WO2018222192A1 - Moteur à turbine à gaz industriel à double corps à rapport de pression élevé avec compresseur à corps à double flux élevé - Google Patents

Moteur à turbine à gaz industriel à double corps à rapport de pression élevé avec compresseur à corps à double flux élevé Download PDF

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Publication number
WO2018222192A1
WO2018222192A1 PCT/US2017/035348 US2017035348W WO2018222192A1 WO 2018222192 A1 WO2018222192 A1 WO 2018222192A1 US 2017035348 W US2017035348 W US 2017035348W WO 2018222192 A1 WO2018222192 A1 WO 2018222192A1
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WIPO (PCT)
Prior art keywords
compressor
high pressure
compressed air
flow path
spool
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US2017/035348
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English (en)
Inventor
John A. Orosa
Joseph D. BROSTMEYER
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Florida Turbine Technologies Inc
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Florida Turbine Technologies Inc
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Filing date
Publication date
Application filed by Florida Turbine Technologies Inc filed Critical Florida Turbine Technologies Inc
Priority to PCT/US2017/035348 priority Critical patent/WO2018222192A1/fr
Publication of WO2018222192A1 publication Critical patent/WO2018222192A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/064—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor having concentric stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates generally to an industrial gas turbine engine, and more specifically to a twin spool industrial gas turbine engine with a low pressure spool that can be operated independently of the high pressure spool.
  • ILT inductor
  • the turbine includes one or more stages of stator vanes and rotor blades that react with the hot gas stream in a progressively decreasing temperature.
  • the efficiency of the turbine - and therefore the engine - can be increased by passing a higher temperature gas stream into the turbine.
  • the turbine inlet temperature is limited to the material properties of the turbine, especially the first stage vanes and blades, and an amount of cooling capability for these first stage airfoils.
  • FIG. 12 shows a single shaft IGT engine with a compressor 1 connected to a turbine 2 with a direct drive electric generator 3 on the compressor end.
  • FIG. 13 shows a dual shaft IGT engine with a high spool shaft and a separate power turbine 4 that directly drives an electric generator 3.
  • FIG. 14 shows a dual shaft aero derivative gas turbine engine with concentric spools in which a shaft 5 of the high pressure spool rotates around the shaft 6 of the low pressure spool, and where a separate low pressure shaft directly drives an electric generator 3.
  • FIG. 15 shows a three-shaft IGT engine with a shaft 6 of the low pressure spool rotating within a shaft 5 of the high pressure spool, and a separate power turbine 4 that directly drives an electric generator 3.
  • the configuration of the FIG. 12 IGT engine is the most common for electric power generation and is limited by non-optimal shaft speeds for achieving high component efficiencies at high pressure ratios.
  • the mass flow inlet and exit capacities are limited structurally by AN 2 (last stage blade stress) and tip speeds that limit inlet and exit diameters due to high tip speed induced Mach number (#) losses in the flow. Therefore for a given rotor speed, there is a maximum inlet diameter and
  • FIG. 13 arrangement is similarly limited in achieving high component efficiencies at high pressure ratios as the FIG. 12 arrangement, since the entire compressor is on one shaft.
  • Turn down ratio is the ratio of the lowest power load at which a gas turbine engine can operate (and still achieve CO emissions below the pollution limit) divided by the full 100% load power.
  • Today's gas turbines have a turn down ratio of around 40%. Some may be able to achieve 30 %.
  • Low part load operation requires a combination of low combustor exit temperatures and low inlet mass flows.
  • Low CO emissions require a high enough combustor temperature to complete the combustion process. Since combustion temperature must be maintained to control CO emissions, the best way to reduce power is to reduce the inlet mass flow.
  • Typical single shaft gas turbine engines use compressor variable inlet guide vanes to reduced inlet mass flow.
  • the limit for the compressor flow reduction is around 50% for single shaft constant rotor speed compressors as in FIG. 12.
  • the FIG. 14 arrangement is similarly limited as the FIG. 12 arrangement in inlet mass flow reduction since the low pressure compressor runs the constant speed of the electric generator 3.
  • FIG. 15 arrangement is the most efficient option of the current configurations for IGT engines, but is not optimal because the low pressure spool shaft 6 rotates within the high pressure spool shaft 5, and thus a further reduction in the high spool radius cannot be achieved.
  • speed of the low spool shaft 6 is reduced to reduce inlet mass flow, there is a mismatch of angle entering the LPT (Low Pressure Turbine) from the HPT (High Pressure Turbine) and mismatch of the flow angle exiting the LPT and entering the PT (Power Turbine) leading to inefficient turbine performance at part load.
  • LPT Low Pressure Turbine
  • HPT High Pressure Turbine
  • An electric generator is connected directly to the high pressure spool and operates at a continuous and constant speed as is required for a direct drive electric generator.
  • the low pressure spool is driven by turbine exhaust from the high pressure spool and includes variable inlet guide vanes in order to regulate the speed of the low pressure spool.
  • Compressed air from the low pressure spool is supplied to an inlet of the compressor of the high pressure spool.
  • An interstage cooler can be used to decrease the temperature of the compressed air passed to the high pressure spool.
  • twin spool IGT engine with separately operable spools can maintain high component efficiencies of the compressor and turbine at high pressure ratios of 40 to 55, which allow for increased turbine inlet temperatures while keeping the exhaust temperature within today's limits.
  • the turbine exhaust from both spools can be directed into a HRSG (heat recovery steam generator) to produce steam that is used to power a steam turbine that drives an electric generator to further increase the overall efficiency of the combined cycle power plant.
  • HRSG heat recovery steam generator
  • a fraction of the compressed air from the low pressure compressor is extracted and further compressed by a boost compressor and then delivered to a cooling circuit for the high pressure turbine stator vanes, where the heated cooling air is then discharged into the combustor.
  • turbine exhaust from the high pressure spool is used to drive an intermediate pressure power turbine (IPPT) that is connected by a power shaft to an external load such as an electric generator, a gearbox, a compressor, or a ship propeller.
  • IPPT intermediate pressure power turbine
  • the intermediate pressure power turbine shaft passes within the low pressure spool whereby the speed of the intermediate pressure power turbine shaft can be regulated by controlling the speed of the low pressure spool and thus regulating the mass flow amount of compressed air supplied from the low spool compressor to the high spool compressor.
  • the load an electric generator, a gearbox, a compressor, or a ship propeller, for example
  • IPPT intermediate pressure power turbine
  • a gas turbine combined cycle power plant can operate with a net thermal efficiency of greater than 67% which is a significant increase over current engine thermal efficiencies.
  • IGT engines used for electrical power production are limited to power output of around 350 MW (for a 60 hertz system) due to size, stress limitations, and mass flow constraints.
  • existing IGT engines can be retrofitted to operate at more than double the existing maximum power output.
  • twin spool IGT engine Another benefit of the twin spool IGT engine is that a family of different sizes of prior art single spool IGT engines can be retrofitted by including the low pressure spool design of the present invention of varying size and pressure ratio that would supply compressed air to the high spool compressor.
  • Cooling air used to cool hot parts of a turbine is reintroduced into a combustor in which the cooling air is discharged into a diffuser located between an outlet of the compressor and an inlet of the combustor in order to energize the boundary layer within the diffuser.
  • cooling air from the stator vanes is discharged parallel to the compressed air flow against an outer wall of the diffuser and cooling air from the rotor blades is discharged parallel to the compressor discharge against an inner wall of the diffuser and at a velocity equal to or greater than the velocity of the compressor discharge air so that the boundary layer in the diffuser is energized.
  • An industrial gas turbine engine for electrical power generator includes a high spool connected directly to an electric generator and a low spool separate from the high spool so that the two spools can be operated rotatably independently of one another.
  • Compressed air from the low spool compressor flows into the inlet of the compressor of the high spool.
  • the high spool compressor includes an inner flow path and an outer flow path with different temperatures of flow.
  • the inner flow path is compressed in the high spool compressor and then discharged into the combustor.
  • the outer flow path is first cooled in an inter-cooler and then compressed in the high spool compressor, where the cooler compressed air is then passed through stator vanes in the turbine to provide cooling.
  • the outer flow path of the high spool compressor is about 20% of the total flow through the high spool compressor. If the outer flow compressed air is not cooled, the compressed air discharged from the high spool compressor would be too hot to be used in cooling of turbine vanes.
  • the high spool compressor can have the cooler air flow in the outer flow path or in the inner flow path so that the cooler compressed air can be used to cool the rotor of the high spool compressor.
  • the high spool compressor with the dual flow paths includes rotor blades with a main blade extending from the rotor and a shroud on the end of the main blade, with one or more smaller blades extending from the shroud to form the compressor airfoils for the outer and smaller flow path.
  • an industrial gas turbine engine for electrical power production includes: a high pressure spool with a dual flow high pressure compressor, a high pressure turbine, and a combustor between the dual flow high pressure compressor and the high pressure turbine, the high pressure turbine having an air cooled airfoil; an electric generator connected to the high pressure spool to produce electrical power; a low pressure spool with a low pressure compressor and a low pressure turbine; the high pressure spool and the low pressure spool being capable of rotating independently; an outlet of the low pressure compressor of the low pressure spool being connected to an inlet of the dual flow high pressure compressor of the high pressure spool; the dual flow high pressure compressor having a first flow path to supply compressed air at a first pressure to the combustor; the dual flow high pressure compressor having a second flow path concentric with the first flow path to supply compressed air at a second pressure higher than the first pressure to the air cooled airfoil within the high pressure turbine; and cooling air from the air cooled airfoil being discharged into the
  • the dual flow high pressure compressor includes multiple rows of rotor blades and stator vanes in which each rotor blade and stator vane includes a shroud separating the first flow path from the second flow path, the first flow path being an inner compressed air flow path and the second flow path being an outer compressed air flow path.
  • the industrial gas turbine engine further includes a second dual flow compressor downstream from a first dual flow compressor, the second dual flow high pressure compressor including an inner axial compressor and an outer centrifugal compressor both connected to a common rotor.
  • the dual flow high pressure compressor includes a second dual flow high pressure compressor downstream from a first dual flow high pressure compressor; the first dual flow high pressure compressor is an axial flow compressor with an inner compressed air flow path and an outer compressed air flow path; the second dual flow high pressure compressor is an axial flow compressor downstream from the inner compressed air flow path; and the first dual flow high pressure compressor and second dual flow high pressure compressor are connected to a common rotor.
  • the air cooled airfoil is a row of turbine stator vanes.
  • the outer centrifugal compressor of the second dual flow high pressure compressor supplies the higher pressure compressed air to the air cooled airfoil, and the inner axial flow compressor of the second dual flow high pressure compressor supplies compressed air directly to the combustor.
  • the inner compressed air flow path supplies compressed air to the air cooled turbine airfoil, and the outer compressed air flow path supplies compressed air directly to the combustor.
  • a multiple stage compressor for an industrial gas turbine engine includes: a rotor; a plurality of rows of rotor blades extending from the rotor; a plurality of rows of stator vanes extending from a stationary housing of the multiple stage compressor; the rows of rotor blades and rows of stator vanes each having a shroud to separate an inner compressed air flow path from an outer compressed air flow path; and the outer compressed air flow path makes up around 20% of the flow of the multiple stage compressor.
  • the inner compressed air flow path and the outer compressed air flow path are both axial flow paths.
  • the rotor, the plurality of rows of rotor blades, are the plurality of rows of stator vanes are part of a first compressor, the multiple stage compressor further including: a second compressor downstream from the first compressor; the first compressor and the second compressor are connected to a common rotor; and the second compressor includes an axial flow inner compressed air flow path and a centrifugal flow outer compressed air flow path.
  • a multiple stage compressor for an industrial gas turbine engine includes: a rotor, a plurality of rows of rotor blades extending from the rotor; a plurality of rows of stator vanes extending from a stationary housing of the multiple stage compressor; the rows of rotor blades and rows of stator vanes each have a shroud to separate an inner compressed air flow path from an outer compressed air flow path; the inner compressed air flow path makes up around 20% of the flow of the multiple stage compressor; a second compressor downstream from a first compressor; the second compressor is connected to the same rotor as the first compressor; the second compressor includes multiple rows of rotor blades and stator vanes; and the second compressor forms a continuation of the inner compressed air flow path of the first compressor to further compress the air from the inner compressed air flow path.
  • FIG. 1 shows a first embodiment of the gas turbine engine with turbine airfoil cooling of the present invention
  • FIG. 2 shows a second embodiment of the gas turbine engine with turbine airfoil cooling with inter-stage cooling of the present invention
  • FIG. 3 shows a third embodiment of the gas turbine engine with turbine airfoil cooling with inter- stage cooling of the present invention
  • FIG. 4 shows a fourth embodiment of the gas turbine engine with turbine airfoil cooling with inter-stage cooling associated with a HRSG for steam production of the present invention
  • FIG. 5 shows a diagram of a power plant with a first embodiment of a mechanically uncoupled twin spool industrial gas turbine engine of the present invention
  • FIG. 6 shows a diagram of a power plant with a second embodiment of a mechanically uncoupled twin spool industrial gas turbine engine of the present invention
  • FIG. 7 shows a diagram of a power plant with a third embodiment of a mechanically uncoupled twin spool industrial gas turbine engine of the present invention
  • FIG. 8 shows a diagram of a gas turbine engine with a fourth embodiment of a mechanically uncoupled twin spool industrial gas turbine engine of the present invention
  • FIG. 9 shows a cross sectional view of a power plant with a mechanically uncoupled three shaft industrial gas turbine engine of the present invention.
  • FIG. 10 is a cross sectional view of a diffuser used between a compressor and a combustor in the gas turbine engine of the present invention.
  • FIG. 11 is a cross sectional view of a second embodiment of a diffuser used between a compressor and a combustor in the gas turbine engine of the present invention
  • FIG. 12 shows a prior art single shaft spool IGT engine with a direct drive electric generator on the compressor end
  • FIG. 13 shows a prior art dual shaft IGT engine with a high spool shaft and a separate power turbine that directly drive an electric generator;
  • FIG. 14 shows a prior art dual shaft aero gas turbine engine with concentric spools in which a high spool rotates around the low spool, and where a separate low pressure shaft that directly drives an electric generator;
  • FIG. 15 shows a prior art three-shaft IGT engine with a low pressure spool rotating within a high pressure spool, and a separate power turbine that directly drives an electric generator;
  • FIG. 16 shows a cross section view of a prior art twin spool aero gas turbine engine with a high spool concentric with and rotatable around the low spool;
  • FIG. 17 shows a cross section view of a mechanically uncoupled twin spool industrial gas turbine engine of the present invention
  • FIG. 18 shows a diagram of a power plant with a mechanically uncoupled twin spool industrial gas turbine engine having a dual flow compressor for another embodiment of the present invention
  • FIG. 19 shows a cross section view of the dual flow compressor with the smaller flow on the outer flow path of the present invention
  • FIG. 20 shows a cross section view of the dual flow compressor of FIG. 19 with a second dual flow compressor located downstream of the present invention
  • FIG. 21 shows a cross section view of a dual flow compressor with the smaller flow on the inner flow path with additional blades to further compress the inner flow path of the present invention
  • FIG. 22 shows a view of one of the blades in the dual flow compressor of the present invention with multiple blades in the outer flow path with one blade on the inner flow path separated by a shroud;
  • FIG. 23 shows a view of one of the blades in the dual flow compressor of the present invention with multiple blades in the inner flow path and one blade extending from the shroud in the outer flow path.
  • FIG. 1 shows a first embodiment of the present invention with a gas turbine engine having a first or main compressor 11, a combustor 12 and a turbine 13 in which the compressor 11 and the turbine 13 are connected together by a rotor shaft.
  • the turbine 13 has a first stage of stator vanes 16 that are cooled.
  • the compressor 11 compresses air that is then burned with a fuel in the combustor 12 to produce a hot gas stream that is passed through the turbine 13.
  • a second or cooling air compressor 14 is driven by a motor 15 to compress air at a higher pressure than from the first compressor 11.
  • the higher compressed air is then passed through the stator vanes 16 in the turbine 13 for cooling, and the heated cooling air is then passed into the combustor 12 to be combined with the fuel and the compressed air from the first or main compressor 11.
  • the second or cooling air compressor 14 produces high pressure compressed air for cooling of the stator vanes 16 such that it can then be discharged into the combustor 12. Without the suitable higher pressure from the cooling air compressor
  • FIG. 2 shows a second embodiment of the present invention in which a cooling air flow compression system includes a low pressure compressor (LPC) 14 and a high pressure compressor (HPC) 17 with an intercooler 21 in-between to cool the compressed air from the LPC 14.
  • LPC low pressure compressor
  • HPC high pressure compressor
  • the compressed air from the cooling air flow compression system (14, 17) and the intercooler 21 is then used to cool the stator vanes 16 which is then discharged into the combustor 12.
  • the cooling air flow compression system (14, 17) with the intercooler 21 produces a higher pressure cooling air than the first compressor 11 so that enough pressure remains after cooling of the stator vanes 16 to be discharged into the combustor 12.
  • FIG. 3 shows a third embodiment of the present invention where the cooling air for the stator vanes 16 is bled off from a later stage (after the first stage and before the last stage) of the main flow compressor 11, passed through an intercooler 21, and then enters a cooling air compressor 14 to be increased in pressure.
  • the higher pressure air from the second or cooling air compressor 14 is then passed through the stator vanes 16 for cooling, and then discharged into the combustor 12.
  • the first or main flow compressor 11 provides approximately around 80% of the required air for the combustor 12.
  • the second or cooling air compressor 14 produces the remaining 20% for the combustor 12.
  • the first or main flow compressor 11 has a pressure ratio of 30 while the second or cooling air compressor 14 has a pressure ratio of 40.
  • FIG. 4 shows another embodiment of the present invention with turbine cooling and an intercooler heat recovery.
  • the gas turbine engine includes a main compressor 11, a combustor 12, and a turbine 13 in which a turbine airfoil such as a stator vane 16 is cooled.
  • Fuel is introduced into the combustor 12 to produce a hot gas stream that is passed through the turbine 13. Compression of the turbine cooling air flow takes place in low pressure compressor (LPC) 32 and a high pressure compressor (HPC) 34 with an intercooler/low pressure steam generator 33 in between.
  • LPC low pressure compressor
  • HPC high pressure compressor
  • An intercooler/low pressure steam generator 33 is positioned between the low pressure compressor 32 and the high pressure compressor 34 to cool the compressed air between compressors (cooling the compressed air from LPC 32 increases its density, which allows for the HPC 34 to create higher pressure) so that it is more effective in cooling turbine airfoil 16.
  • a motor 31 drives both compressors 32 and 34 that compress air for use in cooling of the turbine airfoil 16.
  • the gas turbine 13 exhaust is used to produce steam in a heat recovery steam generator (HRSG) 40.
  • HRSG 40 produces high pressure (HP) steam 42 that is delivered to a high pressure turbine 36 to drive a first electric generator 35.
  • the HRSG 40 also produces low pressure (LP) steam 43 that is combined with LP steam from the HP turbine exhaust that flows into a low pressure (LP) turbine 37 that drives a second electric generator 38.
  • a stack 41 discharges the turbine exhaust after use in the HRSG 40.
  • a condenser 39 condenses the steam discharged from the LP turbine 37 into water that then flows through a pump 44 and then into the HRSG 40 or to the intercooler 33.
  • the intercooler 33 is used to cool the compressed air discharged from the low pressure compressor 32 producing low pressure (LP) steam that then flows into the inlet of the LP turbine 37 along with the LP steam from the HRSG 40.
  • LP low pressure
  • the compressed air from the high pressure compressor 34 has a lower temperature than without the use of an intercooler and therefore the cooling of the turbine airfoil 16 is improved.
  • the cooling air from the turbine airfoil 16 is then discharged into the combustor 12 to be burned with fuel and produce the hot gas stream for the turbine 13.
  • FIG. 5 is a high pressure ratio flexible industrial gas turbine engine with independently operated spools in which the high pressure spool can be operated with or without the low pressure spool depending on the electrical power load.
  • FIG. 5 shows the power plant to include a main gas turbine engine with a high pressure compressor 51, a combustor 53, and a high pressure gas turbine 52 connected by a rotor shaft to an electric generator 55.
  • the main engine (51, 52, 53) and the generator 55 are rotatably supported by bearings.
  • the inlet of the main high pressure compressor 51 is connected to a boost compressor 56 through a valve 57.
  • the high pressure compressor 51 and the high pressure turbine 52 are part of the high pressure spool.
  • a low pressure gas turbine 61 is connected to a low pressure compressor 62 by a rotor shaft which is supported by bearings.
  • the low pressure compressor 62 includes a variable inlet guide vane assembly 63 allowing for modulating the compressed air flow.
  • the low pressure gas turbine 61 and low pressure compressor 62 forms a low pressure spool and is independently operated with (that is, can operate independently from) the main engine or high pressure spool 51, 52, and 53.
  • the high pressure compressor can also include variable inlet guide vanes that allow for flow matching and speed control.
  • the low pressure spool 61 and 62 can be shut down and not be operated while the main engine or high pressure spool 51, 52, and 53 operates to drive the electric generator 55.
  • An outlet of the low pressure compressor 62 is connected by a line 67 to an inlet of the high pressure compressor 51.
  • An intercooler 65 can be used between the outlet of the low pressure compressor 62 and the inlet of the high pressure compressor 51 to cool and increase the density of the compressed air.
  • a valve 66 can also be used in the line 67 for the compressed air from the low pressure compressor 62 to the high pressure compressor 51.
  • FIG. 5 shows the line 67 entering the high pressure compressor 51 downstream from the first stage compressor blades, but could be located upstream from the first stage compressor blades.
  • a large frame heavy duty industrial gas turbine engine (the largest of the industrial gas turbine engines) of the prior art uses only a single spool with the rotor shaft directly connected to an electric generator. This design permits a large amount of power transfer to the generator without the need for a gearbox. Due to these factors, the industrial gas turbine must operate with a very specific rotor speed equal to the synchronization speed of the local electrical power grid supplied by the electric generator.
  • the high spool Because of the high spool being supplied with compressed air from the low spool, the high spool can more than double the mass flow through the engine and thus can produce more than double the output power of the prior art single spool large frame heavy duty industrial gas turbine engine such as that shown in FIG. 12.
  • the efficiency of the gas turbine is known to be largely a function of the overall pressure ratio. While existing IGTs limit the maximum compressor pressure ratio that can be achieved because optimum efficiency cannot be achieved simultaneously in the low and high pressure regions of the compressor while both are operating at the same (synchronous) speed, an arrangement that allows the low and high pressure compressors to each operate at their own optimum rotor speeds will permit the current overall pressure ratio barrier to be broken. In addition, segregating the low and high pressure systems is enabling for improved component efficiency and performance matching. For example, the clearance between rotating blade tips and outer static shrouds or ring segments of existing IGTs must be relatively large because of the size of the components in the low pressure system. In the present invention, the clearances in the high pressure system could be reduced to increase efficiency and performance.
  • twin spool turbocharged IGT of the present invention enables a more operable system such that the engine can deliver higher efficiency at turn-down, or part power, and responsiveness of the engine can be improved. Further, this design allows for a greater level of turndown than is otherwise available from the prior art IGTs.
  • the power output and mass flow of prior art IGTs is limited by the feasible size of the last stage turbine blade.
  • the length of the last stage turbine blade is stress-limited by the product of its swept area (A) and the square of the rotor speed (N). This is commonly referred to as the turbine AN 2 .
  • the turbine flow rate will be limited by the swept area of the blade. If the rotor speed could be reduced, the annulus area could be increased, and the turbine can then be designed to pass more flow and produce more power.
  • gas turbines designed for the 50Hz electricity market which turn at 3,000 rpm, can be designed with a maximum power output capability which is about 44% greater than an equivalent gas turbine designed for the 60Hz market (which turns at 3,600 rpm).
  • a separate low pressure system comprising a low pressure compressor and turbine could be designed to operate at lower speeds to permit significantly larger quantities of air to be delivered to the high pressure (core) of the gas turbine.
  • the solution of the present invention is to switch from single spool to independently operating double spool which allows for the last stage turbine blade to be designed at a lower RPM which keeps the turbine within typical limits.
  • a conventional design of a dual spool engine would place the electric generator on the low spool, fixing the speed of the electric generator, and have a higher RPM high spool engine.
  • the twin spool turbocharged IGT of the present invention the electric generator is located on the high spool, and has a variable speed low spool. This design provides numerous advantages. Since the low spool is untied from the grid frequency, a lower RPM than synchronous can be selected allowing the LPT to operate within AN 2 limits.
  • twin spool turbocharged IGT of the present invention maintains a higher combustion discharge temperature at 12% load than the prior art single spool IGT operating at 40% load.
  • power was reduced by closing the inlet guide vanes on the high pressure compressor.
  • Low and high pressure compressor aerodynamic matching was accomplished using a variable LPT vane which reduces flow area into the LPT, thus reducing low spool RPM.
  • a prior art single spool IGT is capable of achieving a low power setting of approximately 40-50% of max power.
  • the twin spool turbocharged IGT of the present invention is capable of achieving a low power setting of around 12% of max power. This enhanced turndown capability provides a major competitive advantage given the requirements of flexibility being imposed on the electrical grid from variable power generation sources.
  • a HRSG (heat recovery steam generator) 40 with stack 41 is used to take the exhaust gas from the gas turbines 52 and 61 through line 64 and produce steam for use in high pressure steam turbine 36 and low pressure steam turbine 37 that are both connected to drive a second electric generator 38.
  • the exhaust finally is discharged through a stack 41.
  • the second dashed line in FIG. 5 represents a direct connection from the exhaust of the high pressure gas turbine 52 to the HRSG 40 which would bypass the low pressure gas turbine 61.
  • the main engine with the high pressure compressor 51 and high pressure gas turbine 52 is operated to drive the electric generator 55 with the high pressure gas turbine 52 exhaust going into the power or low pressure gas turbine 61 to drive the low pressure compressor 62.
  • the exhaust from the low pressure gas turbine 61 then flows into the HRSG 40 through line 64 to produce steam to drive the two steam turbines 36 and 37 that drive the second electric generator 38.
  • the low pressure compressed air from the low pressure compressor 62 flows into the inlet of the high pressure compressor 51 (as shown by the first dashed line in FIG. 5).
  • the 61 and the low pressure compressor 62 is operated at low speed and the exhaust from the high pressure gas turbine 52 flows into the HRSG 40 through the low pressure gas turbine 61 and line 64 to produce steam for the two steam turbines 36 and 37 that drive the second electric generator 38 and thus keep the parts of the HRSG hot for easy restart when the engine operates at higher loads.
  • Flow into the high pressure compressor 51 is reduced to 25% of the maximum flow.
  • the main engine (51, 52, 53) can go into a very low power mode.
  • the prior art power plants have a low power mode of 40% to 50% (with inlet guide vanes in the compressor) of peak load.
  • the present invention can go down to 15% of peak load while keeping the steam temperature temporarily high of the power plant hot (by passing the hot gas flow through) for easy restart when higher power output is required.
  • the inter-cooler 65 can also include water injection to cool the low pressure compressed air.
  • a means for controlling the engine is necessary in order to reduce low spool rotor speed without shutting off completely, while ensuring stable operation of the low pressure compressor 62 and high pressure compressor 51. Without a safe control strategy, part power aerodynamic mismatching of the compressor can lead to compressor stall and/or surge, which is to be avoided for safety and durability concerns.
  • a convenient way to control the low rotor speed while correctly matching the compressors aerodynamically is by means of a variable low pressure turbine vane 63.
  • variable low pressure turbine vane 63 Closing the variable low pressure turbine vane 63 at part power conditions reduces the flow area and flow capacity of the low pressure turbine 61, which subsequently results in a reduction of low pressure spool (61, 62) rotational speed. This reduction in rotor speed reduces the air flow through the low pressure compressor 62 which provides a better aerodynamic match with the high pressure compressor 51 at part power.
  • FIG. 6 The embodiment of FIG. 6 is similar to that in FIG. 5 but with the addition of cooling air used for the high pressure turbine 52 stator vanes 76 that are then discharged into the combustor 53 of the high spool.
  • some of the compressed air discharged from the low pressure compressor 62 can be passed through an intercooler 71, through a cooling air compressor 72 driven by a motor 73, through line 75, and then used to cool the stator vanes 76 in the high pressure gas turbine 52 of the high speed spool.
  • This cooling air is then passed through line 77 and is discharged into the inlet of the combustor 53 and combined with the compressed air from the high pressure compressor 51 for combustion with a fuel to produce the hot gas flow used to drive the two gas turbines 52 and 61.
  • the amount of compression produced by the cooling air compressor 72 is sufficient to overcome the pressure losses from cooling the stator vanes 76 and to maintain sufficient over-pressure to flow into the combustor 53.
  • the LPC 62 flow not passed to the intercooler 71 is passed through an optional intercooler 65 through line 67 to the high pressure compressor 51 inlet.
  • FIG. 7 is similar to the embodiment in FIG. 6, but with only one intercooler 65 used to cool the compressed air going into the high pressure compressor 51 and the stator vanes 76 of the high pressure turbine 52.
  • a cooling air compressor 72 driven by a motor 73 is used to increase the pressure of the low pressure compressor 62 high enough to pass through the stator vanes 76 with enough pressure to flow into the combustor 53 at around the same pressure as the high pressure compressor outlet for discharged into the combustor 53.
  • the compressed air used to cool the stator vanes 76 in the high pressure turbine 52 is injected into the combustor 53.
  • a diffuser 101 is positioned between an outlet of the high pressure compressor 51 and an inlet of the combustor 53 that diffuses the compressed air flow.
  • the cooling air 104 from the stator vanes and the cooling air 105 from the rotor blades of the high pressure turbine 52 is discharged into the diffuser 101 to merge with the compressed air from the high pressure compressor 81 prior to entering the combustor 53.
  • the cooling air from the stator vanes 76 is discharged into an outer plenum 102 surrounding the diffuser 101 that directs the cooling air flow in a direction 107 parallel to the discharged compressed air 106 from the compressor 81.
  • the cooling air from the rotor blades is discharged into an inner plenum 103 where the cooling air flows in a direction 107 parallel to the discharged compressed air 106 from the compressor.
  • the cooling air from the two plenums 102 and 103 is accelerated to a velocity equal to or greater than the velocity of the compressed air 106 from the compressor in order to prevent the boundary layer from forming.
  • FIG. 11 shows a second embodiment of the diffuser 101 in which the cooling air flow from the stator vanes and the rotor blades (arrows 104 and 105, respectively) is discharged into the diffuser 101 from the two plenums 102 and 103 through an arrangement of film cooling holes 108.
  • FIG. 8 shows a cross sectional arrangement of a twin spool turbo-charged IGT for the present invention.
  • the low pressure turbine 61 has a variable area nozzle and is located within a flow case just behind or downstream of the exit from the HPT 52 so that the flow from the high pressure turbine 52 flows directly into the LPT 61 without loss.
  • the rotor shaft from the LPT 61 to the LPC 62 passes through the flow case that forms the exhaust for the LPT 61 hot gas and the inlet for the air into the LPC 62.
  • the LPC 62 is connected by the line 67 to an inlet of the HPC 51.
  • the high spool (with HPC 51, HPT 52, and combustor 53) directly drives an electric generator 55.
  • FIG. 9 shows an embodiment of the present invention in which the power plant can be used to drive a load 85 where the load can be an electric generator or a compressor or a screw propeller for a ship.
  • the power plant in FIG. 9 includes the high spool and the low spool like in previous embodiments, but with an intermediate pressure power turbine (IPPT) 84 that is driven by exhaust from the HPT to drive the load 85 through a free shaft (FS).
  • IPPT intermediate pressure power turbine
  • a high pressure compressor 81 is rotatably connected to a high pressure turbine 82 through a rotor with a combustor 83 located in between to form the high spool.
  • a low pressure turbine 91 is rotatably connected to a low pressure compressor 92 to form the low spool.
  • the LPT 91 includes variable inlet guide vanes or nozzles 93.
  • the high pressure compressor 81 also has multiple variable stator vanes (VSV).
  • An intermediate pressure power turbine (IPPT) 84 is located immediately downstream from the HPT 82 and is rotatably connected to the load 85 through a free shaft (FS) that passes through the inside of and rotates within the rotor shaft (RS) of the low spool.
  • a compressed air line 67 connects the outlet of the LPC 92 to an inlet of the HPC 81, and can include an intercooler 65.
  • a boost compressor 56 can be used to supply low pressure compressed air to the HPC 81 when the low spool (91, 92) is running low.
  • An optional HRSG 40 is connected to the LPT 91 exhaust through line 64 to convert the turbine exhaust into steam and drive the high pressure steam turbine 36 and the low pressure steam turbine 37 that both drive the electric generator 38.
  • the IPPT 84 and the HPT 82 are located within a case close to one another as are the LPT 61 and HPT 52 in FIG. 8.
  • the HRSG 40 might not be needed if the engine is used to propel a ship.
  • the twin spool IGT engine of FIG. 9 shows another novel arrangement which has many of the same attributes of FIGS. 5-7 embodiments.
  • the mechanical or generator load speed is allowed to operate independently from the gas turbine high pressure shaft speed via a low pressure shaft connected to the load. This independent load shaft speed attribute is usually most important for mechanical loads.
  • the FS (free shaft) is still free to slow down for improved part load performance and low turndown to 12% load.
  • the low pressure shaft is passed through the (ID) of the FS since the FS runs at low speed and higher radius compared to the HP shaft.
  • the HP shaft speed can remain high in this arrangement.
  • Options for the FIG. 9 power plant include: intercool the entire flow from the
  • a variable geometry HPC 81 is used to control speed along with the variable LPT vane 93.
  • FIG. 17 shows a twin spool turbo-charged IGT of the present invention that does not require an intercooler 65 for cooling the compressed air that is delivered to the stator vanes of the turbine like in the FIG. 9 embodiment.
  • the power turbine can be operated rotationally independent of the main core engine 121 that drives the electric generator 55, as opposed to the prior art twin spool aero engine shown in FIG. 16.
  • the high pressure spool and the low pressure spool operate together (FIG. 16 aero engine) because the hot gas stream from the combustor must flow through both turbines so that both compressors are driven.
  • the low pressure spool 122 can operate at different speeds while the main core engine 121 (the high spool that drives the electric generator 55) can operate at a constant speed.
  • FIG. 18 shows an illustration of an embodiment of the power plant of the present invention in which the dual flow high pressure compressor 130 is used.
  • the high pressure turbine 52 of the main engine drives the dual flow high pressure compressor 130 that has an inner flow path 133 separated from, but concentric with, an outer flow path 134, where the inner flow path 133 flows into the combustor 53 while the outer flow path flows into the stator vanes 76 for cooling thereof.
  • the compressed air from the LPC 62 is divided into a main flow through line 67 that flows into the inner flow path 133 of the dual flow high pressure compressor 130 and a smaller flow through line 131 (around 20%) that flows through an intercooler 65 to provide cooling.
  • This smaller and cooled compressed air flow through line 131 then flows into the outer flow path 134 of the dual flow high pressure compressor 130 and then to one or more rows of the stator vanes 76 of the HPT 52 to provide cooling of the stator vanes 76.
  • the inner and outer compressed air flow paths 133 and 134 are both axial flow paths.
  • the cooling air is then discharged into the combustor 53.
  • the cooling air from the LPC 62 used for cooling of the stator vanes 76 must be compressed further and cooled in order to adequately cool the stator vanes 76 and have enough pressure to pass through the stator vanes 76 and then flow into the combustor 53.
  • a separate compressor is not needed to further compress the air from the LPC 62 that is used for cooling the stator vanes 76.
  • FIG. 19 shows one embodiment of the dual flow high pressure compressor
  • Rotor blades 140 extend from the rotor 141 and stator vanes 145 extend from the stator or casing 139 (which may also be referred to as a stationary housing 139).
  • Each rotor blade 140 includes an inner airfoil 142 and an outer airfoil 144 with a shroud 143 separating the two flow paths formed by the inner and outer airfoils.
  • Each stator vane 145 also includes a shroud 143 to separate the inner air flow path from the outer air flow path.
  • a number of stages of blades 140 and vanes 145 are used to compress the air to the desired pressure.
  • a second dual flow high pressure compressor 146 located downstream from the first dual flow high pressure compressor 130 is used to further compress the air.
  • the first and second dual flow high pressure compressors 130 and 146 may collectively be referred to as a multiple stage compressor.
  • the rotor 141 includes a first rotor blade 152 on the inner flow path and a second compressor blade 151 on the outer flow path. More than one rotor blades 152 and compressor blades 151 may be used.
  • the second compressor blade(s) 151 in this embodiment is an outer centrifugal compressor that can increase the pressure of the outer flow path beyond the pressure in the inner flow path so that turbine stator vane 76 cooling can be performed with enough remaining pressure to dump the cooling air from the stator vanes back into the combustor 53.
  • the first rotor blade(s) 152 is an inner axial compressor that supplies compressed air directly to the combustor (53).
  • the first 130 and second 146 dual flow high pressure compressors are connected to the same rotor 141 and thus rotate together. Because around 20% of the total compressed air flow is used for cooling of the stator vanes 76 in the HPT 52, the outer flow path 134 in the FIGS. 19 and 20 embodiments are smaller such that approximately 20% of the total flow through the compressor flow in the outer flow path 134.
  • FIG. 21 shows a second embodiment of the dual flow high pressure compressor 130 of the present invention where the smaller flow path (which includes approximately 20% of the main flow) flows along the inner flow path 133. Passing the smaller air flow along the inner flow path 133 provides cooling of the rotor 141.
  • the inner flow path 133 extends further aft (and includes rotor blades 140 and stator vanes 145) than the outer flow path 134 because the inner flow path 133 must be at a higher pressure than the outer flow path 134, since the cooling air from the inner flow path 133 is used for cooling of the turbine stator vanes 76.
  • FIG. 22 shows an embodiment of rotor blades 140 used in the dual flow high pressure compressor 130 where the inner airfoil 142 includes one large blade that extends from the rotor 141 and the outer airfoil 144 includes a number of smaller blades extending from the shroud 143. Because the outer flow path 134 is smaller, more blades can be used for each stage to compress the air. This blade would be used in the dual flow high pressure compressor 130 of FIGS. 19 and 20, for example.
  • FIG. 23 shows an embodiment of the rotor blades 140 used in the dual flow high pressure compressor 130 of FIG. 21, for example, where the inner airfoil 142 includes a number of smaller blades in the inner flow path 133 and the outer airfoil 144 includes a larger blade in the outer flow path 134.
  • the shroud 143 separates the two flow paths 133, 134.
  • the inner airfoil 142 can include multiple blades in the smaller inner flow path 133 to keep passage aspect ratios from getting too small.
  • One or more blades 140 can be used.
  • the FIG. 23 embodiment suffers from the issue that the smaller blades of the inner airfoil 142 must support the large blade of the outer airfoil 144 located radially outward.
  • this embodiment would allow for the compressed air used for cooling the stator vanes 76 to flow along the rotor 141 for additional cooling of the rotor 141.
  • one or more blades 140 can be used.
  • an industrial gas turbine engine for electrical power production includes: a high pressure spool with a dual flow high pressure compressor (130), a high pressure turbine (52), and a combustor (53) between the dual flow high pressure compressor (130) and the high pressure turbine (52), the high pressure turbine (52) having an air cooled airfoil (76); an electric generator (55) connected to the high pressure spool to produce electrical power; a low pressure spool with a low pressure compressor (62) and a low pressure turbine (61); the high pressure spool and the low pressure spool being capable of rotating independently; an outlet of the low pressure compressor (62) of the low pressure spool being connected to an inlet of the dual flow high pressure compressor (130) of the high pressure spool; the dual flow high pressure compressor (130) having a first flow path (133) to supply compressed air at a first pressure to the combustor (53); the dual flow high pressure compressor (130) having a second flow path (134) concentric with the first flow path (133) to supply compressed air
  • the dual flow high pressure compressor (130) includes multiple rows of rotor blades (140) and stator vanes (145) in which each rotor blade (140) and stator vane (145) includes a shroud (143) separating the first flow path (133) from the second flow path (134), the first flow path (133) being an inner compressed air flow path and the second flow path (134) being an outer compressed air flow path.
  • the industrial gas turbine engine further includes a second dual flow compressor (146) downstream from a first dual flow compressor (130), the second dual flow high pressure compressor (146) including an inner axial compressor (152) and an outer centrifugal compressor (151) both connected to a common rotor (141).
  • the dual flow high pressure compressor (130) includes a second dual flow high pressure compressor (146) downstream from a first dual flow high pressure compressor (130); the first dual flow high pressure compressor (130) is an axial flow compressor with an inner compressed air flow path (133) and an outer compressed air flow path (134); the second dual flow high pressure compressor (146) is an axial flow compressor downstream from the inner compressed air flow path (133); and the first dual flow high pressure compressor (130) and second dual flow high pressure compressor (146) are connected to a common rotor (141).
  • the air cooled airfoil is a row of turbine stator vanes (76).
  • the outer centrifugal compressor (151) of the second dual flow high pressure compressor (146) supplies the higher pressure compressed air to the air cooled airfoil (76), and the inner axial flow compressor (152) of the second dual flow high pressure compressor (146) supplies compressed air directly to the combustor (53).
  • the inner compressed air flow path (133) supplies compressed air to the air cooled turbine airfoil (76), and the outer compressed air flow path (134) supplies compressed air directly to the combustor (53).
  • a multiple stage compressor for an industrial gas turbine engine includes: a rotor (141); a plurality of rows of rotor blades (140) extending from the rotor (141); a plurality of rows of stator vanes (145) extending from a stationary housing (139) of the multiple stage compressor; the rows of rotor blades (140) and rows of stator vanes (145) each having a shroud (143) to separate an inner compressed air flow path (133) from an outer compressed air flow path (134); and the outer compressed air flow path (134) makes up around 20% of the flow of the multiple stage compressor.
  • the inner compressed air flow path (133) and the outer compressed air flow path (134) are both axial flow paths.
  • the rotor (140), the plurality of rows of rotor blades (140), are the plurality of rows of stator vanes (145) are part of a first compressor (130), the multiple stage compressor further including: a second compressor (146) downstream from the first compressor (130); the first compressor (130) and the second compressor (146) are connected to a common rotor (141); and the second compressor (146) includes an axial flow inner compressed air flow path (133) and a centrifugal flow outer compressed air flow path (134).
  • a multiple stage compressor for an industrial gas turbine engine includes: a rotor (141); a plurality of rows of rotor blades (140) extending from the rotor (141); a plurality of rows of stator vanes (145) extending from a stationary housing (139) of the multiple stage compressor; the rows of rotor blades (140) and rows of stator vanes (145) each have a shroud (143) to separate the inner compressed air flow path (133) from the outer compressed air flow path (134); the inner compressed air flow path (133) makes up around 20% of the flow of the multiple stage compressor; a second compressor (146) downstream from a first compressor (130); the second compressor (146) is connected to the same rotor (141) as the first compressor (130); the second compressor (146) includes multiple rows of rotor blades (152) and stator vanes (151); and the second compressor (146) forms a continuation of the inner compressed air flow path (133) of the first compressor (130) to further compress the air from the inner

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Abstract

L'invention concerne un moteur à turbine à gaz industriel pour la production d'énergie électrique comprenant une bobine haute pression et une bobine basse pression, la bobine basse pression pouvant être actionnée d'un mode de pleine puissance à un mode de puissance nulle lorsqu'elle est complètement coupée, la bobine basse pression étant actionnée à une demande électrique élevée pour fournir de l'air comprimé au compresseur haute pression de la bobine haute pression et l'échappement de turbine étant utilisé pour entraîner un second générateur électrique à partir de la vapeur produite dans un générateur de vapeur à récupération de chaleur. La bobine haute pression comprend un compresseur haute pression ayant un trajet d'écoulement d'air comprimé interne et un trajet d'écoulement d'air comprimé externe dans lequel une pression plus élevée fournit un refroidissement à une aube de turbine qui est ensuite déchargé dans une chambre de combustion du moteur.
PCT/US2017/035348 2017-06-01 2017-06-01 Moteur à turbine à gaz industriel à double corps à rapport de pression élevé avec compresseur à corps à double flux élevé Ceased WO2018222192A1 (fr)

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Cited By (1)

* Cited by examiner, † Cited by third party
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CN114151194A (zh) * 2022-02-10 2022-03-08 成都中科翼能科技有限公司 一种燃气轮机双层传力装置

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US5697208A (en) * 1995-06-02 1997-12-16 Solar Turbines Incorporated Turbine cooling cycle
US6250061B1 (en) * 1999-03-02 2001-06-26 General Electric Company Compressor system and methods for reducing cooling airflow
WO2003018960A1 (fr) * 2001-08-29 2003-03-06 Pratt & Whitney Canada Corp. Compresseur à double courant
WO2016127187A2 (fr) * 2015-02-06 2016-08-11 Florida Turbine Technologies, Inc. Appareil et processus d'adaptation d'une centrale électrique à combiné
US20160305261A1 (en) * 2015-04-16 2016-10-20 John A Orosa High pressure ratio twin spool industrial gas turbine engine with dual flow high spool compressor

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Publication number Priority date Publication date Assignee Title
US5697208A (en) * 1995-06-02 1997-12-16 Solar Turbines Incorporated Turbine cooling cycle
US6250061B1 (en) * 1999-03-02 2001-06-26 General Electric Company Compressor system and methods for reducing cooling airflow
WO2003018960A1 (fr) * 2001-08-29 2003-03-06 Pratt & Whitney Canada Corp. Compresseur à double courant
WO2016127187A2 (fr) * 2015-02-06 2016-08-11 Florida Turbine Technologies, Inc. Appareil et processus d'adaptation d'une centrale électrique à combiné
US20160305261A1 (en) * 2015-04-16 2016-10-20 John A Orosa High pressure ratio twin spool industrial gas turbine engine with dual flow high spool compressor

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114151194A (zh) * 2022-02-10 2022-03-08 成都中科翼能科技有限公司 一种燃气轮机双层传力装置

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