchanger HX.
  • WDL42 liquid diluent
  • WDL41 Heated liquid from HX flows (herein “WDL41”) into the Once Through Steam Generator (herein “OTSG”), and upstream into the upstream combustor (herein “WDL32”), into the Blend-Trim region (herein “WDL35”), and into the downstream combustor walls in the equilibrating region and transition region, (herein “WDL398”).
  • Fig.4A shows a portion of heated liquid diluent WDL41 further recovering heat in the OTSG to form steam (herein “WDS4”).
  • This vaporized diluent may be delivered back into the Blend Trim region as WDS35, and into the upstream region as WDS32 such as into the upstream fuel mass flow MF at CZ32.
  • an upstream premix region may be provided between the compressor outlet / diffuser inlet CZ3 and the combusting region outlet at CZ35. This may deliver liquid diluent WDL32 into the oxidant mass flow MX feeding one or more combusting regions C1 through C7. This premix region may similarly be located between an upstream combustor inlet plane CZ31 near the inlet 100 pilot P and the combusting region inlet near CZ34. [0181] The premix region may comprise perforated direct contact tubes 14 connected to a liquid diluent supply flow WDL31 to deliver diluent spray into the upstream oxidant fluid WX34.
  • Valves may be configured to control delivery of one or more flows of fuel and/or diluent into one or more of the diffuser DIF, the pilot P, combusting region 730, and Blend-Trim region 850, etc.
  • Valve VDL42 may control the return flow of diluent liquid through the heat exchanger HX.
  • Valve VDL35 may control flow of heated liquid diluent WDL35 into the Blend-Trim region 850.
  • Valve VDL32 may control liquid diluent WDL32 to the combusting region manifold 730.
  • VF32 may control fuel fluid flow WF32 into the combusting system.
  • Valve VF31 may control fuel fluid flow WF31 to the pilot P.
  • some scalable combustor embodiments may comprise a cylindrical combustor 704, with an outer cylindrical outer pressure vessel 172, and an inner cylindrical axial pressure wall 147, with a common axis from an upstream inlet 134 to a downstream outlet 136, parallel to the combustion flow direction.
  • Fig. 4B further depicts an upstream ignition (pilot) section 720, a fuel rich Combusting section 730, a Blend-Trim region 850 with residual diluent and oxidant delivery, and a downstream Equilibration region 900.
  • transversely extended combusting sections 732 may be bounded with side walls 734.
  • the relative circumferential transverse wall elongation may be greater than 1.15 times the shallow spacing by radial depth of side walls 734. adjacent combustor wall between opposed transverse – axial combusting chamber walls.
  • Fig.4B a portion of the Scalable Combustor, CMB is depicted extending from a flame authority 100 or pilot P at axial flow location CZ31 from the outlet of the upstream diffuser through a combusting section 730 and a downstream Blend-Trim region 850 opening into the downstream equilibrating region 900.
  • Fig.4B shows an embodiment of a Cylindrical-Axial (circumferentially-radially stacked) combustor 702 shown in cylindrical coordinates with a Radial axis (“R”) perpendicular to an Axial flow axis (Z) with a circumferential direction Theta ( ⁇ ).
  • R Radial axis
  • scalable combustors may use a curvilinear flow axis with non- cylindrical walls.
  • Such embodiments may include multiple scalable (“fan”) combusting shells (or burners) configured generally about Radial - Circumferential Theta (R - ⁇ ) cylindrical surfaces. These cylindrical combusting shells may be stacked radially, and generally perpendicularly, to the primary streamwise flow axis of oxidant fluid F5 through the scalable combustor, oriented along the axial (Z) flow direction, from an upstream fluid inlet 134 to a fluid flow outlet 136 for heated pressurized hot combusted fluid F20.
  • fan combusting shells
  • R - ⁇ Radial - Circumferential Theta
  • such scalable circumferential combustor embodiments 702 may be configured within an outer Pressure Vessel Wall 172.
  • a pilot fuel fluid flow F3, and a pilot oxidant fluid flow F6, may be delivered to an upstream Ignition Authority (Flame Igniter or Pilot) 100, configured to combust these fluids and to form a hot pilot fluid flow F22.
  • Pilot diluent fluid F8 flow may be separately delivered to the Pilot 100, and/or mixed in with pilot fuel fluid F3, and/or pilot oxidant fluid F6 flowing into the Pilot 100 in an upstream pilot region 720.
  • pilot fluid flow F22 from Pilot 100 may be distributed in upstream pilot region 720 to an upstream end of a pilot fluid distribution system 722 comprising one or more scalable pilot fluid delivery ducts (or “fan” burner ducts) 728.
  • pilot fluid delivery ducts (or “fan” burners) 728 may be configured circumferentially around the cylindrically stacked scalable combustor 702. [0192] Pilot fluid delivery ducts 728 may deliver hot pilot fluid into one or more combusting systems (or mid-fan burners) 732 in an axially intermediate combusting region 730.
  • each combusting system 732 generally comprises two radially opposing circumferential combusting radially outward side walls 736 (with corresponding radially inward side walls). These combusting radially outward side walls 736 may be bounded and connected by corresponding combusting (mid-fan) (circumferentially) end walls 734. In other configurations, radial side walls 736 may be curved around to radially meet and transversely or circumferentially bound the combusting region. [0194] Each combusting system radial side wall 736 may comprise numerous fluid delivery orifices 80 such as schematically depicted in Fig.4C.
  • Pressurized oxidant fluid F5 may be delivered into the Cylindrical-Axial combusting system 702 and delivered into combusting system 732 through orifices 80 configured in combusting system radial side walls 736.
  • the diameter or size of orifices 80 may vary transversely to adjust the fluid delivery rate per orifice.
  • diluted fuel fluid F2 may be delivered through a similar axial Fuel Manifold 770 between circumferentially adjacent combusting regions on alternating sides of the combusting regions from the oxidant fluid F5 delivery.
  • premixed reactive fuel-oxidant mixture with optional diluent may be delivered into the cylindrical-axial combustor 702, and delivered through perforated combustor radial side walls 736 in combusting systems 732 within the combusting region 730.
  • energetic fluid from one or more combusting systems 732 in combusting region 730 may be delivered to circumferential downstream Blend-Trim region 850 comprising Blend-Trim oxidant-diluent delivery and reacting region manifold walls 857 feeding related Blend-Trim reacting regions.
  • Each Blend-Trim reacting region 850 may comprise opposing circumferential Blend-Trim perforated side walls 857 to bound combustion within that region.
  • Blend-Trim region side walls 857 may generally be connected by one or more far-fan end walls 746.
  • the Blend-Trim side walls 857 may also be configured to join at their circumferentially transverse ends.
  • Multiple sets of circumferential combustors 732 and Blend-Trim Regions 850 may be configured within combustor outer wall or pressure vessel 172.
  • Fig.4C depicts an expanded view of a combustor wall section radial side wall 736 showing orifices 80 through a combustor fluid duct wall 132 protected by a thermal insulating barrier 150.
  • Fig.4D depicts a sample radial circumferential (R Theta) cross-section of a portion of a comBusting region extending circumferentially by a Combusting section angle THC.
  • This example shows an oXidant Manifold on the CCW side feeding oxidant fluid F5 with the THBMX CW portion shown as feeding two CW adjacent combusting regions.
  • Fig.4D depicts a fuel manifold encompassing a THBMF CW portion correspondingly feeding the two radially adjacent combusting regions including a combusting feeder radial depth (Thickness) CR15T.
  • Fig.4D further depicts an outer oxidant fluid feeder extending radially with a radial depth (Thickness) CR12T inside of an outer circumferential wall having an inner radius CR12. That outer oxidant fluid feeder extends circumferentially over an included angle THBFX4 and feeds oxidant fluid through multiple orifices into a combusting region extending radially with a radial depth (or Thickness) CR15T from outer wall inner radius CR15 to inner wall outer radius CR16.
  • Thickness radial depth
  • Oxidant fluid F5 optionally with diluent may flow along the oXidant fluid feeder and through oXidant orifices with a typical diameter DXO into a radially adjacent outer combusting region extending radially with a depth (or Thickness) CR15T between combusting chamber outer radius CR15 and combusting chamber inner radius CR16.
  • oxidant orifices may be offset from the CCW manifold by a circumferential angle THBXO, and spaced apart by a circumferential angle THBXS, with an Jth orifice in an Ith oxidant feeder positioned at a circumferential angle THBXIJ.
  • Fig.4D further depicts Fuel fluid flow F2 optionally diluted with diluent fluid, flowing through a CW comBusting region manifold extending through circumferential Theta angle THBMF.
  • This CW fuel fluid manifold delivers fuel fluid through a fuel complementary feeder extending radially with a depth (Thickness) CR18T, and feeding fuel fluid through fuel fluid orifices with typical fuel orifice diameter DFO into the outer combusting region between CR15 and CR16 extending radially with a depth (Thickness) CR15T and circumferentially about an angle THBFF4.
  • This fuel feeder with a depth CR18T may similarly feed fluid into an inwards combusting region extending radially between CR25 and CR26, and circumferentially across THBFF4.
  • diluted (“humid”) oxidant fluid F5 may similarly be delivered radially inward (and longitudinally) through the radial manifold feeder length RBFX4 and width Theta12T between circumferential angles Theta12 and Theta15 into a radial combusting region of circumferential width Theta15T.
  • diluent fluid F12 may be delivered into axially extending region RBMF of width Theta18T and thence through orifices of diameter DFO a radial CCW diluent manifold extending circumferentially by Theta18T for each of the central combusting regions extending by Theta 15T and radially by RBFF4, axially along the combusting region.
  • Fig.4E depicts a Radial Axial circumferential (R-Z) plan view of two radially adjacent symmetric combusting regions (CZ34 to CZ35) and Blend-Trim regions (CZ35 to CZ39).
  • the radially lower (visually right or clockwise CW) region depicts radially outward (CCW) bounding end walls 734 and radially inward (CW) bounding end walls 735.
  • Such combusting regions may extend axially from the upstream Pilot 100 outlet or combusting region inlet CZ34 to combusting region downstream axial boundary CZ35.
  • the downstream Blend Trim region may extend axially (Z) from CZ35 to CZ39.
  • such adjacent symmetric combusting regions may have radially outward adjacent (+R or CCW) oxidant fluid manifold regions, between manifold wall 250 and combusting wall 734 ducting oxidant fluid (or diluted oxidant fluid) F5 from upstream of inlet CZ34 into such adjacent combusting regions.
  • such symmetric combusting regions may have adjacent radially inward (-R or CW) fuel manifold regions, between manifold wall 250 and combusting wall 735, ducting fuel fluid (or diluted fuel fluid) F2.
  • Such outwardly adjacent (R+ CCW) oxidant manifolds and inwardly adjacent (- R CW) fuel manifolds may be commonly bounded and divided by a sigmoidally curved longitudinal (radial-axial R-Z) manifold divider wall 250 between combusting upstream inlet CZ34 and combusting midstream outlet CZ35 bounds, and thence to the Blend-Trim region axially between midstream Blend-Trim inlet planes CZ35 and the downstream Blend-Trim outlet planes CZ39.
  • FIG.4E The left (+R, CCW) portion of Fig.4E further depicts an upstream region circumferentially increasing transverse (radial) width region 731 with axial flow distance, downstream of the Pilot 100, having an increasing radial (R) width with an outward wall curvature along the axial (Z) direction.
  • This axially increasing combustion region volume may beneficially accommodate an axially increasing volumetric flow from increasing delivered oxidant, fuel and diluent mass flows, and from rising temperature with combustion, thereby reducing fluid acceleration and pressure drop losses.
  • Fig.4A and 4E similarly depict a configuration with a downstream combusting region 733 with transversely increasing width (radially +R to -R) (or CCW-CW) but with decreasing radial-axial wall curvature. This may beneficially provide an aerodynamically smoother transition between the Blend-Trim region and an equilibrating region extending downstream from planes CZ39 to CZ394 (as shown in Fig.4A).
  • Fig.4E further depicts an axially intermediate combusting transition region 732.
  • This intermediate combusting transition region 732 transverse width (+R to -R) may increase downstream with axial (Z) distance, from an axially increasing width wall curvature from combusting upstream section 731, to an axially decreasing width wall curvature such as in combusting downstream section 733.
  • Fig.4E depicts distributions of fuel fluid delivery orifices 81, and distributions of oxidant fluid delivery orifices 82 opening into the combusting region from CZ34 to CZ35. Further distributions of oxidant and/or diluent delivery orifices 83 may be configured downstream to open into the Blend-Trim region axially between planes CZ35 to CZ39.
  • This Blend-Trim combusting region with delivery orifices 83 may be transversely bounded by radially outward combusting wall 734 and radially inward combusting wall 735.
  • a downstream Blend-Trim manifold region may be provided to deliver diluted oxidant fluid F5 (or oxidant fluid F4 not shown) axially between axial planes CZ35 and CZ39, and bounded by radially outward (+R) transverse manifold (CCW) wall 250 and radially inward (-R) manifold (CW) wall 734.
  • This radially outward (+R) oxidant fluid delivery manifold between transverse manifold wall 250 and inward manifold wall 734 may bounded downstream at CZ39 by manifold wall 250 joining manifold wall 734.
  • Inward manifold wall 734 may be bounded with transverse manifold wall 250 joining with an axially upstream bounding wall 249 between the upstream delivery of diluted fuel flow F2 (or fuel fluid flow F1 not shown) and the downstream delivery bound (between manifold wall 250 and combusting wall 734) for Blend-Trim diluted oxidant fluid F5.
  • Fig.4E further depicts varying transverse positioning versus axial location of oxidant orifices 82, fuel orifices 81, and Blend-Trim diluted oxidant orifices 83
  • Fig.4G depicts a corresponding outward (or inward) axial circumferential (Z Theta) “unrolled” plan view of a symmetric combustor fluid feeder region. This extends axially in the flow direction from an upstream Pilot 100, with a CCW axial diluted oxidant fluid manifold region 244 ducting upstream diluted oxidant fluid F4 to upstream oxidant feeders.
  • the fluid feeder region of Fig.4G may include a second CCW axial oxidant manifold 245 ducting diluted oxidant fluid F5 further downstream.
  • the Fig.4G configuration similarly depicts a CW inward upstream first fuel manifold region 242 ducting first fuel fluid F1 comprising a fuel to upstream feeders. This may be divided by Upstream/Downstream Fuel Fluid Manifold Dividing wall 252 from a second intermediate CW outward fuel fluid manifold region 243, such as ducting a Diluted Fuel Fluid flow F2 (or another flow of Fuel Fluid) further downstream.
  • an upstream to Downstream Fuel Feeder to Blend- Trim Dividing Wall 253 may divide and separate upstream diluted fuel fluid F2, flowing through the intermediate fuel fluid manifold region 243 between CZ34 and CZ35, from Blend-Trim diluent flow F7 flowing downstream to the Blend-Trim region 850 between planes CZ35 and CZ39.
  • Manifold bounding wall 253 may adjoin the downstream diluted oxidant or diluent fluid feeder extending down to plane CZ39.
  • the CCW oxidant fluid manifolds and CW fuel fluid manifolds may be separated by a sigmoidally curved longitudinal radial manifold divider 250 that colds the downstream transverse Trim feeder ending axially at plane CZ39.
  • Downstream Combusting-oxidant fluid manifold divider 248 may be similarly curved and configured parallel to the manifold divider 250 and aerodynamically curved as it connects with the upstream of the transverse Blend-Trim feeder opening at CZ35.
  • An axial-radial manifold divider 253 bounding between diluted fuel fluid flow F2 and diluent fluid flow F7 may be curved or sigmoidal from upstream CZ34 to downstream at CZ35 where it adjoins oxidant feeder delivering oxidant fluid X7 (or optionally diluted oxidant fluid).
  • axial radial mid Upstream Combusting oXidant Manifold Dividing wall 247 may divide Diluted Rich oXidant Upstream Fluid Manifold 244 from second Diluted Rich oXidant Downstream Fluid Manifold 245.
  • downstream axial radial oXidant-Blend-Trim manifold wall 248 may divide midstream second oxidant fluid manifold 245 from diluted oxidant Blend-Trim manifold 246.
  • a first fuel fluid F1 (optionally diluted) may be delivered into fuel fluid manifold 242 bounded by Fuel Feeder Upstream/Downstream Manifold Dividing Wall 252, and be delivered as multiple fuel fluids, such as U1, U2, and U3, flowing through respective multiple transverse fluid fuel fluid feeders.
  • These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that range.
  • a second diluted fuel fluid F2 (or a second fuel fluid flow not shown) may be delivered into downstream fuel fluid manifold 243 and be delivered as multiple fuel fluid flows U4, U5, U6 and U7 flowing into multiple transverse fluid fuel fluid feeders and thence into the adjacent combusting region via fuel fluid orifices 81A.
  • These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that axial range.
  • oxidant fluid F4 may be delivered via Diluted Oxidant Fluid Upstream Manifold 244 as oxidant fluid flows X1, X2, and X3 through multiple transverse oxidant fluid feeders and thence through oxidant fluid orifices 82A. Such oxidant fluid F4 delivery may interleave with delivery of first fuel fluid F1, such as through U1 to U3, through respective upstream transverse fuel fluid feeders.
  • oxidant fluid F5 may be delivered via Diluted oXidant Fluid Downstream Manifold 245 as oxidant fluid flows such as X4, X5, X6, and X7 (or optionally diluted oxidant fluid) through multiple respective transverse oxidant fluid feeders, and thence into the adjacent combusting region via multiple oxidant fluid orifices 82B.
  • Such oxidant fluid delivery through oxidant feeders may interleave fuel fluid delivery flows, such as U4 to U7, through respective transverse fuel fluid feeders in the upstream combusting region from CZ34 to CZ35
  • diluted oxidant fluid F6 may be delivered via CCW Diluted Oxidant Blend-Trim Manifold 246 to downstream Blend-Trim feeders.
  • Blend fluids such as B1 and B2
  • Upstream Blend-Trim orifices 83A, and Midstream Blend-Trim Orifices 83B into the radially adjacent Blend-Trim region downstream of the combusting region.
  • a portion of diluted oxidant fluid F6 may be delivered as one or more Trim fluid flows, such as T1, through a transverse trim feeder and thence through Downstream Blend-Trim orifices 83C into the radially adjacent Blend-Trim region between planes CZ35 and CZ39, axially downstream of the combusting region.
  • Trim fluid flows such as T1
  • Blend-Trim diluent fluid F7 may be delivered via CW Diluent-Trim manifold 238 downstream into Diluent-Trim region 850 between CZ35 and CZ39.
  • Blend-Trim diluent fluid F7 may be delivered as one or more diluent fluids D1, D2, and D3 through transverse diluent feeders and thence through diluent fluid orifices 86A, 86B, and 86C, into the radially adjacent downstream Blend-Trim region of the combustor.
  • walls 253 and 250 of CW diluent trim manifold 238 to the Blend- Trim feeder region may be outwardly curved in an axially upstream section 731. They may similarly be inwardly curved in axially downstream section 733.
  • the intermediate combusting region 732 may be sigmoidally curved section to aerodynamically connect upstream section 731 and downstream section 733. (In other configurations intermediate combusting region 732 may be linearly configured.) Downstream section 850 of bounding wall 250 may transition from inwardly curved section 733 to connect aerodynamically with the downstream equilibrating region axial slope.
  • Asymmetric Combusting Systems [0229] Per Fig.4H, and Fig.4I, some combustor configurations may use an asymmetric combustor about a longitudinal oxidant manifold feeding transverse circumferential oxidant fluid feeders on the CCW and CW sides of the oxidant manifold.
  • FIG.4H depicts a circumferentially (Z Theta) “unrolled” plan view of two adjacent asymmetric combusting regions with an axial fluid flow axis Z, and circumferential axis Theta perpendicular to a radial axis R. This may have combustor walls radially adjacent to the combusting region, with fuel fluid orifices 81, oxidant fluid orifices 82, and/or Blend-Trim region diluent fluid delivery orifices such as 83.
  • such asymmetric combusting region configurations may have circumferentially adjacent oxidant fluid manifold bounding Combustion Chamber Transverse CCW side End Wall 734 directing oxidant fluid F5 between upstream combusting region inlet CZ34 and combusting fluid downstream end CZ35. They may similarly have circumferentially adjacent bounding fuel fluid Combustion Chaber Transverse CW side End Wall 735 delivering fuel fluid F2 between CZ34 and combusting region Downstream Manifold End Dividing Wall 249.
  • diluted oxidant fluid F7 may be delivered into the downstream Blend-Trim manifold region 850 bounded by side bounding manifold walls 735 and axially bounding Downstream Manifold End Dividing Wall 249, extending axially from planes CZ35 to CZ39.
  • Some asymmetric combusting region configurations may include a common upstream Pilot 100 feeding adjacent combusting shells. This Pilot 100 may be fed by Pilot Fuel Fluid F3, Pilot Oxidant Fluid F6, and Pilot Diluent Fluid F8.
  • the asymmetric combustor configuration of Fig.4H may have a sigmoidally curved oxidant fluid boundary such as described in Fig.4H and adapted to such an asymmetric configuration. This may have a circumferentially (Theta) outwardly curving upstream manifold-combusting region bounding wall section 731 with axially increasing distance Z.
  • the asymmetric combustor may have a correspondingly circumferentially (Theta) inwardly curving downstream manifold with bounding Combustion Chamber Downstream Transverse End Wall section 733 with axially increasing distance Z.
  • the asymmetric combustor configuration of Fig.4H may have a connecting intermediate Combusting Chamber Midstream Transverse End Wall 732 transitioning from the outward to the inward circumferential-axial curvature.
  • the oxidant fluid manifold of Fig.4H may further have a downstream Blend- Trim region 850 with a Blend-Trim diluent/oxidant fluid manifold wall 734 that may have an aerodynamically varying curvature between the axially upstream adjacent combusting region downstream transverse end wall 733 and the downstream equilibrating region wall beginning at CZ39 and extending into equilibrating region 900 per Fig.4A.
  • Fig.4I depicts an example of a circumferentially “unrolled” circumferentially- axially (Z Theta) asymmetric combustor fluid feeder configuration.
  • first fuel fluid flow F1 may be delivered into an upstream transverse fuel fluid feeder as fuel fluid U1 and thence into the combusting region through one or more fuel fluid orifices 81A.
  • further portions of first fuel fluid F1 may be delivered into progressively downstream transverse fuel fluid feeders as to feed fuel fluids U2 and U3. These may be delivered from the transverse fuel fluid feeders through similar or increasing number of fuel fluid orifices 81A into the radially adjacent combusting region.
  • Fig.4I similarly depicts an oxidant fluid manifold axially feeding oxidant fluid F4 flows X1, X2 and X3 progressively axially into respective upstream transverse oxidant fluid feeders and thence into oxidant fluid orifices 82A into the radially adjacent combusting chamber.
  • Combinations of the size, (or area), number of the respective fuel fluid orifices 81, oxidant fluid orifices 82, and relative fuel fluid and oxidant fluid delivery pressures may be configured to provide a desired range of relative fuel to oxidant composition relative to stoichiometric composition (PHI). (Or equivalently, the relative oxidant to fuel ratio LAMBDA).
  • first fuel fluid F1 and/or oxidant fluid F4 may comprise gaseous and/or liquid diluent, such as steam, water vapor, and/or liquid water as delivered through transverse feeders and orifices into the combusting chamber.
  • diluted fuel fluid F2 may be axially delivered through a fuel fluid manifold and thence into one or more transverse fuel fluid feeders as fuel fluid flows U4, U5, U6 and/or U7.
  • oxidant fluid flow F5 may be delivered through the outer axial oxidant fluid manifold and then as one or more oxidant fluid feeder flows, such as X4, X5, X6, into respective transverse oxidant fluid feeders and thence through oxidant fluid orifices 82B into the radially adjacent combusting region.
  • diluent fluid F14 such as liquid water
  • diluent fluid flows D1 and D2 may be delivered to downstream Blend-Trim region through one or more transverse feeders such as diluent fluid flows D1 and D2, and thence through orifices 86A into radially adjacent Blend-Trim region 850 in the combustor axially between planes CZ35 and CZ39.
  • further oxidant fluid optionally with diluent fluid may be delivered through transverse Blend-Trim feeders as Blend-Trim fluids B1 and/or T1 and thence through Blend-Trim orifices 83A and 83C into the downstream Blend-Trim region 850 of the combusting chamber axially between planes CZ35 and CZ39.
  • Cooling Upstream Combustion [0248]
  • the embodiments depicted herein enable further flexibility in configuring diluent delivery separately from oxidant and fluid delivery. This may be beneficially used to reduce and control combusting temperatures independently of relative fuel to oxidant composition (Phi) (or relative oxidant to fuel composition Lambda).
  • gaseous and/or liquid diluent fluid D1 and D2 may be delivered with one or more fuel fluid flows U5 to U7.
  • gaseous and/or liquid diluent fluid D1 and D2 may be delivered with oxidant fluids X4, X5, and/or X6.
  • Such increases in diluent fluid with the combusting fuel and oxidant fluid flows may be used to reduce the combusting temperatures and thence reduce emission formation such as NOx. In some configurations, this may be delivered with rich to stoichiometric portion of oxidant delivery to form associated rich to stoichiometric combusting regions.
  • one or more of axially upstream to downstream manifold walls may be fairly aligned axially between the upstream combusting region at CZ34, and the downstream connection with related transverse fluid delivery feeders. Such alignment may beneficially reduce the rate of change in axial fluid flow cross- sectional area (expansion) and delivery flow rate, and thereby reduce related fluid pressure drops.
  • Fig.4J depicts a schematic circumferentially (Z Theta) “unrolled” combusting section of a radially inward (or outward) wall configuration, depicting larger and more numerous upstream oxidant fluid delivery orifices 82 and downstream smaller and fewer fuel fluid delivery orifices 81. E.g., in a 2:1 ratio. Oxidant fluid orifices may be circumferentially offset from fuel fluid orifices to improve mixing and reduce quenching.
  • Fig.4K depicts a schematic circumferentially (Z Theta) “unrolled” combusting section radially inward (or outward) wall configuration with fewer upstream fuel fluid delivery orifices 81, and more numerous downstream oxidant fluid delivery orifices 82. E.g., in a 1:2 ratio. Fuel fluid orifices may be circumferentially offset from oxidant fluid orifices to improve mixing and reduce quenching probabilities.
  • Fig.4L depicts a schematic circumferentially (Z Theta) “unrolled” configuration a downstream Blend-Trim region section having oxidant fluid orifices 83A and 83C in a radially outward (or inward) Blend-Trim region wall.
  • Upstream Blend-Trim orifices 83A may be offset ClockWise (CW) from downstream Blend-Trim region orifices 83C.
  • Fig.4M depicts a sample schematic configuration of a downstream Blend-Trim region section having oxidant fluid delivery orifices 83A and 83C in a radially inward (or outward) Blend-Trim region wall.
  • Blend-Trim orifices 83A may be offset CounterClockWise (CCW) from ClockWise (CW) downstream Blend-Trim orifices 83C.
  • CCW CounterClockWise
  • Blend-Trim orifices 83A and 83C configured radially outward of a combusting region may be offset ClockWise (CW) and CounterClockWise (CCW) from Blend-Trim orifices 83A and 83C configured radially inward of the combusting shell.
  • Fig.4N depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut through a CounterClockWise (CCW) circumferentially outward combusting region wall 734.
  • CCW CounterClockWise
  • This sample configuration Fig.4N shows eight radially outward oxidant fluid delivery openings X1 through X8 for radially outward oxidant fluid feeders (or diluted oxidant fluid feeders).
  • Fig.4O depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut inward of the CCW circumferentially outward end wall (734) having eight radially outward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in outward transverse oxidant feeders.
  • Fig.4O further shows these outwardly oxidant fluid openings (X1-X8) may be complemented with eight interspersed radially inward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in inward transverse oxidant feeders.
  • These oxidant fluid passages (X1-X8 and X1-X8) may be interspersed with narrower fuel fluid delivery passages (unmarked).
  • Fig.4Q depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region through a Clockwise (CW) circumferentially outward side bounding combusting region end wall 735 having eight radially outward fuel fluid delivery openings U1 through U8. These may be complemented by and interspersed with eight radially inward fuel fluid passage openings U1 through U8.
  • Fig.4P depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region inward of the CW circumferentially outward end wall (735) having eight oxidant fluid feeder delivery passage openings (U1 through U8) interspersed with eight oxidant fluid feeder delivery passage openings (e.g., X1-X8 not labeled).
  • Figures 4N through 4Q further depict combustor radial height (or length) parameters labeled from the first outward combusting shell towards the next inward combusting shell.
  • CR12 labels the radially outward oxidant fluid feeder wall outer radius.
  • Figures 4N through 4Q further depict combustor radial inner height parameters labeled from the first outward combusting shell towards the next inward combusting shell along the radial R axis.
  • CR12T labels the radially inner depth (height or Thickness) of the outer oxidant fluid transverse feeders shown in Fig.4N and Fig.4O.
  • CR12T similarly labels the radially inner height of the outer fuel fluid transverse feeders shown in Fig.4P and Fig.4Q.
  • the radial parameter CR15T labels the combusting region radially inner height (Thickness) between CR15 and CR16 shown in Fig.4O and Fig.4P.
  • CR18T similarly labels the radial thickness of the radially inner oxidant and fuel transverse feeders between CR16 and CR24 shown in Fig.4N through Fig.4Q.
  • Figures 4N though 4Q further depict the combustor axial boundaries from the upstream combusting region boundary at CZ34 to the downstream combusting fluid delivery boundary at CZ35 (at a reference plane CBQ) along the axial flow Z axis.
  • Fig.4O further depicts typical Axially Inner Inlet Widths 810 of radially outer transverse oXidant fluid feeders X1 to X8 supplying the central combusting region near the outer open side (e.g., CounterClockWise CCW side near the oxidant fluid feeder opening from the adjacent oxidant manifold).
  • axially inner axial widths of radially inner transverse oxidant fluid feeders X1 to X8 supplying oxidant fluid into the central combusting region in Fig.4O may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis.
  • Fig.4O further depicts the corresponding Axially Inner Far End Widths 809 of radially outer transverse Fuel Fluid feeders U1 to U8 near the transversely closed end of the fuel fluid feeders near the adjacent oxidant fluid manifold (e.g., the CCW side).
  • Fig.4P further depicts typical Axially Inner Inlet Widths 808 of radially outer transverse Fuel Fluid feeders U1 to U8 supplying the central combusting region near the outer open side (e.g., the Clockwise CW side near the fuel fluid feeder opening from the adjacent fluid manifold).
  • the inner axial widths of radially inner transverse fuel fluid feeders U1 to U8 supplying fuel fluid into the central combusting region in Fig.4P may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis.
  • Fig.4P further depicts the corresponding axially inner widths 811 of outer transverse oxidant fluid feeders (X1-X8 not labeled) near the transversely closed end of the oxidant fluid feeders near the adjacent fuel fluid manifold (e.g., the CW side).
  • Fig.4P similarly shows the inner transverse oxidant fluid feeders (X1-X8 not labeled) between CR16 and CR24, with corresponding inner widths (811 not labeled) between fluid feeder walls.
  • Fig.4R schematically depicts an axial circumferential (Z Theta) plan view perspective of a pair of transverse fluid feeders delivering oxidant fluid X into multiple oxidant fluid orifices 82 with typical oxidant fluid orifice diameters DXO, and delivering fluid F into multiple fuel fluid orifices 81 with typical fuel fluid orifice diameters DFO.
  • the fuel fluid feeder is depicted with an axial width DFF compared to the wider Oxidant Fluid Feeder with an axial width DFX.
  • diluent feeders may be utilized with a Diluent Fluid Feeder width DFD (not shown).
  • fuel fluid orifices 81 in the fuel fluid feeder may be circumferentially displaced by a circumferential angle THF from the vertical plane, ClockWise (CW) positive.
  • oxidant fluid orifices 82 may be configured in pairs circumferentially positioned about fuel fluid orifices 81, with a narrower circumferential separation angle THXN between oxidant fluid between nearest centers of oxidant fluid orifices 82 of separated orifice pairs.
  • Oxidant fluid orifices 82 may have a wider adjacent orifice circumferential separation angle THXW between oxidant orifice centers of wider separated orifice pairs.
  • oxidant orifices may be spaced further apart, or may be spaced uniformly apart.
  • circumferential spacing of orifices about the combustor may be further varied along axially differing fluid feeders. These may use one or both of circumferentially even spacing, and circumferentially asymmetric spacing.
  • circumferential spacing may be closer near one and/or both inner and outer combusting chamber boundaries than in circumferentially inner regions. Other configurations may provide more space between orifices near circumferential boundaries.
  • Fig.4S shows another axial circumferential plan view of a fuel feeder feeding fuel fluid F through fuel fluid orifices 81 and an axially adjacent oxidant fluid feeder feeding oxidant fluid X through a multiplicity of oxidant fluid orifices 82.
  • This configuration depicts the oxidant fluid orifices 82 as axially (Z) separated and radially (Theta) aligned.
  • Oxidant fluid orifices 82 may similarly be circumferentially aligned with fuel fluid orifices 82 as depicted here. Such configurations may improve jet penetration into the combusting fluid flow.
  • Fig.4T depicts a schematic radial circumferential (R Theta) cross-section “elevation view” of an outer combusting region wall 736 with an insulating liner 738 bounding the combusting region with an outer radius CR15.
  • Outer fuel fluid orifices 87 may be configured at a positive angle PhiX (or a negative angle -PhiX) from the radial axis R to deliver fuel fluid in the negative CCW direction.
  • Fig.4T further shows an inner combusting region boundary wall at CR16 radially displaced by a radial thickness CR15T from the outer combusting region wall.
  • the radially inner combusting wall may have an outer insulating liner 738 protecting a radially inner structural wall 737.
  • Inner oxidant fluid orifices 88 may be configured at an opposing negative angle -PhiX (or an opposing positive angle PhiX) from the radial axis R to delivery oxidant fluid in the negative CCW direction.
  • Fig.4T may similarly be configured with fuel fluid orifices 87 oriented with a negative angle -PhiX, and oxidant fluid orifices 88 oriented in the opposite direction with a positive angle PhiX. Further configurations may comprise both fuel fluid orifices 87 and oxidant fluid orifices 88 configured with the same positive angle PhiX. Similar configurations may comprise fuel fluid orifices 87 and oxidant fluid orifices 88 configured with a similar negative angle -PhiX (or positive angle PhiX).
  • some fuel fluid delivery orifices 87 and oxidant fluid delivery orifices 88 in axially offset fluid feeders may be circumferentially oriented with similar positive angle PhiX (or negative angle -PhiX).
  • upstream fluid delivery orifices 87 (or 88) and downstream fluid delivery orifices 88 (or 87) may be configured with opposing positive angles PhiX and negative angles -PhiX) oxidant (not shown).
  • upstream fuel fluid orifices 81A may be circumferentially offset from (or aligned with) downstream oxidant fluid orifices 82B.
  • upstream oxidant fluid orifices 82A may be circumferentially offset to (or aligned with) downstream oxidant fluid orifices 82B.
  • Fig.4U depicts a radial circumferential (R Theta) “elevation” view of a sample configuration of outer transverse Fuel feeders marked F, and alternating outer oXidant transverse feeders marked X.
  • These fuel and oxidant feeders may have a radially outer wall 802 bounded by an outer radius CR11.
  • These feeders may have a radially inner wall 801 bounded by a feeder inner radius CR15, forming a radially outer surface of the inner first combusting region.
  • the outer feeder inner wall 801 may comprise a radially outward (structural) side wall 736 covered on the inner combusting region side by a protective thermal insulating coating 738.
  • Fig.4U further depicts fuel feeders F comprising fuel fluid orifices 87 to deliver fuel fluid into the adjacent inner combusting region.
  • oxidant feeders X may comprise orifices 88 delivering oxidant fluid into the adjacent combusting region radially inwards of the feeder inner 801 wall at CR15. As shown, oxidant feeders X may be circumferentially wider in the transverse (Theta) direction than fuel feeders F to accommodate the larger volumetric oxidant fluid flows versus smaller fuel fluid flows. [0285] Per Fig.4U in some configurations, outer fuel fluid orifices 87 and oxidant fluid orifices 88 may both be angled circumferentially with a negative angle (-PhiX) from the radial axis R.
  • -PhiX negative angle
  • Other configurations may use fuel fluid orifices 87 and oxidant fluid orifices 88 with the opposite circumferential positive angle (PhiX) from the radial axis R.
  • Further configurations may alternate angles of fuel fluid orifices and oxidant fluid orifices positive (PhiX) and negative (-PhiX) angles between radially inward and outward orifices.
  • FIG.4U shows a radially inward (“lower”) feeder array portion from the outer feeder wall radius CR16 (or radially inner combusting region boundary) with outer insulating layer 738 protecting combusting chamber radially inner wall 737, to radially inner feeder wall radius CR20.
  • Joint fluid width widths of fluid feeder pairs shown in Fig.4U may include a first oxidant-fuel fluid pair width (FP1) and a second oxidant-fuel fluid pair width (FP2).
  • inner oxidant (X) fluid feeders may be configured opposite outer fuel (F) fluid feeders
  • inner fuel (F) fluid feeders may be configured opposite to outer oxidant (X) fluid feeders.
  • common circumferentially transverse (outer) walls 133 may be used for opposite outer CounterClockWise (CCW) (“transverse”) and ClockWise (CW) boundaries.
  • CCW CounterClockWise
  • fuel (F) fluid orifices 87 may be configured circumferentially about the middle of fuel fluid feeder (F) with a circumferential offset of about PWF/2 from the fuel -oxidant feeder dividing wall 133.
  • the oxidant orifices 88 may be configured about midway (transversely) across the oxidant feeder displaced by a distance of about PWX/2 from the fuel- oxidant feeder dividing wall 133 (such as circumferentially aligned oxidant fluid orifices 82 as shown in Fig.4S).
  • Fig.4U depicts a configuration where the radially inward (“lower”) oxidant feeders (X) may have two oxidant orifices 88 transversely configured within the oxidant feeder (X).
  • these two orifices 88 may be positioned transversely at about a distance PWX/3 of about one third the passage Width of oXidant feeder from the oxidant feeder walls (similar to configurations of oxidant fluid orifices 82 of diameter DXO as shown in Fig.4R.)
  • orifices may be aerodynamically configured to reduce combustor pressure drop and to improve efficiency.
  • Fig.4V depicts a detailed view of a fluid orifice in the Radial Circumferential (R Theta) plane with fluid flow F through an outer combustor wall.
  • fluid F may flow in through an oxidant fluid orifice of diameter DXO through a feeder structural wall of thickness CR13T protected by a feeder wall insulating coating of thickness CR14T.
  • the fluid inlet and outlet may have rounded corners.
  • the upper orifice inlet may have a smaller radius ROI while the lower orifice outlet may have a larger orifice outlet ROO.
  • Fig.4W depicts a detailed view of an angled orifice in the Radial Circumferential (R Theta) plane through the outer combustor wall of thickness CR13T with an insulation layer of thickness CR14T.
  • the angled oxidant fluid orifice may be configured with a flow axis at an angle THM relative to the Radial axis R with a diameter DXO perpendicular to the orifice flow axis.
  • Fig. 4X depicts a closed end of an oxidant feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold fuel fluid flow FFM flowing axially past the closed end, and a fuel feeder flow portion FFF flowing around the closed end.
  • the oxidant fluid manifold may have an outer oxidant feeder axial width PXWO, and an inner oxidant feeder axial width PXWI with feeder wall thickness FWT.
  • the oxidant feeder axially upstream radius RXU may be configured smaller than the downstream oxidant radius RXD. E.g., the downstream radius RXD may be twice that of the upstream radius RXU or more.
  • Fig. 4Y depicts a closed end of a fuel fluid feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold oxidant fluid flow FXM flowing axially past the closed end, and an oxidant feeder flow portion FXF flowing around the closed end. [0299] Per Fig.
  • such fuel fluid feeders may have an outer fuel feeder axial width PFWO, and an inner fuel feeder axial width PFWI, with feeder wall thickness FWT.
  • the oxidant feeder axially upstream radius RFU may be configured smaller than the downstream oxidant radius RFD. E.g., the downstream radius RFD may be twice that of the upstream radius RFU or more.
  • Numerous Orifices to Improve Mixing [0300] In some configurations, fuel, oxidant, and/or diluent orifices may be used. Orifice size may be correspondingly reduced, such as to maintain overall cumulative orifice area within a desired range of the downstream combusting system cross-sectional area.
  • each combusting shell may use 50 to 100 oxidant orifices. In other configurations this may be increased to 101 to 200 oxidant orifices. Similarly, 201 to 400 oxidant orifices may be used. Further combustors may use 401 to 800 orifices or more, for more uniform combustion of difficult fuels like ammonia.
  • Such changes may beneficially be used to facilitate combustion of fuels with higher ignition energy, higher combusting temperature, slower flame speed, and/or slower combusting rates.
  • Modeling Combustion and Emissions [0304] The applicant won a US Department of Energy High Performance For Computing Manufacturing (HPC4Mfg) supercomputer grant, and an HPC4EnergyInnovation supercomputer grant.
  • VAST scalable combustors (such as using a scalable combusting region and a cylindrical equilibrating region), were modeled using more than 110 independent parameters.
  • 23 parameters were selected to model combustion over typical gas turbine pressures, temperatures, and specific power rates.
  • Argonne National Laboratory (herein ANL) conducted reactive computational fluid dynamic modeling (herein “RCFD”) to evaluate low, medium, and high values (0%, 50%, 100%) for each of these selected parameter ranges.
  • Applicant ranked those parameters by parameter importance to Unburned Hydrocarbons (UHC) (or equivalent unburnt fuel), Nitrogen Oxides (NOx), and Carbon Monoxide (CO) emissions.
  • UHC Unburned Hydrocarbons
  • NOx Nitrogen Oxides
  • CO Carbon Monoxide
  • LLNL Lawrence Livermore National Labs
  • Those methods and resulting software enabled the applicant to configure its scalable gas turbine combustor configurations so as to probably achieve less than 1 ppmvd each for UHC, NOx and CO emissions over commercial gas turbine operating conditions. This predicts emissions below the strictest California county emission requirements of 2.3 ppmvd NOx and CO without using catalysts.
  • Such very low emissions provide major advantages with typically 7% to 10% lower CapEx for commercial gas turbines operating on natural gas with emissions control using Selective Catalytic Conversion (SCR). It further promises substantially lower operating costs by eliminating ammonia delivery and associated “slip” emissions.
  • SCR Selective Catalytic Conversion
  • the techniques, configurations and methods as described herein further detail extend, and/or adapt that initial modeling RCFD modeling on methane. They likely enable extending and/or improving the methods to further using the range of conventional to sustainable fuels. E.g., to include methane, natural gas, methanol, ethanol, ammonia, cracked ammonia (herein combinations of “H2 N2, and NH3”), and hydrogen.
  • NOx formation is likely to increase as the product of (Fuel * O 2 ) and exponentially with combusting temperature.
  • Rich combustion cooled by steam and/or diluent in the upstream combusting region with residual combustion Blend region uniquely enables transitioning from rich hot upstream combustion to near stoichiometric combustion. This will likely be highly beneficial in avoiding NOx formation.
  • Fig.4F schematically shows a typical combustor axial Temperature profile with 1,570K (1397°C) outlet temperature. Such runs reduced outlet NOx (and CO) emissions on Methane to sub 1 ppmvd (parts per million by volume diluted to 15% O 2 ).
  • Fig.4F depicts an example of preliminary modeling of ammonia (NH3) combustion with air, and diluent water and steam. Temperature and emissions are depicted along a flow axis from the upstream combusting inlet CZ34 to the downstream combustor outlet at CZ4. This exploratory reactive RCFD modeling of diluted NH3 air combustion was conducted in applicant’s prior simplified scalable combustor.
  • the left axis shows the mean cross-sectional temperature
  • the right axis the outlet NOx and NH 3 emissions in ppmvd (parts per million diluted to 15% O 2 ).
  • the mean upstream combusting hot gas temperature peaks near 1,830K ( ⁇ 1,557oC) about the end of the Blend-Trim region T1.
  • an assumed combustor wall cooling rate is prescribed, reducing the combustor outlet temperature at CZ4 to a prescribed 1,527K (1,300oC) typical of a mid-range gas Turbine Inlet Temperature (TIT).
  • Cooling Combustion [0317]
  • remaining undelivered diluent may be moved from the downstream Trim region feeders T1 to be delivered up into the Blend region feeders (e.g., B1 and B2).
  • a major portion of this remaining diluent may be delivered to the upstream Blend feeder B1 to provide cooler rich (sub stoichiometric) combustion, with temperature being controlled independently of the relative local fuel to oxidant ratio Phi (or the relative local oxidant to fuel ratio Lambda).
  • part of this diluent may further be delivered further upstream into the downstream end of the combusting region, such as to delivering with fuel U7 and/or oxidant fluid X7 (or optionally diluted oxidant fluid) in the axially downstream (or last) combusting region axial 733.
  • Such diluent may further be delivered into the last two to last seven combusting regions upstream of CZ35.
  • Excess oxidant (or air) T1 may similarly be delivered in through the downstream Trim region. Such a combination of upstream diluent and downstream excess oxidant may achieve the coolest Blend region rich combustion with the least oxidant up to stoichiometric combustion.
  • ammonia may be delivered upstream under hot fuel rich (excess fuel, sub-stoichiometric oxygen) conditions (with Phi ( ⁇ ) > 1 or Lambda ⁇ 1). Upstream combusting temperatures may be increased by reducing upstream diluent. Such conditions may increase upstream ammonia cracking to hydrogen and nitrogen. Such in situ rich cracking of ammonia to hydrogen and nitrogen may facilitate downstream rich combustion, thereby reducing overall NOx formation.
  • Ammonia fuel may be delivered as Fuel F1 into this region, (and/or as diluted Fuel F2, not shown).
  • a portion Ammonia Fuel F1 may be cracked to hydrogen and nitrogen, with residual ammonia recovered from this region as cracked Fuel fluid F16.
  • This region 853 may provide multiple serpentine passages without orifices to increase (or fewer to decrease) the residence time, or to modify it.
  • Some combustor configurations may configure the temperature of transverse feeders without orifices, adjacent to the combusting region, and/or in the upstream combusting region.
  • One or more of the axial location, temperature, fuel F1 fluid flow rate, number of transverse passages, and contact duration may be adjusted sufficient to thermally crack a portion of ammonia fuel to hydrogen and nitrogen. E.g. from 2% to 98% ammonia cracking, or 5% to 60% cracking, or from 10% to 40% cracking, and/or for 15% to 25% cracking etc. Catalysts may similarly be used within transverse fluid feeders to facilitate cracking of ammonia. Such cracking may further be configured together with diluent to then form diluted fuel fluid F2 for delivery into the combustor.
  • an energetic fluid may be formed by heating one or more delivered fluids to temperatures such that the temperature and flow rate of the delivered energetic reactant and co-reactant mixture gas is sufficient to ignite the reactive fluid in the primary reaction zone.
  • Manufacturing Methods [0324] One or more of such scalable parametric combustor configurations depicted may be constructed using additive manufacturing (or “4D printing”) techniques. Such manufacturing techniques may facilitate forming the numerous oxidant fluid, fuel fluid, and diluent fluid transverse feeders with the corresponding orifices delivering fluid from the transverse feeders into the combusting chambers.
  • such scalable shell combustors may be formed in two halves with inner insulating coatings over outer structural walls. These may then be assembled and be suitably held, bonded or fastened together. In other configurations, such orifices may be formed by laser ablation, chemical etching, mechanical or fluid jet drilling, or similar material removal techniques.
  • Radial Annular Multiple Scalable Combustors may be designed to achieve ultra-clean combustion for gas turbines, combined heat and power systems, industrial heating and/or cooling, and other applications requiring ultra- clean well controlled combustion and/or similar chemical reaction.
  • walls with multiple fluid jets delivered through orifices may be configured with relatively shallow spacing between those walls to improve relative jet penetration.
  • the mass flow rates of fuel, oxidant, and diluent delivery, or any combination thereof, into an upstream combusting flow may be configured to increase reliable combustion operating range, combustion operational robustness, and/or the degree and/or uniformity of fluid mixing.
  • Fig.5A shows an end on Downstream to Upstream view of the downstream end of multiple Scalable Combustors Radially Oriented in the upstream portion of an Annular Gas Turbine Combustor 750 extending from a combusting region inlet 134 to a combusting region outlet 136 such as for use in a gas turbine combustion system.
  • one or more flame authorities 100 may be configured to supply hot igniting gas F22 into an upstream flame authority duct (ignition authority duct or pilot feeder duct) configured about the upstream inlet region 720 of a combusting system 750.
  • the upstream flame authority duct may feed the hot igniting gas F22 into the upstream region, such as from CZ31 to CZ34 of one or more combusting shells (such as are shown in perspective Fig.4B, and from the downstream view in Fig.5B and the upstream view in Fig.5C.) [0330]
  • the one or more upstream flame authorities 100 may be fed with Pilot Fuel fluid F3 comprising a fuel fluid (or first reactant fluid), a Pilot Oxidant Fluid F6 comprising an oxidant fluid (or second reactant fluid), and a Pilot Diluent Fluid F8 comprising a diluent fluid or thermal diluent.
  • some embodiments may configure a scalable combustor 730 with multiple scalable combustion sections (or combusting chambers or “fan burners”) as depicted in a downstream to upstream radial - circumferential (R- Theta) view. These may have a radial configuration of combusting chambers 730 between an inner annular duct wall 147, and an outer Pressure Vessel Wall 172, to form the radial multi-fan annular combustor 730.
  • Fig. 5C shows a radial-circumferential (R-Theta) view of multiple outwardly oriented combustion sections (or multi-fan burners).
  • FIG.5C further shows a more detailed perspective view of a combustion section 730 as portion of the radial multi-fan annular combustor 741 (as configured in Fig.5C).
  • An upstream combusting section 741 is configured between an upstream combusting fluid duct inlet transverse plane 134, and a downstream combusting fluid duct outlet transverse plane 136.
  • Fig.5B has similar detailed configuration of the radial multi-fan annular combustor 730 with outwardly oriented multi-fan burners configured along radial orientations, not shown.).
  • All or some of Fig.5 curves can be cycloidal shaped curves.
  • cycloidal curves can indeed improve flow efficiency by minimizing abrupt directional changes, reducing separation, and optimizing flow attachment. Their effectiveness is often most notable in systems where fluid needs to turn within constrained spaces or where maintaining laminar flow is advantageous.
  • These cycloidal properties can also be beneficial for fluid dynamics in applications where maintaining flow velocity and smooth directional change is beneficial.
  • Fig.5C shows an exploded outward to inward perspective view of Fig.5B, (and correspondingly for Fig. 5A).
  • An upstream igniter or flame authority 100 receives, mixes, and reacts a pilot fuel fluid F3 mixed with pilot oxidant fluid F6, with one or both fluids optionally mixed with pilot diluent fluid F8, to form a hot pilot fluid F22.
  • the hot pilot fluid F22 from upstream flame authority 100 may then be distributed to the upstream end 134 of one or more mid-fan combusting sections or burners 74 such as at plane 134, *** via an optional hot pilot duct 138.
  • One or more of the scalable combustors 732*** and 742*** may be configured and extended between a surrounding duct wall 132 *** and/or a surrounding pressure vessel 172 as described herein with respect to the circumferential annular multi-combusting chamber scalable combustor 750 as depicted in Fig. ***.
  • Radial Annular Multi-Fan *** [0337] With reference to Fig.
  • the orifice dimensions, side wall depth spacing Ld ⁇ *** ⁇ and pressure drop across the circumferential annular scalable combustor 730*** may be configured to deliver premix fluid F14 ***into fan burners at a rate sufficient to feed and react with the incoming hot pilot fluid F22 to form more hot or energetic fluid F20 without quenching the reaction within the scalable combustor.
  • the delivery rate of premix fluid F14 may similarly be configured to maintain the temperature of the reacting fluid within each fan burner above a prescribed reaction temperature quench limit.
  • One or more transverse distributions of one or more of fuel fluid delivery orifices, oxidant fluid delivery orifices, and/or diluent fluid delivery orifices may be configured to achieve one or more of a prescribed transverse composition distribution, a prescribed transverse temperature distribution, and/or a prescribed transverse velocity distribution, about one or more prescribed axial planes normal to the combusting fluid flow, between the hot pilot fluid F22 inlet at CZ34, and the combustor outlet at CZ4.
  • a plurality of transverse distributions of orifice size, spacing, and/or orientation may preferably be configured to achieve a desired change in transverse composition and/or temperature distributions in a plurality of curvilinear surfaces distributed across the streamwise flow direction within the combustor.
  • Such transverse distributions of orifices in perpendicular planes and/or transverse curvilinear surfaces may be configured at multiple locations along the streamwise flow.
  • some configurations may physically configure orifice distributions and size, and/or dynamically control fluid delivery to control the temperature T of the hot combusting gas at a radial location R in an axial plane at axial location CZ between the combustor inlet at CZ34 (as shown in Fig.5D), into an upstream combusting fuel rich region between axial locations CZ34 and CZ35.
  • some configurations may configure and/or control one or more oxidant and/or diluent fluid flows in a downstream Blend-Trim region between axial locations CZ35 and CZ39 (***).
  • Such configurations may further configure fuel, oxidant and/or diluent orifices to control fluid flows compositions, and/or temperatures in an equilibrating region from CZ39 to the combusting region outlet at CZ4.
  • Fig. 5D shows a schematic graph of combusting fluid Temperature at an axial transition location CZ35 between an upstream combusting fuel rich region and a downstream Blend-Trim region.
  • the methods described herein may be used to control a temperature T35i at the inner radius Ri relative to (such as higher than) a desired corresponding radially outer temperature T35o at the outer radius Ro.
  • Such temperature control may be achieved by adjusting the diluent to fuel ratio Omega.
  • the water to fuel mass ratio omega may be increased to reduce outlet temperatures and reduced to increase outlet temperatures.
  • Such configurations may similarly control an outer temperature T35o at the outer radius Ro to be higher than a desired corresponding downstream outlet temperature. E.g., this may accommodate outer wall cooling at outer radius Ro from the transition axial location CZ35 to the combustor outlet axial location CZ4 in the combustor outlet plane.
  • first intermediate temperature T35j at a combustor intermediate radius Rj between the inner radius Ri and outer radius Ro.
  • This first intermediate temperature T35j may be controlled relative to (such as below) one or both of the inner radial temperature T35i at the combustor inner radius Ri, and the outer radial temperature T35o at the outer radius Ro.
  • Such configurations may further control a second intermediate temperature T35k at a second intermediate radius Rk.
  • the second intermediate temperature T35k may be controlled relative to (such as below) one or both of the inner temperature T35i at inner radius Ri, and the outer radial temperature T35o at the outer radius Ro (such as shown in Fig.5D).
  • Such configurations as shown in Fig. 5E may assist in controlling one or more corresponding downstream outlet temperatures in the outlet plane at CZ4 as shown in Fig.5F. E.g., to control an outlet temperature T4j at that combustor intermediate radius Rj. Such configurations may further control temperature T35J to assist in controlling a corresponding second intermediate outlet temperature T4k at the second intermediate radius Rk (as shown in Fig.5E).
  • the first intermediate temperature T35j at a first intermediate radius Rj, and second intermediate temperature T35k at the second intermediate radius Rk may further be configured to obtain a desired intermediate temperature gradient DT35jk between that first intermediate radius Rj and that second intermediate radius Rk in the combustor axial transition plane CZ35.
  • Fig.5E shows a corresponding schematic graph of the hot gas outlet temperature T4 versus combustor radius R at an axial location CZ4 in the combustor outlet plane (or the turbine inlet plan) downstream of the equilibrating region.
  • Some configurations may control upstream fluid delivery of one or more of fuel fluid, oxidant fluid, and/or diluent fluid to control the outlet temperature T4 with a radially inner outlet temperature T4i at the inner radius Ri in the outlet plane at axial location CZ4.
  • such configurations may similarly control the outlet temperature T4 to have a radially outer outlet temperature T4o at the outer radius Ro in the outlet plane at axial location CZ4.
  • This outer temperature T4o may be configured relative to (such as higher than) the radially inner outlet temperature T4i at the inner radius Ri in the outlet plane.
  • upstream delivery of one or more of fuel fluid, oxidant fluid, and/or diluent fluid may be further varied to control a first intermediate temperature T4j at a first intermediate radius Rj, in the combustor outlet.
  • upstream fluid delivery may be configured to control a second intermediate temperature T4k at a second intermediate radius Rk in the outlet plane at CZ4.
  • one or more upstream intermediate temperatures T35j and/or T35k (with the intermediate temperature gradient DT35jk of Fig. 5D) and/or corresponding diluent and oxidant fluid delivery orifices in the Blend-Trim region.
  • upstream orifices may be configured towards achieving desired downstream outlet temperatures shown in Fig. 5E. e.g. to achieve outlet temperature T4j at a first intermediate radius Rj, and/or the second intermediate temperature T4k at the second intermediate radius Rk with the corresponding temperature gradient DT4jk between those two intermediate outlet temperatures in the combustor outlet plane at the axial location CZ4.
  • some configurations may control one or both of an inner temperature T35i at the inner radius Ri, and /or an outer temperature T35o at the outer radius Ro relative to (such as higher than) a desired corresponding downstream outlet temperature T4o such as shown in Fig. 5E.
  • Fig.5F shows a schematic graph of a hot Wall Temperature Tw versus combustor axial length Z, from an outer transition wall temperature TW35o at the transition boundary CZ35 at the downstream end of the fuel delivery region, to the outlet outer wall temperature TW4o the combustor outlet at axial outlet location CZ4.
  • such temperatures may further be adjusted to control an inner wall temperature TW4i, and an outer wall temperature TWro.
  • Such temperatures may begin at an upstream inner wall temperature TW35i, and/or outer wall temperature of TW35o at the rich/blend-trim axial boundary CZ35.
  • Such temperatures may include an intermediate inner wall temperature TW39i, and/or an outer wall temperature TW39o at the blend-Trim region outlet axially at CZ39.
  • One or more temperature distributions may be varied to a downstream outer wall temperature of TW4i at the inner wall, and/or TW4o at the outer wall, at the combustor axial outlet at CZ4.
  • Fig.5G shows a schematic graph of an axial Velocity V of combustion hot gas versus the combustor radius R, from radially inner to radially outer walls, at the combustor outlet, at the downstream axial location.
  • This hot gas configuration may be adjusted by adjusting the radial distribution of the sum of CZ4 axial orifices in the upstream combustion region. E.g., these may be adjusted to have an axial velocity V of V4i near the combustor inner radius R4i near the inner wall (axially at CZ4).
  • This mean velocity V may be increased up to a mean velocity V4j at the first intermediate radius R4j.
  • Fig.5H is a graph showing an “unrolled” section of circumferential distribution of hot gas temperature T versus combustor circumferential angle Theta for a region encompassing a first radially oriented combustor located CounterClockWise (CCW) (left side) marked Theta1. It further extends Clockwise to and similarly depicts a second radially oriented combustor located ClockWise (CW) (right side) marked Theta2.
  • CCW CounterClockWise
  • Fig.5I further shows radially inner temperatures in an upper (hotter) line between a lower fluid temperature Tsi and upper fluid inlet temperature Ti, at a combustor inner radius Ri, marked “At Ri”.
  • Fig.5I similarly shows corresponding radially outer fluid temperatures between Tso and To versus circumferential angle Theta near or at a combustor outer radius Ro, marked “At Ro”.
  • CCW CounterClockWise
  • Fig.5I similarly shows a cooled counterclockwise (CCW) first combustion inner section at R1 centered at Theta1I. This covers a circumferential width of Delta Theta 1 (1) from Theta1WI to Theta1WO. It shows a second combustion inner section displaced clockwise from the first inner section, and centered at Theta2I from a counterclockwise angle Theta2WI to a clockwise angle Theta2CI.
  • Fig.5I Graph of hot gas temperature T versus combustor circumferential angle Theta, with temperatures between Ts and Ti, at inner radius Ri, and at outer radius Ro, with a heated counterclockwise first combustion section Theta1 and a second clockwise combustion section Theta2.
  • Fig.5J Graph of hot gas velocity versus combustor circumferential angle Theta, between velocities Vs and V1, for values at inner radius Ri, and at outer radius Ro, with a cooled counterclockwise first combustion section at Theta1 and a clockwise second combustion section at Theta2.
  • *** [0362] Combustors Radially Oriented in the inlet of an Annular Gas Turbine Combustor.
  • *** Scalable Omega Combustor [0364] One or more curves ranging from cycloidal to hyperbolic to parabolic may be used for portions of the diffuser, combustor, and/or transition zone walls.
  • the Scalable Combustor may further be axially configured into an Omega shaped combustor as depicted in Fig.5K in the Radial-Axial (R-Z) Cross-Section Elevation View.
  • This Scalable Combustor extends radially outward from the Turbine Axis, herein a Scalable Omega Combustor 707 (or Omega Combustor).
  • Oxidant fluid flow WX34 may be delivered through an upstream diffuser into a generally axially oriented combusting region inlet CZ31 to the Scalable Omega Combustor (per the terminology of Fig.4A and Fig.4B).
  • Oxidant Fluid (or Second Fluid) F4 may be delivered from an upstream compressor 407 (CPR) and redirected radially outwardly (+R) and then outwardly upstream (+R -Z) through an outwardly reversing duct into scalable combusting and trim-blend region 704 between upstream combustor plane CZ34 and downstream combustor plane CZ39 (similarly to that depicted in Fig. 4A and Fig. 4B).
  • Oxidant, fuel and diluent fluids may be delivered into the Combusting Region 704 (similarly to that shown schematically in Fig.4A, Fig.4B, and to other Figures and disclosure herein referencing Combusting Region 704.
  • Hot combusting fluid may then be delivered from Combusting Region 704 into Equilibrating Region 900 within an outer and inner pressure vessel wall 172.
  • This pressure vessel wall 172 may be protected by a thermal barrier coating 34.
  • Forming such an Omega combustor may increase the combusting fluid residence time for combustion between the shortened axial distance from CZ31 to CZ4 along the Turbine Axis. This may beneficially increases the ratio of Equilibrating volume per axial length.
  • Fluid Premixing Chambers Combustion may be improved and/or emissions reduced by premixing one or more of fuel, oxidant, and diluent fluids prior to delivery into the upstream combusting and/or downstream Blend-Trim regions such as in Fig. 5L shown in a Radial-Axial Plan View.
  • Fig. 5L depicts Premixing Chambers configured in the Scalable Combustor to Premix one or more of Fuel fluid F2, Oxidant fluid F5, and Diluent fluids F7.
  • Fig.5L shows a detailed circumferentially inward-looking Plan View in the Radial-Axial (R-Z) plane.
  • R Theta perforated transversely extended fuel feeder walls 842 and oxidant feeder walls 844 are in contrast with continuous radial circumferential fuel feeder walls and oxidant feeder walls such as shown in Fig.4G and Fig.4I.
  • a plurality of radial – circumferentially extending (R-Theta) walls 842 may be used to form one or more transverse fuel fluid feeder passages 751.
  • Such fuel fluid feeders 751 may deliver fuel fluid F2 radially outward from fuel feeder manifold 770 such as bounded by radially inner manifold wall 253.
  • a plurality of radial – circumferentially extending (R-Theta) walls 844 (such as between upstream bound CZ34 and downstream bound CZ35) may be used to form one or more transverse oxidant fluid feeder passages 761.
  • Such oxidant fluid feeder passages 761 may deliver oxidant fluid F5 radially inward from an outer oxidant fluid feeder manifold 780 such as bounded by manifold wall 250.
  • Such radial-circumferential extending feeder walls 842 and 844 may be used to form one or more premixing regions radially bounded by radially inner end walls 828 and radially outer end walls 826. Such premixing regions may be formed into multiple smaller blended feeder premixing chambers 847 by separating them radially with axial- circumferential blended feeder divider walls 846 extending axially between radial- circumferential extending feeder walls 842 and 844.
  • One or more fuel fluid delivery orifices 81 may be configured between fuel fluid feeder 751 and premixing chambers 847. Such fuel fluid orifices 81 may deliver fuel fluid F2 into multiple fluid premixing chambers 847.
  • One or more premixed reactive fluid orifices 87 may be configured in the circumferential – radial (Theta – R) combusting region walls to deliver premixed fuel rich reactive fluid mixture F12 from such premixing chamber(s) into the circumferentially adjacent combusting region. The diameter of such premixed reactive fluid orifices 87 may be constrained to avoid flashback from the combusting region back into such premixing chambers 847 under operating conditions with applicable fuels.
  • the number of premixed reactive fluid orifices 87 may be configured within a prescribed range to provide a prescribed range of cumulative premixed fluid delivery area to deliver into the adjacent combusting chamber the amount of premixed rich fluid F12 formed per such premixing regions formed between the fuel feeder 751 and oxidant feeder 761.
  • premixed reactive fluid orifices 87 and/or the related premixed fluid orifice delivery area may be configured relative to the premixed fluid formed to constrain one of a pressure drop across said premixing orifices to be below a prescribed premixing pressure drop, and a ratio of premixed fluid delivery distance per axial flow distance relative to the local combusting fluid axial velocity within the combusting region.
  • Premixing Blend-Trim Feeder As described above for reactive premixing chambers, non-reactive dilutive premixing chambers 851 may be configured in the Blend-Trim region downstream of CZ35.
  • Oxidative Fluid F5 may be delivered oxidative orifices 83 into premixing dilutive chambers 851.
  • Dilutive fluid F7 may similarly be fed through dilutive orifices 84 into such dilutive premixing chambers 851.
  • Oxidative Fluid F5 and Dilutive Fluid F7 may be premixed with in such premixing chambers 851 and delivered through premixed dilutive orifices 852 into the Blend Trim region downstream of the Combusting to Blend Trim boundary CZ35.
  • Controllable Flexible Scalable Ignition Authority [0377] Referring to Fig. 5M depicts the outer fluid delivery region of a Controllable Flexible Scalable Ignition Authority 100, (or Pilot Authority).
  • Igniter or Pilot Fuel fluid F3 may be delivered into a fuel fluid delivery feeder.
  • a fluid delivery feeders may be semi-circular having an Inner Fuel Feeder Radius RFI and an Outer Fuel Feeder Radius RFO.
  • One or more fuel Fluid Orifices 81 may be distributed about the upper fluid delivery feeder in an Ignition Authority 100.
  • Fig.5M further depicts the Ignition Authority 100 as having an oXidant (or air) fluid delivery inlet port feeding an oxidant fluid delivery feeder axially upstream at CZ31.
  • oxidant fluid may be delivered through an outer delivery feeders such as depicted.
  • This outer oXidant pilot feeder may be semi-circular having an Inner Oxidant Outer Feeder Inner Radius RXOI (similar to the outer Fuel Feeder Radius (RFO), and an Outer Oxidant Feeder Outer Radius RXOO.
  • Such oxidant fluid may similarly be delivered through an inner Oxidant delivery feeder.
  • Such an inner oXidant pilot fluid feeder may be semi-circular having an Inner Oxidant Feeder Outer Radius RXIO.
  • one or more Oxidant Fluid Orifices 82 may be distributed about the upper oxidant fluid Outer delivery feeder in an Ignition Authority 100.
  • Fig.5N depicts a schematic Perspective View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices above an intermediate or middle Combusting Region.
  • Fig.5O through Fig.5S show plan views of five cross-sections of such Ignition Authorities 100.
  • Fig.5O through Fig.5S show plan views of five cross-sections of such Ignition Authorities 100.
  • FIG. 5O shows a Schematic Plan View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle or central Combusting Region, similar to Fig.5M.
  • Fig. 5P depicts Fuel Orifices 81 and Oxidant Orifices 82 in a Plan View of Ignition Authority Upper Inner Wall to the Ignition Authority’s central combusting chamber.
  • Fig.5Q Depicts a cross-section Plan View through Igniter Authority Mid-Section along the normal to the Ignition Authority outer and inner surfaces.
  • FIG. 5R depicts Fuel Orifices 81 and Oxidant Orifices 82 in a Plan View of Ignition Authority Lower Inner Wall to the Ignition Authority’s central combusting chamber.
  • Fig. 5S shows a Schematic Plan View of an Ignition Authority Inner Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the central Combusting Region, similar to Fig.5M and Fig.5O.
  • Fig.5T depicts a Close-up schematic view of an Igniter in the Wall of the central Pilot Combusting Region. Such igniters may have two electrodes 124 connected to an ignition source 126.
  • Fig.5U depicts methods for combustor wall cooling which may utilize a diluent, or provide for ammonia cracking, or combinations thereof.
  • this Fig. 5U depicts a Radial-Axial (R-Z) Cross-Section of an outer Combustor Wall such as between the Combusting region or Blend-Trim region and/or the Equilibrating region or downstream diffuser region.
  • R-Z Radial-Axial
  • Fig.5V Radial Inner to Outer Temperature Profile (T vs R) of Equilibrating Zone Flow Temperature Upstream at CZ39 and Downstream at CZ4. ⁇
  • Design and Emergency Power [0393] Fig.6A “Power Versus Temperature Graph of Brayton Cycle and VAST Cycles” schematically displays the drastic reduction in typical Brayton Design Power 650 with increasing ambient Compressor Inlet Temperature of a gas turbine operating in a Brayton Cycle (or “Simple Cycle”). E.g., dropping from ⁇ 120% of design power at -17.8°C (0°F) (such as in winter), down to ⁇ 75% of design power at 60°C (140°F) (such as in Kuwait in summer).
  • a Brayton Emergency Power 652 in a Brayton or Simple Cycle Gas Turbine may typically rise to about 110% of design Brayton or Simple Cycle Power at a given ambient temperature, and likely less than 120% of design Brayton Cycle Power.
  • Such drastic 25% drop in Brayton cycle design peaking power generating capacity when warming from 15°C to 60°C (59°F to 140°F) typically raises dangers of substantially higher blackout probabilities during the strong increase in air condition power loads hot season heat waves. This is particularly dangerous in equatorial regions and in southern US States.
  • Fig.6A depicts how the gas turbine operating in a simple VAST Cycle (or VASTIG Cycle) may have a level VAST Design Power 640 with increasing ambient temperature.
  • VAST Design Power 640 and VAST Emergency Power 464 may generate 55% to 65% more power for the same gas turbine expander by controlling combusting temperature using recycled steam and/or hot water, over such a temperature range as from -18 °C to 60°C (0°F to 140°F).
  • Fig.6A depicts how the VAST Cycle (or VASTIG Cycle) may increase the design Simple (Brayton) Cycle gas turbine design power 650 from 100 MW up to a VAST Cycle Design Power 640 to generate ⁇ 155 MW of power for the same expander together with a smaller compressor 407 (CPR), and heat recovery systems at standard ISO conditions (15°C, 1 Atm, 60% RH).
  • VAST Cycle or VASTIG Cycle
  • CPR compressor 407
  • the VAST Cycle may increase such a Simple (Brayton) Cycle Emergency Power 652 from ⁇ 110 MW at ISO conditions to a VAST Cycle Emergency Power 646 of ⁇ 170 MW assuming a higher operating temperature for the same allowable air flow within a compressor surge margin of the compressor 407 (CPR), with a generator 620 sized for that higher power, for the same ISO reference expander inlet air conditions.
  • Fig.6A depicts an option of the VAST Cycle Upper Design Power 642 to leverage the declining oxidant or air flow with increasing ambient temperature by cooling the oxidant or air flow with increasing thermal diluent and higher exhaust heat recovery up to the maximum ambient design temperature (e.g., 60°C or 140°F).
  • Such increased cooling by higher diluent would enable raising the VAST Upper Emergency Power 648 to ⁇ 185 MW using the same expander in a VASTIG Cycle operating at maximum ambient design temperature such as 60°C (or 140°F).
  • maximum ambient design temperature such as 60°C (or 140°F).
  • This configuration sizes the generator for ⁇ 185 MWe to deliver that VAST Upper Emergency Power 648 output assuming a maximum 60°C ambient temperature.
  • This increases maximum emergency electrical power by ⁇ 125% above the 82 MW in the Brayton Emergency Power (Simple Cycle) 652 at the same maximum ambient air temperature of 60°C, 140°F.
  • FIG.6A further depicts how the VAST Design Power may be held constant independent of temperature over that -18°C to 60°C (0°F to 140°F) with the generator sized for the highest (or coldest) temperature power.
  • Fig.6A further depicts increasing the VAST Upper Design Power by 6.5% (from 155 MW at -17.8°C (0°F) up to about 165 MW at 60°C (140°F) for the same size expander and with the generator sized for this Upper Design Power (or Upper Emergency Power) at the maximum ambient temperature. This would enable the VAST power system to generate more power to supply higher summer peaking power demand.
  • Fig. 6A schematically depicts a potential declining lower bound for a VAST Power System nominally distinguishing its expected power performance versus temperature from other power cycles, including degradation due to operating and environmental factors. Controller Subsystems [0404] Fig.
  • FIG. 6B depicts a high-level schematic of a Control System 588 having one or more Controllers which may comprise one or more Processors 589 in communication with one or more Memory systems 591.
  • the one or more Processors 589 and one or more Memory systems 591 in the Control System 588 may further be configured or described as comprising one or more Controller Sub-Systems.
  • Each of the Controller Sub-Systems may further comprise one or more processors 589 in communications with one or more memory systems 591.
  • One of the Control System 588, and/or each of the Controller Sub-Systems may comprise an Energy Storage System 630, and optionally an Energy Storage Controller 618.
  • the Control System B588 may comprise a Pilot Controller 619A and a Combustor Controller 619B with one or both comprising Processors 589 and one or more memory systems 591. These may respectively control the operations of the Ignition Authority (Pilot), and the Combusting System.
  • the overall Control System 588 and/or each of the Controller Sub-Systems may be configured to interact hierarchically, cooperatively, and/or relatively independently and to communicate accordingly. Further processor systems 589, memory systems 591, energy storage systems 630, and/or energy storage controllers 618 may be configured to provide one or more degrees system redundancy to achieve greater system reliability.
  • Controller Sub-Systems may include functions of a Mass Controller 614, and a Thermal Controller 615.
  • the Control System may further comprise one or both of a Power Controller 616, an Emissions Controller 617, and/or an Energy Storage Controller 618.
  • One or more of the controller Sub-Systems may further have separate processors, memory systems, communications systems, and/or energy storage to facilitate operations, maintenance, and/or reliability.
  • the Mass Controller 614 portion of Fig.6B may be configured to control one or more flows of fuel comprising one or more of Gaseous Hydrocarbons such as Methane (CH4), Ethane (C2H6), Propane (C3H8), Liquid Hydrocarbons such as Diesel Fuel, Jet Fuel JP5, Heavy Crude, Bitumen, or fractions thereof, Alcohols such as Methanol, Ethanol, and Butanol, and Renewable or Sustainable Fuels such as Hydrogen (H2), and Ammonia (NH3).
  • Gaseous Hydrocarbons such as Methane (CH4), Ethane (C2H6), Propane (C3H8)
  • Liquid Hydrocarbons such as Diesel Fuel, Jet Fuel JP5, Heavy Crude, Bitumen, or fractions thereof
  • Alcohols such as Methanol, Ethanol, and Butanol
  • Renewable or Sustainable Fuels such as Hydrogen (H2), and Ammonia (NH3).
  • the Mass Controller 614 may control one or more input Oxidant flows comprising one or more of Oxygen, Air, Liquid Air, or mixtures of Oxygen and diluents comprising one or more of Nitrogen, Argon, Carbon Dioxide and/or other non-reactive or low reactive gases.
  • the Mass Controller 614 may control the formation and flow of one or more output fluids such as the Hot Gas flowing out of a VAST Combustor or Flare, and/or in and/or out of a Gas Turbine Expander.
  • the Mass Controller 614 of Fig.6B may further control one or more diluent flows such as Water, Steam, Ice slurry, excess Oxidant, excess Air, Nitrogen, liquid Nitrogen, Carbon Dioxide, Liquid Carbon Dioxide, Supercritical CO2, Argon, Helium, and/or other inert gases.
  • the Mass Controller 614 of Fig.6B may further control one or more Reactant flows such as Ammonia, or Nitrogen Oxides (NOx) (such as to react with excess Nitrogen Oxides and/or Ammonia.) to an Emissions Controller 617.
  • the Mass Controller 614 of Fig.6B may control formation and flows of one or more flows of Hot Gas, such as from one or more flame authorities into one or more combusting sections, blend regions, or trim sections, thus forming a hot gas.
  • the Mass Controller 614 of Fig.6B may control flows of a portion of Hot gas to a Thermal Controller Sub-System which in turn controls formation and direction of Steam, Hot Water, (and/or Hot Gas, CO 2 etc.), to an End Use such as Industrial applications.
  • the Mass Controller 614 and/or Thermal Controller 615 may in turn control the Gas Composition, and/or Gas Temperature of such a hot fluid formed.
  • Thermal Controller [0412]
  • the Thermal Controller 615 may control flows of Hot Gas such as controlling fuel Ignition, combustion, and delivery the gases to form steam and/or hot water and their delivery to End Use applications.
  • the Thermal Controller 615 may further control one or more of Gas Composition and/or Gas temperature.
  • the Thermal Controller 615 may receive feedback from one or both of the Power Grid and/or Power Use.
  • the Mass Controller 614 may receive feedback from one or both of the Power Grid and Power Use.
  • Power Controller [0413]
  • the Control System 588 of Fig.6B and Fig.6C may comprise a Power Controller 616 that may control one or both of electrical power generated and delivered to a Power Grid, and/or to a Power Use such as in a local or industrial power application such as is depicted in Fig.6C.
  • the Power Controller 616 may comprise a Processor 589 and Memory 591 in communication with the Control System 588.
  • Power Controller 616 of Fig.6B and Fig.6C may control one or more of power flows, including one or more of turbine shaft mechanical power and/or electrical power from a Generator 620. This may include one or more of generator Voltage (V), Current Amps (A), shaft rotational speed Omega S ( ⁇ S), Generator rotational speed or frequency Omega G ( ⁇ G), Generator output Power frequency Omega P ( ⁇ P), and the Generator Phase angle Omega Phi ( ⁇ ). Power Controller 616 may further receive feedback from one or both of the Power Grid and/or Power Use.
  • Emissions Controller [0415] Per Fig. 6B and Fig. 6C, the Control System 588 may comprise an Emissions Controller 617 which may have a Processor in communication 589with Memory 591.
  • Emissions Controller 617 may control one or more of formation or discharge of Nitrogen Oxides (NOx), Ammonia (NH 3 ), Carbon Monoxide (CO), Unburned Fuel (UF) (including any Unburned Hydrocarbon).
  • an Emissions Treater 471 may be positioned in the gas turbine expander outlet flow F24, such as between the Steam Generator 472, and the Economizer 474.
  • Such an Emissions Treater 471 may include mixing or spraying fluid (such as water or carbon dioxide) comprising one of ammonia (NH3) and/or nitrogen oxides (NOx).
  • Such treatment by ammonia (NH3) in Emissions Treater 471 may be used to reduce residual NOx emissions to below required emission standards.
  • Emissions Treater 471 may be used to spray fluid comprising nitrogen oxides (NOx) to react with and reduce residual excess ammonia (NH3) fuel to below prescribed ammonia emissions levels.
  • NOx nitrogen oxides
  • NH3 residual excess ammonia
  • each of the Mass Controller 614, Thermal Controller 615, Power Controller 616, and Emissions Controller 617 may comprise separate independently controllable sections of an Ignition Controller, and a Combustor Controller.
  • Energy Storage Controller [0418]
  • Control System 588 may comprise an Energy Storage Controller 618 which may comprise a Processor 589 in communication with Memory 591.
  • the Energy Storage Controller 618 may provide reliable and/or backup power to one or more of the Control System 588, the Mass Controller 614, the Thermal Controller 615, the Power Controller 616, and/or the Emissions Controller 617, as well as to the Energy Storage Controller 618 itself.
  • the Energy Storage Controller 618 may further control Energy Storage 630 for the Gas Turbine Energy System (such as shown in Fig.4A).
  • Such Energy Storage 630 may provide energy for black start capabilities, and to buffer power system fluctuations.
  • the Energy Storage 630 may comprise sufficient energy storage to sustain the VAST Power System with Thermal Power and/or Power Generation to operate at full power for two months to four months.
  • Fig. 6C depicts major components of the Control System 588 including one or more of Fuel Controller 592, Oxidant (O 2 /Air) Controller 594, Water Controller 597, Steam Controller 598, Trim Controller, 599 and/or Generator Controller 622.
  • the Control System 588 may comprise a processor 589 and/or memory 591.
  • a processor 589 and/or memory 591 may be included in one or more of each of these Controllers 592, 594, 597, 598, 599 and/or 622.
  • the Fuel Controller 592 may control one or more of inlet Fuel Flow Control 233A, Fuel Pump P1, and/or Pilot/Combustor Fuel Flow Control 233B to deliver pilot fuel fluid F3. Pilot/Combustor Fuel Flow control 223B may similarly control primary fuel fluid F2 to the Combustor 704.
  • Oxidant (O2/Air) Fluid Control 594 may control one or more inlet oxidant valves 232 to vary delivery of oxidant fluid F4 into the Compressor 407 (CPR) such as by compressor inlet control vanes.
  • Diluent or Water control 597 may control water diluent valve 236 to regulate the flow of water condensed from combustion hot gas F20 via Condenser 480 and to deliver it back into the combustion / power system, or to discharge a portion of excess net recovered water for potable water or for other use.
  • Water Control 597 may regulate diluent or water pump P2 to pressurize recovered diluent/water and deliver it to the Economizer 474 to condense water vapor from the combustion gas exiting the expander exhaust gas steam heat exchanger or Once Thru Steam Generator 472.
  • Water Control 597 may control water diluent valve 239 to control one or more of water diluent delivery into the inlet of Compressor 407 (CPR), and/or within Compressor 407 itself at one or more locations such as through orifices in stationary vanes and/or orifices in rotating blades.
  • the Power or Generator Controller 622 may control one or more of gas turbine shaft speed Omega ( ⁇ S), generator speed ( ⁇ G), and/or generated power frequency Omega ( ⁇ P). Power Controller may further control one or more of shaft power, generator Voltage (V), generator current (A), and power phase angle Phi ( ⁇ ).
  • the Power Controller may further control individual power generation phase angles Phi1 ( ⁇ 1), Phi2 ( ⁇ 2), and Phi3 ( ⁇ 3), not shown).
  • the Power or Generator Controller 622 may further control one or more of power from a Generator 620 delivered to a Power Grid, to a non-grid Power Use, and/or to an Energy Storage system 630, such as a black start power system, battery storage, thermal storage, hydro-power storage, and/or compressed gas storage.
  • Control System Sensors [0428] Fig. 6D depicts a Schematic Graph of Control System Sensors and Actuators.
  • the Compressor 407 may sense and regulate fluid properties to one or more of the Compressor 407 (CPR), the Combustor 704, the Expander 440, the Steam Generator, such as a Once Through Steam Generator (OTSG) 472, an Economizer 474, and a Condenser 480.
  • the Compressor 407 and Expander 440 may be connected by a shaft to the Generator 620 to generate three phase (or single phase) power.
  • Fuel Sensors [0429] Per Fig.6D, and Fig.6C, the fuel delivery system may comprise delivering fuel F2 to a fuel pump (or first pump) P1 monitored with a pilot fuel speed sensor SF ⁇ .
  • the properties of fuel fluid F2 pressurized by Pump P1 may be measured by fuel pressure sensor SFP, fuel temperature Sensor SFT and Fuel Flow Sensor SFF.
  • the pressurized Fuel F2 a may be controlled by a two-way fuel valve or splitter SXF to deliver a portion as Pilot Fuel F3 into the upstream Pilot 100, and as Fuel Fluid F2 into the Combustor region 704.
  • Delivery of Pilot Fuel F3 into upstream region CZ33 may be monitored by a Pilot Fuel mass flow sensor SFF33, a Pilot Fuel Pressure Sensor SFP33, and/or a Pilot Fuel Temperature Sensor SFT33.
  • Pilot Fuel Pump speed may monitor fuel delivery to the fuel ST32 ***??? pump P1.
  • a speed sensor S ⁇ P1 may monitor the speed of Fuel Pump P1 delivering Fuel Fluid to a control valve *** to deliver pilot fuel F** to the Pilot, and optionally combustor fuel F*** to the Pilot and/or the Combustor.
  • Combustor Fuel Sensors [0433] Control of the Combustor 704 may similarly utilize one or more of the First fuel Pump P1, with Fuel Pump 2 Speed Sensor S ⁇ F34, Fuel *** 233B for Fuel Mass Flow sensor SWF34, Fuel Pressure Sensor SFP34, and/or Fuel Temperature sensor SFT34-5, Combustor Diluent Water Flow Sensors [0434] Control of the Combustor 704 may further utilize one or more of a liquid diluent or water pump P2, a liquid diluent or Water Mass Flow Sensor SW ⁇ 34, a liquid diluent or Water Pressure Sensor SWP34, and liquid diluent or Water Temperature Sensor SWT34-5.
  • the power generation system may comprise a common Compressor - Expander – Generator drive shaft monitored by a Rotational speed Sensor S ⁇ R,
  • the Power generated by the Generator 620 may be monitored by a Power Frequency Sensor S ⁇ P, a Power Phase Sensor S ⁇ P, a System Voltage sensor SV, and Power Current Sensor SA. These may further be differentiated with Voltage, Current, and Phase of each of three power generation phases (not shown). Where the Compressor 407, Expander 440, and/or Generator 620 are rotated at different rates, the individual shaft speeds may be monitored (not shown). Preheating Turbine Pilots, Combustors, and Expanders.
  • the power generation system may comprise a Condenser 480 to recover net cooling diluent liquid water from the Expander discharge after heat recovery in the Once Through Steam Generator and Economizer.
  • the gaseous fluid flow out of the Flue Exhaust discharged from the Condenser may be monitored by one or more of an Exhaust Temperature Sensor STX, an Exhaust Pressure Sensor SPX, and an Exhaust Humidity Sensor SHX.
  • the condensed liquid flow recovered from the Condenser 480 may be controlled by valve 236.
  • Mass flow of diluent required within the power cycle is returned via flow F7 to pump P2 to feed the Economizer 474 and thence into the Steam Generator 472 and the Combustor 704. Cooling mass flow may further be directed to pump P3 to feed and cool the Compressor 407 via flow F***.
  • Mass flow of excess condensed liquid diluent such as liquid water discharge monitored, by discharged Exhaust Water Temperature Sensor SWT8, discharged Exhaust Water Pressure Sensor SWP8.
  • Vaporized diluent F188 delivered to outside thermal use such as steam for industrial heat, may be condensed, recovered, cleaned as needed, and recycled via diluent fluid flow F*** back into the power system via mixing valve 236.
  • Recycled condensed diluent mass flow may be monitored by liquid Water mass flow sensor to the Economizer 474 SWF.
  • Economizer Sensors [0438] Per Fig. 6D, the inlet diluent flow F2 into the Economizer via diluent or water Pump P2 may be monitored by one or more of a pump speed (Omega) sensor SW ⁇ , a diluent or water mass flow (W) Pressure Sensor SWP, a diluent or Water Temperature flow Sensor SWT, [0439] Economizer discharge flow out of the Economizer may be monitored by Temperature Sensor ST7. Water mass flow resolution and accuracy may be increased by use of a high resolution optical encoder.
  • Fig. 6E discloses system operational flexibility of the novel embodiments and control methods disclosed. These embodiments and methods include multiple low temperature and high temperature control methods. Exemplary embodiments exhibit novel selected ranges of preheating and operating options in VAST Cycle gas turbine systems. [0441] Such embodiments depicted Fig. 6E include various sequential actions to transition from a cold start at time Tau Zero ( ⁇ 0) to starting power generation about Tau Eleven ( ⁇ 11). Such depictions further exemplify various operating power embodiments from Tau Eleven ( ⁇ 11) to Tau Twenty-One ( ⁇ 21).
  • TIT Turbine Inlet Temperatures
  • Such embodiments may control power generation over multiple power levels. E.g., as from Power level One to Power level Five (P1-P5).
  • P1-P5 Power level One to Power level Five
  • Such power operation may be followed by various shutdown operations from Tau Twenty-One ( ⁇ 21) to Tau Twenty-Five ( ⁇ 25). These show Pilot Outlet Temperatures (T34) at the inlet to the combusting region inlet at upstream axial location CZ34. They further show combustor outlet / expander inlet temperature T4 at combustor outlet / expander inlet axially at CZ4.
  • T34 Pilot Outlet Temperatures
  • P1 Power One
  • P3 Design power P3 at Tau 15 ( ⁇ 15).
  • P4A and P4B power generation may be configured and controlled as shown in P4A and P4B for according to grid need to achieve higher peaking power, or maximum emergency peak power as needed as discussed as follows.
  • a gas turbine compressor may be rotated about its axis by one or more of exciting the generator to operate as a motor, using a separate starter motor, and/or a fuel driven engine, with mechanical, magnetic, electromechanical, hydraulic and/or gaseous power transmission, to rotate the expander and generator. (This may similarly use discharging compressed air through the compressor or through a hydraulic or pneumatic motor). Such operations may be conducted from time Tau One ( ⁇ 1) to Tau Two ( ⁇ 2), and from stationary up to a speed Omega R ( ⁇ R).
  • oxidant fluid such as air
  • startup steps may follow industry purging or fluid flushing standards to prevent explosions, such as used for gas turbines or boilers.
  • Fig.6E, Fig.6F, (and Fig.6G) such system preheating may be used with a stationary rotor, or with a prescribed rate of mechanical or electrical system rotation during preheating. Such system preheating rotation may be controlled over a prescribed rotational rate range.
  • the rotational rate may be between 0.001 Hz and 45 Hz (0.06 RPM and 2,700 RPM), between 0.002 Hz and 20 Hz, (0.12 RPM and 1,200 RPM), between 0.02 Hz and 10 Hz (1.2 RPM and 600 RPM), between 0.06 Hz and 5 Hz (3.6 RPM and 300 RPM), between 0.1 Hz and 3 Hz (6 RPM and 180 RPM), between 0.2 Hz and 1.5 Hz (12 RPM and 90 RPM), and/or between 0.3 Hz and 0.8 Hz (24 RPM and 48 RPM).
  • Other ranges in system rotation rates may similarly be used for such gas turbine preheating.
  • pilot fuel fluid, pilot oxidant fluid, and pilot diluent fluid may be provided to one or more upstream multifluid flame authorities (or pilot lights) 100.
  • a pilot blower and/or pressurized oxidant storage may alternatively be used to supply oxidant to the pilot during startup (not shown).
  • this flame authority startup operation may ignite the mixture of Ignition Authority (pilot) fuel fluid, and Ignition Authority (pilot) oxidant fluid and pilot diluent fluid in the flame authorities 100 to generate stable low emission flames at Tau Three ( ⁇ 3).
  • pilot outlet / combusting region(s) may generate pilot fluid and deliver it to the combustor inlet at temperature T34A.
  • thermal diluent fluid may be delivered to flame authorities 100 to cool and control the pilot combusting fluids.
  • combinations of oxidant fluid, fuel fluid and diluent fluid may control the flame authority (pilot) combusting fluids to desired pilot fluid temperatures T34A at the flame authority outlet CZ34, such as between 600°C and 1300°C.
  • Such diluted flame authority operation may control pilot NOx and CO emissions to below 1 ppmvd.
  • the flame authority 100 delivered to CZ34 may be used to ignite mixtures of fuel, oxidant and optionally diluent in the combustor and to preheat the combustor.
  • One or more of fuel fluid, oxidant fluid and/or diluent fluid may be delivered to the combustor in multiple axial and transverse locations.
  • Thermal diluent fluid may be delivered to cool and control initial warming fluid temperatures within a prescribed range, and to achieve a prescribed rate of fluid warming.
  • This warming fluid may be delivered to and through a plurality of combusting and equilibrating regions and into the turbine expander at CZ4.
  • initial warming fluid may be formed by combusting and cooling combusting gases for delivery at a temperature T34A to T34B within a range such as between 0°C to 1000°C. e.g., in Fig.6E from time Tau Three A ( ⁇ 3A) to time Tau Five ( ⁇ 5), and/or from time Tau Three A ( ⁇ 3A) to time Tau Six ( ⁇ 6).
  • Such preliminary flame authority fluid deliver temperature T4A may be selected as within 20°C to 700°C, or 30°C to 400°C, or within 40°C to 200°C, or 50°C to 100°C, etc. In other configurations, the flame authority fluid delivery temperature T4A may be configured to be within 500°C to 1800°C, or 600°C to 1600°C, or within 800°C to 1400°C, or within 1000°C to 1200°C, etc.
  • the flame authority fluid delivery temperature T4A may similarly be configured to be within 700°C to 1,500°C, or between 800°C and 1,300°C, or within 900°C to 1,200°C, or within 1000°C to 1,100°C, or between 1,200°C to 1,400°C etc.
  • Controlling Thermal Warmup Ramp Rates [0452] Referring to Fig. 6E and Fig. 6F, in such initial warming from Start to Standby times, warming fluid (or multifluid pilot fluid) may be delivered while slowly rotating the gas turbine expander. Such slow warmup system rotation may be achieved by mechanical, hydraulic, pheumatic, and/or electrical power etc.
  • the warming rate may be ramped up at one or more prescribed temperature rise rates to achieve downstream combustor wall, expander stator, blade, and/or expander wall preheating rate(s).
  • Preheating Rate to Standby Operating Temperatures [0453]
  • Fig.6F depicts preheating the VAST gas turbine to hot Standby Operating conditions typical of gas turbine operating temperatures. E.g., such Standby Operating temperatures may require stator and/or blade cooling, and/or combustor or turbine wall cooling.
  • Fig. 6F depicts combustor outlet temperature / Turbine Inlet Temperature T4 being warmed from ambient temperature at Tau 4 ( ⁇ 4) up to Turbine Inlet operating temperatures of T4D at Tau Seven B ( ⁇ 7B).
  • Fig.6E depict preheating the VAST gas turbine to a nominal heated combustor and expander temperature without cooling, such as from 30°C to 1,100°C, between from time Tau Five ( ⁇ 5) to time Tau Six ( ⁇ 6).
  • Such warming fluid may raise the combustor outlet temperature T4A, (in Fig.6E without cooling) at various selected temperature rise rates, such as depicted from a start at time Tau Four ( ⁇ 4) up to time Tau Seven A ( ⁇ 7A) in Fig.6, Similarly warming fluid to combustor outlet temperature T4B in Fig.
  • the Flame authorities 100 may have multiple fuel and oxidant orifices. E.g., three fuel orifice and six oxidant orifices are shown in Fig.5M. A similar configuration may further be placed on the opposite side of the ignition authority. Fuel, oxidant and diluent fluid may be delivered to one or both sides of each ignition authority.
  • the number of flame authorities 100 may be controlled to achieve the prescribed rate of preheating.
  • other ranges of fluid igniters may similarly be prescribed, such as between 1 and 16 fluid igniters, or between 2 and 8 fluid igniters, or between 3 and 6 fluid igniters.
  • Combustor thermal ramp rates may be configured within a range of 10°C/minute to 10,000°C/min, or within 20°C/min to 2,000°C/min, or within 30°C/min to 500°C/min, or within 40°C/min to 250°C/min or within 50°C/min to 100°C/min etc.
  • Such Standby operation may be configured to preheat the combustion outlet temperature or Turbine Inlet Temperature (TIT) to selected temperatures.
  • TIT Turbine Inlet Temperature
  • combustor outlet temperature or Turbine Inlet Temperature (TIT) may be warmed from ambient temperature at time Tau 4 ( ⁇ 4) up to an operating Turbine Inlet Temperature of T4D at time Tau Seven B ( ⁇ 7B). Such heating may then be reduced maintain such TIT at T4D under Standby operation.
  • Such Standby temperatures T4D may be controlled to temperatures requiring blade cooling, such as between 1100°C and 1800°C, or between 1200°C and 1600°C, or between 1300°C and 1500°C, or between 1350°C and 1450°C.
  • Other preheated standby temperature ranges may similarly be selected, such as to combustion outlet or Turbine Inlet Temperatures (TIT) between 1200°C and 1500°C, or to between 1300°C and 1400°C.
  • TIT combustion outlet or Turbine Inlet Temperatures
  • a low flame authority combusting temperature may be selected for the upstream flame authority 100 from time period from Tau Three A ( ⁇ 3A) to time Tau Five ( ⁇ 5), such as 650 deg C.
  • the Combustor Outlet Temperature/Turbine Inlet temperature may be increased over this period from ambient temperature at time Tau Three A ( ⁇ 3A) to near 600°C at time Tau Six ( ⁇ 6).
  • the flame authority 100 may be warmed from temperature T34A at Tau Five ( ⁇ 5) to temperature T34B at Tau Six ( ⁇ 6) e.g., from about e.g., Fig.6E depicts the flame authority 100 outlet hot gas being heated from ⁇ 650°C to about 1150°C over this period.
  • the Combustor outlet temperature may correspondingly be increased to T34B at Tau Seven A ( ⁇ 7A).
  • Fig.6E and Fig.6F may be combined in various configurations to achieve multiple alternative configurations. These may utilize differing start/standby configurations with low and high ignition authority temperatures. E.g., these may utilize lower warming to a lower temperature such as T34A without blade cooling. Alternatively, they may use higher warming to a higher temperature such as T34D with blade cooling. Startup temperature ramp rates may differ such as between T4A and T4B.
  • Operating temperatures may vary between and about one or more of temperatures such as T4D, Peak T4E, T4F, Emergency T4G, Peak T4H, and T4J.
  • Generated power frequency may vary about ⁇ P (not shown).
  • Gas turbine and Generator Rotor speeds may increase from a power frequency ⁇ P to a generator rotational frequency (speed) ⁇ R.
  • Per Fig.6G similarly note the varying Power generated between Power one (P1), Power Two (P2), Power 3 (P3), Peaking Power Four A (P4A), Emergency Power Four B (P4B), and regular Power Five (P5).
  • the preheated gas turbine at temperature T4C may be rapidly ramped up the expander-generator speed from Omega R ( ⁇ R) to Omega P ( ⁇ P).
  • the generator reaches near grid frequency, it begins Power One (P1) over the time Tau Eight ( ⁇ 8) to time Tau Ten ( ⁇ 10).
  • the Ignition Authority 100 may ignite the gas turbine and may be ramped up the turbine temperature from temperature 4C (T4C) on up to part way towards Temperature Four D (T4D) by Time Tau Eleven ( ⁇ 11).
  • Power may then be ramped up to Power P2 with the temperature reaching peaking temperature Four D (T4D) at time Tau Thirteen ( ⁇ 10).
  • This power and temperature may be held until time Tau Nineteen ( ⁇ 19). Temperature may then be ramped up to Emergency Temperature Four (T4E) at with power ramping up to Power Three (P3) at time Tau Fifteen ( ⁇ 15). Temperature may then be ramped Up from Temperature Four E (T4E) to Temperature Four F (T4F) while power is ramped back Down from time Tau Ninteen ( ⁇ 19) to time Tau Twenty ( ⁇ 20).
  • Power may then be shut down from Power Five (P5) over Time Tau Twenty-One ( ⁇ 20) to Time Tau Twenty Two ( ⁇ 20). Meanwhile, the temperature may be independently ramped down from Temperature Five G (T5G) back down to ambient temperature.
  • Fig.6E and Fig.6F may be combined in various configurations to achieve multiple alternative configurations. These may utilize differing start/standby configurations with low and high ignition authority temperatures. E.g., these may utilize lower warming to a lower temperature such as T34A without blade cooling. Alternatively, they may use higher warming to a higher temperature such as T34D with blade cooling. Startup temperature ramp rates may differ such as between T4A and T4B.
  • Operating temperatures may vary between and about one or more of temperatures such as T4D, Peak T4E, T4F, Emergency T4G, Peak T4H, and T4J.
  • Generated power frequency may vary about ⁇ P (not shown). Gas turbine and Generator Rotor speeds may increase from a power frequency ⁇ P to a generator rotational speed (frequency) ⁇ R.
  • Per Fig.6G similarly note the varying Power generated between Power one (P1), Power Two (P2), Power 3 (P3), Peaking Power Four A (P4A), Emergency Power Four B (P4B), and regular Power Five (P5).
  • P1 Power one
  • P2 Power Two
  • P3 Power 3
  • Peaking Power Four A P4A
  • Emergency Power Four B P4B
  • regular Power Five P5
  • the Ignition Authority is preheated to temperature T Thirty_Four D (T34D) by Time Tau 3B ( ⁇ 3B).
  • the Combustor and gas Turbine Expander have been preheated to operating Temperature 4D (T4D).
  • the Power may then be ramped UP to Power Four A (P4A) while the Temperature TIT is being ramped Down from peaking temperature to operating Temperature Four F (T4F) while the Power may then be ramped up to Emergency Power Four A (P4A) at Time Tau Eighteen ( ⁇ 18).
  • This generator power Four B (P4B) and turbine operating temperature Four F (T4F) may be held until time Tau Nineteen ( ⁇ 19). Temperature may then be ramped back down to normal Operating Temperature, Frequency WP temperature to Four G (T4G), and Power and Power Five (P5).
  • Power may then be shut down from Power Five (P5) over Time Tau Twenty-One ( ⁇ 21) to Time Tau Twenty-Two ( ⁇ 22).
  • the Combustor/Expander temperature may be independently ramped down from Temperature Four G (T4G) back down to ambient temperature over Time Twenty-One ( ⁇ 21) to Time Twenty-Three ( ⁇ 23).
  • the Ignition Authority Temperature may similarly be ramped back down from Temperature Thirty-Four D (T34D) to ambient over time from Tau Twenty-Two ( ⁇ 22) to Tau Twenty-Fou ( ⁇ 24).
  • T34D Temperature Thirty-Four D
  • the ignition authority and the Combustor/Gas Turbine may be ramped back to Standby conditions as before.
  • Such preheating may control one or more of the relative ratio Lambda of oxidant fluid to fuel fluid, relative to the corresponding relative stoichiometric ratio (Omega: oxidant to fuel mass ratio relative to the stoichiometric oxidant to fuel mass ratio), the diluent to oxidant mass ratio (Lambda), the gaseous diluent (e.g., steam) to fuel ratio, the liquid diluent (e.g., water) to fuel ratio, or some combination of such ratios sufficient to control combustion within combustion quench limits.
  • Such ratios may further control one or more of these fluid ratios sufficient to control prescribed emission rates during warmup to below prescribed concentrations.
  • Preheating and Standby Temperature Ranges may generate hot fluid to within a prescribed combusting range. E.g., such as within 600°C to 1,800°C, or 800°C to 1,600°C, or 900°C to 1400°C, or 1000°C to 1300°C, or 1100°C to 1200°C etc.
  • the upper range of preheating fluid may be selected to be lower than a prescribed maximum temperature for gas turbine blades without cooling.
  • the upper range of the preheating fluid may be selected to be higher than the minimum temperature requiring cooling and lower than the maximum temperature for gas turbine expander blades with fluid cooling.
  • the composition and equilibrating times may be correspondingly configured to achieve prescribed emission limits during such combustion.
  • Such hot combusting fluid may be diluted with one or both of gaseous diluent and liquid diluent (such as steam and/or liquid water, gaseous CO 2 , liquid CO 2 , and/or supercritical CO2), and/or excess oxidant (such as air) to reduce the temperature of the combusting fluid to within such prescribed warming fluid temperature delivery ranges, and to increase temperature with prescribed temperature warming rates such as described above.
  • gaseous diluent and liquid diluent such as steam and/or liquid water, gaseous CO 2 , liquid CO 2 , and/or supercritical CO2
  • excess oxidant such as air
  • Such combustion, hot fluid formation, fluid cooling, and fluid temperature ramp rates may further be configured to constrain material strains, and/or strain rates in the combustor and/or expander to with prescribe strain ranges, and/or strain rate ranges. Such methods may similarly be conducted to reduce thermal stresses and/or stress rates to within prescribed ranges. Such methods may reduce equipment fatigue and creep. They may maintenance frequency and system and power generating costs. Fast Ramping Scalable Combustors. [0480] VAST Cycle starting, ramping, operating, peak power and emergency power methods such as depicted in Fig. 6E, and Fig.
  • Such techniques may achieve lower loss standby and/or faster dispatch rates with shorter ramp-up times than conventional industrial turbine ramp speeds. e.g., by reducing startup or ramp times from historic slow ramps (e.g., 8 hours) down to one or more of 30 minutes, 15 minutes, 5 minutes, 2 minutes, and 1 minute, or less.
  • Such VAST Cycle operating techniques may be used to more effectively and reliably meet increasing requirements for hot standby power, such as California’s fifteen (15) minute dispatch schedule, its five (5) minute dispatch schedule, and/or its one (1) minute emergency dispatch time period (EDT).
  • EDT emergency dispatch time period
  • Such hybrid gas turbine power operating techniques may similarly supply California’s 10-minute spinning-reserve and/or non-spinning reserve. Such techniques may further be used to reduce thermal creep, reduce cyclic thermal fatigue, reduce cyclic mechanical fatigue, improving longevity, and reduce hot standby fuel use. One or more of these may reduce operating, maintenance, repair, and/or replacement costs. They may correspondingly reduce down time. Such novel capabilities may further earn higher revenues, and better ensure essential grid reliability with lower costs, lower risks, and/or improved profitability. [0483] Methods used herein may precisely control combustor outlet temperature / Turbine Inlet Temperature T4 by the ratio Omega of liquid diluent flow to fuel flow rates.
  • liquid water flow may be monitored with a turbine flow meter using a high resolution optical encoder.
  • Such operating techniques may be used to control ignition authority temperature, combustor temperature, and gas/or turbine temperature faster, more reliably, and/or more accurately using scalable combustors, more independently of power scheduling and/or power demand. These techniques may be used to enable faster power ramps, and reduce combustor and/or turbine temperature gradients. They may improve one or more of compressor, pilot, combustor, expander, generator, and/or overall efficiency.
  • Such combustor and system configuration and/or control methods may further be used to independently control a thermal ramp up (and/or shut down) rate of the Once Thru Steam Generator (OTSG) to hot standby and/or to full hot operating temperatures, separately from the ignition authority, combustor, expander, and/or generator temperature and/or power. Such methods may reduce the thermal stresses and cyclic fatigue of the Once Through Steam Generator (OTSG) heat recovery system, or for a similar Heat Recovery Steam Generator (HRSG).
  • the combustion configuration and control methods described may be used for hybrid Combined Heat and Power (CHP) applications.
  • Such CHP applications may deliver heat to one or more thermal applications, such as through hot water and/or steam, and/or hot gas, such as nitrogen, oxygen and/or carbon dioxide. They may independently generate power, and separately control combustion temperature by delivery of one or more of residual steam, hot water, and/or cold water or other thermal diluent such as Carbon Dioxide (CO2).
  • thermal applications such as through hot water and/or steam, and/or hot gas, such as nitrogen, oxygen and/or carbon dioxide. They may independently generate power, and separately control combustion temperature by delivery of one or more of residual steam, hot water, and/or cold water or other thermal diluent such as Carbon Dioxide (CO2).
  • CO2 Carbon Dioxide
  • each combusting shell comprising: i. a plurality of oxidant fluid feeders; ii. a plurality of fuel fluid feeders; and iii. a plurality of diluent fluid feeders; d. an upstream flame authority configured to: i. receive and mix pilot fuel fluid, pilot oxidant fluid, and pilot diluent fluid; ii. combust the mixed pilot fluids to form a hot pilot fluid; and e. a pilot fluid distribution system configured to: i.
  • a combustor system comprising: a. a combustor wall comprising a fluid duct wall and a thermal insulating barrier; b. a plurality of orifices extending through the combustor wall; c. wherein the plurality of orifices are configured with: i. varying diameters across a transverse direction of the combustor wall; or ii.
  • a combustor system comprising: a. a combustor having an axial flow direction; b.
  • opposing radially and circumferentially extended fluid manifolds comprising: i. an oxidant fluid manifold configured to deliver diluted oxidant fluid; and ii. a fuel fluid manifold configured to deliver diluted fuel fluid; c. a plurality of adjacent combusting regions positioned between the opposing fluid manifolds; d. wherein the oxidant fluid manifold comprises: i. a plurality of oxidant orifices configured to deliver the diluted oxidant fluid into the adjacent combusting regions; ii. an outer oxidant fluid feeder extending radially with a first radial depth; and iii.
  • a combustor system comprising: a.
  • a combustor having an axial flow direction and a radial direction; b. a plurality of axially spaced fluid feeders comprising: i. fuel fluid feeders configured to deliver diluted fuel fluid; and ii. oxidant fluid feeders configured to deliver diluted oxidant fluid; c. wherein each fuel fluid feeder comprises: i. a plurality of fuel orifices distributed in a radially transverse pattern; and ii. fuel orifices configured to deliver progressively varying fuel fluid flows U1 through U7; d. wherein each oxidant fluid feeder comprises: i. a plurality of oxidant orifices distributed in a radially transverse pattern; and ii.
  • oxidant orifices configured to deliver progressively varying oxidant fluid flows X1 through X6; e. a control system configured to control the radially transverse distribution of the fuel orifices and oxidant orifices to achieve: i. prescribed oxidant to fuel ratios across the radial direction; ii. prescribed temperature distributions at the combustor outlet; and iii. prescribed axial velocity distributions at the combustor outlet; f. wherein the control system is further configured to: i. vary the ratio of oxidant delivery to fuel delivery between upstream and downstream portions of a combusting chamber; and ii. control fluid delivery rates to maintain combustion temperature above a combustion quench limit.
  • a combustor system comprising: a.
  • a combustor having an axial flow direction and a radial direction; b. an asymmetric manifold configuration comprising: i. a radially wider oxidant manifold configured to deliver oxidant fluid; and ii. a radially narrower fuel manifold configured to deliver fuel fluid; c. wherein the oxidant manifold comprises: i. a plurality of oxidant feeders delivering oxidant fluid flows X1 through X7; ii. oxidant fluid orifices configured in the oxidant feeders; and iii. a circumferentially wider oxidant feeder passage width to accommodate larger volumetric oxidant fluid flows; d. wherein the fuel manifold comprises: i.
  • a plurality of fuel feeders delivering fuel fluid flows U1 through U7; ii. fuel fluid orifices configured in the fuel feeders; and iii. a circumferentially narrower fuel feeder passage width corresponding to smaller fuel fluid flows; e. wherein the asymmetric manifold configuration provides: i. transverse-axial fluid delivery; ii. controlled mixing of oxidant and fuel fluids; and iii. progressive delivery of oxidant and fuel fluids along the axial direction; f. a downstream blend-trim region configured to receive: i. diluted oxidant fluid flows through blend-trim orifices; and ii. diluent fluid flows through diluent orifices.
  • a combustor system comprising: a. a combustor having an axial flow direction and a radial direction; b. a plurality of fluid orifices configured in combustor walls, wherein the fluid orifices comprise: i. oxidant fluid orifices configured to deliver oxidant fluid; ii. fuel fluid orifices configured to deliver fuel fluid; and iii. diluent fluid orifices configured to deliver diluent fluid; c. wherein the fluid orifices are arranged in a radially transverse spatial distribution comprising: i. upstream orifices having a first spatial distribution pattern; and ii.
  • downstream orifices having a second spatial distribution pattern; d. wherein the upstream orifices comprise: i. larger and more numerous upstream oxidant fluid delivery orifices; and ii. smaller and fewer downstream fuel fluid delivery orifices in a 2:1 ratio; e. wherein the downstream orifices comprise: i. fewer upstream fuel fluid delivery orifices; and ii. more numerous downstream oxidant fluid delivery orifices in a 1:2 ratio; f. wherein: i. oxidant fluid orifices are circumferentially offset from fuel fluid orifices to improve mixing and reduce quenching; ii. upstream blend-trim orifices are offset from downstream blend-trim orifices; and iii.
  • a combustor system comprising: a. a combustor having an axial flow direction and a radial direction; b. a plurality of fluid orifices configured in combustor walls comprising: i. upstream orifices configured to deliver fluids in a first radially transverse spatial configuration; and ii. downstream orifices configured to deliver fluids in a second radially transverse spatial configuration; c. wherein the upstream orifices comprise: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; and iii.
  • diluent fluid orifices configured to deliver diluent fluid; d. wherein the downstream orifices comprise: i. fuel fluid orifices configured in a different spatial pattern than the upstream fuel fluid orifices; ii. oxidant fluid orifices configured in a different spatial pattern than the upstream oxidant fluid orifices; and iii. diluent fluid orifices configured in a different spatial pattern than the upstream diluent fluid orifices; e. wherein: i. the upstream oxidant fluid orifices are circumferentially offset from the upstream fuel fluid orifices; ii.
  • a combustor system comprising: a. a combustor having a combusting shell with an outer portion; b. a heated combusting region within the combusting shell configured to: i. receive fuel fluid comprising ammonia; ii.
  • the heated combusting region comprises: i. sufficient volume to provide residence time for thermal cracking; ii. temperatures between about 400°C to about 650°C to facilitate ammonia cracking; d. a fuel delivery system configured to: i. deliver the ammonia fuel fluid to the outer portion of the combusting shell; ii. control fuel delivery rates to maintain combustion temperature above a combustion quench limit; e. wherein the heated combusting region is configured to: i. crack a major portion of the ammonia fuel to hydrogen and nitrogen; ii. achieve ammonia conversion efficiency greater than about 99%; f. a control system configured to: i.
  • a combustor system comprising: a. an annular combustor comprising: i. an inner annular combusting region wall; ii. an outer annular combusting region wall; and iii. a combusting region extending radially between the inner and outer walls; b. wherein the combusting region comprises: i. a radially extended width oriented from the inner wall to the outer wall; ii.
  • each combusting shell comprises: i. a first combusting chamber wall deposed axially and circumferentially; ii. a radially opposed second combusting chamber wall; iii. a plurality of fluid feeders configured about the combusting chamber walls; d. wherein the fluid feeders comprise: i. fuel fluid feeders configured to deliver fuel fluid; ii. oxidant fluid feeders configured to deliver oxidant fluid; and iii. diluent fluid feeders configured to deliver diluent fluid; e. wherein the combusting region is configured to: i.
  • a combustor system comprising: a. an annular combustor comprising: i. a radially inner wall; ii. a radially outer wall; and iii. expander inlet stators positioned between the inner and outer walls; b. a combusting region comprising: i. an outwardly extended width oriented along a radial direction; ii.
  • each combusting shell comprises: i. a first combusting chamber wall deposed axially and circumferentially; ii. a radially opposed second combusting chamber wall; iii. a plurality of fluid feeders configured about the combusting chamber walls; d. wherein the fluid feeders comprise: i. fuel fluid feeders configured to deliver fuel fluid; ii. oxidant fluid feeders configured to deliver oxidant fluid; and iii.
  • a combustor system comprising: a. a combustor having an upstream combusting region comprising: i. a first combusting chamber wall deposed axially and circumferentially; ii.
  • a radially opposed second combusting chamber wall iii. an inner combustor wall and an outer combustor wall; b. a plurality of fluid orifices configured in the combusting chamber walls comprising: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; iii. diluent fluid orifices configured to deliver diluent fluid; c. wherein the fluid orifices are distributed in a radial pattern configured to: i. control radial temperature distribution across the combusting region; ii. accommodate cooling of the inner combustor wall; iii.
  • a control system configured to: i. control delivery of fuel fluid through the fuel fluid orifices; ii. control delivery of oxidant fluid through the oxidant fluid orifices; iii. control delivery of diluent fluid through the diluent fluid orifices; e. wherein the control system is further configured to maintain: i. a first temperature at an inner radius relative to a second temperature at an outer radius; ii. prescribed intermediate temperatures between the inner and outer radii; iii. temperature gradients between intermediate radial positions; f. wherein the control system controls fluid delivery to: i. maintain combustion temperature above a combustion quench limit; ii.
  • a combustor system comprising: a. a combustor having: i. a radially inner wall; ii. a radially outer wall; and iii. an upstream combusting region and a blend-trim region between the inner and outer walls; b. a plurality of fluid orifices configured in the combusting region comprising: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; iii.
  • diluent fluid orifices configured to deliver diluent fluid; c. a plurality of blend-trim orifices configured in the blend-trim region to deliver: i. additional oxidant fluid; ii. additional diluent fluid; iii. fluid mixtures to control combustion completion; d. wherein the fluid orifices and blend-trim orifices are distributed to achieve: i. a radially inner outlet temperature T4i at an inner radius Ri; ii. a radially outer outlet temperature T4o at an outer radius Ro; iii. wherein T4o is higher than T4i at the combustor outlet; e. a control system configured to control: i.
  • a combustor system comprising: a. a combustor having: i. a radially inner wall; ii. a radially outer wall; and iii.
  • a plurality of fluid orifices configured in the combusting region comprising: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; iii. diluent fluid orifices configured to deliver diluent fluid; c. a plurality of blend-trim orifices configured in the blend-trim region to deliver: i. additional oxidant fluid; ii. additional diluent fluid; iii. fluid mixtures to control combustion completion; d.
  • the fluid orifices and blend-trim orifices are distributed to achieve: i. an inner wall temperature Tw4i at the inner wall; ii. an outer wall temperature Tw4o at the outer wall; iii. prescribed wall temperature ranges between Tw4i and Tw4o; e. wherein the wall temperatures are controlled through: i. an upstream inner wall temperature Tw35i at a transition boundary; ii. an upstream outer wall temperature Tw35o at the transition boundary; iii. intermediate inner and outer wall temperatures Tw39i and Tw39o at a blend-trim region outlet; f. a control system configured to maintain: i. the inner and outer wall temperatures within desired temperature ranges; ii.
  • a combustor system comprising: a. a combustor having: i. a radially inner wall at a radius R4i; ii. a radially outer wall at a radius R4o; and iii. an upstream combusting region between the inner and outer walls; b. a plurality of fluid orifices configured in the upstream combusting region comprising: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; iii.
  • diluent fluid orifices configured to deliver diluent fluid; c. wherein the fluid orifices are distributed to achieve at a combustor outlet: i. a radially inner axial velocity V4i near the inner wall; ii. a first intermediate axial velocity V4j at a first intermediate radius R4j; iii. a second intermediate axial velocity V4k at a second intermediate radius R4k; iv. a radially outer axial velocity V4o near the outer wall; d. wherein at least one of: i. the radially inner axial velocity V4i is lower than both intermediate velocities V4j and V4k; and ii.
  • the radially outer axial velocity V4o is lower than both intermediate velocities V4j and V4k; e. a control system configured to control: i. fuel fluid delivery through the fuel fluid orifices; ii. oxidant fluid delivery through the oxidant fluid orifices; iii. diluent fluid delivery through the diluent fluid orifices; f. wherein the control system maintains: i. prescribed velocity distributions between the inner and outer walls; ii. prescribed velocity gradients between intermediate radial positions; iii. combustion temperature above a combustion quench limit.
  • a combustor system comprising: a. a combustor having: i.
  • a combustor system comprising: a. a combustor having: i. a circumferentially inner region; ii. a circumferentially outer region; and iii. an upstream combusting region between the inner and outer regions; b.
  • a plurality of fluid orifices configured in the upstream combusting region comprising: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; iii. diluent fluid orifices configured to deliver diluent fluid; c. wherein the fluid orifices are distributed to achieve at a combustor outlet: i. a circumferentially inner temperature Ti; ii. a circumferentially intermediate temperature T between Ti and To; iii. a circumferentially outer temperature To; iv. wherein at least one of Ti and To is lower than T; d. wherein the temperature distribution is controlled through: i.
  • a control system configured to control: i. fuel fluid delivery through the fuel fluid orifices; ii. oxidant fluid delivery through the oxidant fluid orifices; iii. diluent fluid delivery through the diluent fluid orifices; f. wherein the control system maintains: i. prescribed temperature distributions between inner and outer circumferential regions; ii. prescribed temperature gradients between intermediate circumferential positions; iii. combustion temperature above a combustion quench limit.
  • a combustor system comprising: a. a combustor having: i. a circumferentially inner region; ii. a circumferentially outer region; and iii. an upstream combusting region between the inner and outer regions; b. a plurality of fluid orifices configured in the upstream combusting region comprising: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; iii. diluent fluid orifices configured to deliver diluent fluid; c. wherein the fluid orifices are distributed to achieve at a combustor outlet: i.
  • a circumferentially inner temperature Ti ii. a circumferentially intermediate temperature T between Ti and To; iii. a circumferentially outer temperature To; iv. wherein at least one of Ti and To is higher than T; d. wherein the temperature distribution is controlled through: i. a first combustion section centered at angle Theta1i; ii. a second combustion section centered at angle Theta2i; iii. prescribed temperature gradients between the combustion sections; e. wherein the combustion sections comprise: i. a first section extending circumferentially from angle Theta1wi to Theta1ci; ii. a second section displaced clockwise from the first section; iii.
  • a combustor system comprising: a. a combustor having: i. a radially inner region at an inner radius Ri; ii. a radially outer region at an outer radius Ro; and iii. an upstream combusting region between the inner and outer regions; b.
  • a plurality of fluid orifices configured in the upstream combusting region comprising: i. fuel fluid orifices configured to deliver fuel fluid; ii. oxidant fluid orifices configured to deliver oxidant fluid; iii. diluent fluid orifices configured to deliver diluent fluid; c. wherein the fluid orifices are distributed to achieve at a combustor outlet: i. inner velocities Vi at the inner radius Ri; ii. outer velocities Vo at the outer radius Ro; iii. prescribed velocity distributions between Vi and Vo; d. wherein the velocity distribution is controlled through: i. a first combustion section centered at angle Theta1; ii.
  • a second combustion section centered at angle Theta2; iii. prescribed velocity gradients between the combustion sections; e. wherein the combustion sections comprise: i. a cooled counterclockwise first section from angle Theta1wi to Theta1ci; ii. a clockwise second section from angle Theta2wi to Theta2ci; iii. velocity ranges between Vsi and Vi at inner radius Ri; iv. velocity ranges between Vso and Vo at outer radius Ro; f. a control system configured to maintain: i. prescribed velocity distributions between inner and outer circumferential regions; ii. prescribed velocity gradients between intermediate circumferential positions; iii. combustion temperature above a combustion quench limit.
  • a combustor system comprising: a. a combustor having: i. an upstream combusting region; ii. a plurality of mixing chambers; and iii. fluid delivery passages connected to the mixing chambers; b. a plurality of fluid feeders configured to deliver into the mixing chambers: i. fuel fluid comprising a fuel; ii. oxidant fluid comprising an oxidant; iii. diluent fluid comprising a diluent; c. wherein the mixing chambers are configured to: i.
  • the mixing chambers comprise: i. radial-circumferential extending feeder walls; ii. radially inner and outer end walls; iii. axial-circumferential blended feeder divider walls; e. wherein the mixing chambers include: i. fuel fluid delivery orifices configured between fuel fluid feeders and mixing chambers; ii.
  • premixed reactive fluid orifices configured to deliver premixed fluid into adjacent combusting regions; iii. orifice diameters constrained to avoid flashback from combusting regions; f. a control system configured to: i. control delivery of fluids to the mixing chambers; ii. maintain combustion temperature above a combustion quench limit; iii. achieve prescribed temperature distributions at the combustor outlet.
  • a combustor system comprising: a. a combustor having: i. a downstream combusting region; ii. a plurality of mixing chambers; and iii. fluid delivery passages connected to the mixing chambers; b. a plurality of fluid feeders configured to deliver into the mixing chambers: i.
  • oxidant fluid comprising an oxidant; ii. diluent fluid comprising a diluent; iii. fluid mixtures to control combustion completion; c. wherein the mixing chambers are configured to: i. receive and mix combinations of: - oxidant fluid and diluent fluid; ii. form premixed diluted oxidant fluid mixtures; iii. deliver the premixed diluted oxidant fluid mixtures into the downstream combusting flow; d. wherein the mixing chambers comprise: i. non-reactive dilutive premixing chambers in a blend-trim region; ii. oxidative fluid orifices delivering oxidative fluid into the premixing chambers; iii.
  • the mixing chambers include: i. premixed dilutive orifices configured to deliver premixed diluted oxidant fluid into the blend-trim region; ii. orifice configurations to achieve prescribed mixing; iii. orifice distributions to control combustion completion; f. a control system configured to: i. control delivery of oxidant and diluent fluids to the mixing chambers; ii. maintain combustion temperature above a combustion quench limit; iii. achieve prescribed temperature distributions at the combustor outlet.
  • SCR selective catalytic reduction
  • Stage 2 NOx – SCR for NH3 - After an expansion turbine section, create a thermogenerator to serve as a NOx generator using CH4, diesel, or other hydrocarbonaceous fuel.
  • Implement Storage and Control Systems by: o Installing pressurized surge tank for NOx storage o Maintaining pressure of surge tank above exhaust gas stream level of a simple cycle gas turbine or above low pressure of HRSG in a combined cycle gas turbine.
  • Method Steps Forming a liquid mixture comprising one of: o Ammonia (NH3) o Nitrogen Oxides (NOx) 2.
  • NH3 o Ammonia
  • NOx Nitrogen Oxides
  • 3. Configuring sufficient equilibrating region volume to provide adequate residence time for NH3 and NOx mixing and reaction below prescribed limits. 4.
  • duct, tube or array configurations are provided, similar two- or three- dimensional configurations or combinations of those configurations may be efficaciously utilized, including varying the nominal thicknesses, diameters, cross sectional shapes, spacings, orientations, and other dimensions and parameters for perforated ducts, perforated tubes, manifolds, sub-manifolds and tube arrays.
  • fuel, diluent, water, steam, air, oxygen, and oxidant have been used, the processes are generally applicable to other combinations of those fluids or to other combinations of other reacting, co-reacting, and diluent or non-reacting fluids.
  • control measures may utilize one or more measures to control the differential ejection pressure distributions across the fluid orifices 80, to vibrate the orifices, and/or to control the electro-magnetic field about the orifices 80 using one or more measures described herein, and/or by using similar means of modulating the orifices’ location, the fluid pressure, and the surrounding electro-magnetic field.

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  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne des systèmes et des procédés de combustion évolutive. Un système de dispositif de combustion évolutive comprend un système de distribution de fluide conçu pour distribuer un fluide combustible comprenant un combustible, un fluide oxydant comprenant un oxydant ; et un fluide diluant comprenant un diluant ; dans un dispositif de combustion, en communication fluidique avec le système de distribution de fluide. Le dispositif de combustion comprend une chambre de combustion présentant une première paroi de dispositif de combustion et une seconde paroi de dispositif de combustion opposée à la première paroi de dispositif de combustion. Le dispositif de combustion comprend en outre une pluralité d'orifices dans au moins l'une des première et seconde parois de dispositif de combustion et une sortie de dispositif de combustion. Les première et seconde parois de dispositif de combustion sont allongées transversalement par rapport à un espacement peu profond entre les première et seconde parois de dispositif de combustion, le long de directions transversales et perpendiculaires à une direction d'écoulement dans le sens de l'écoulement à travers le dispositif de combustion.
PCT/US2024/055262 2023-11-08 2024-11-08 Systèmes et procédés pour dispositifs de combustion évolutive Pending WO2025102000A1 (fr)

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3241609A (en) * 1964-03-03 1966-03-22 Itt Sheet metal heat exchange stack or fire tube for gas fired hot air furnaces
US20090180939A1 (en) * 2003-01-22 2009-07-16 Hagen David L Trifluid reactor
US20200263870A1 (en) * 2015-08-27 2020-08-20 Johns Manville Burner panels, submerged combustion melters, and methods
US20220412557A1 (en) * 2017-03-07 2022-12-29 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3241609A (en) * 1964-03-03 1966-03-22 Itt Sheet metal heat exchange stack or fire tube for gas fired hot air furnaces
US20090180939A1 (en) * 2003-01-22 2009-07-16 Hagen David L Trifluid reactor
US20200263870A1 (en) * 2015-08-27 2020-08-20 Johns Manville Burner panels, submerged combustion melters, and methods
US20220412557A1 (en) * 2017-03-07 2022-12-29 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof

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