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
• • 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
  • F23R3/10—Air inlet arrangements for primary air

Definitions

• This disclosure relates generally to a turbine engine and, more particularly, to a fuel nozzle for the turbine engine.
• a gas turbine engine includes one or more fuel nozzles for injecting fuel into a combustor for combustion.
• fuel nozzles for injecting fuel into a combustor for combustion.
• Various types of fuel nozzles are known in the art. While these known fuel nozzles have various benefits, there is still room in the art for improvement.
• an apparatus for a powerplant that includes a fuel nozzle.
• the fuel nozzle extends longitudinally in a first longitudinal direction along a nozzle centerline to a distal end.
• the fuel nozzle includes a fuel circuit and an air circuit.
• the fuel circuit includes a fuel cavity, a plurality of first fuel passages and a plurality of second fuel passages.
• the first fuel passages respectively extend within the fuel nozzle from the fuel cavity to a plurality of first fuel outlets disposed at the distal end of the fuel nozzle.
• the first fuel outlets are arranged circumferentially about the nozzle centerline in a first fuel outlet array.
• the second fuel passages respectively extend within the fuel nozzle from the fuel cavity to a plurality of second fuel outlets disposed at the distal end of the fuel nozzle.
• the second fuel outlets are arranged circumferentially about the nozzle centerline in a second fuel outlet array radially outboard of the first fuel outlet array.
• the air circuit includes a plurality of air passages that respectively extend within the fuel nozzle to a plurality of air outlets disposed at the distal end of the fuel nozzle.
• the air outlets are arranged circumferentially about the nozzle centerline in an air outlet array radially outboard of the second fuel outlet array.
• a powerplant that includes a fuel nozzle.
• the fuel nozzle extends longitudinally in a first longitudinal direction along a nozzle centerline to a distal end.
• the fuel nozzle includes a nozzle face, a plurality of first fuel passages and a plurality of air passages.
• the nozzle face is disposed at the distal end of the fuel nozzle and extends circumferentially around the nozzle centerline.
• the nozzle face has a concave sectional geometry in a reference plane parallel to the nozzle centerline.
• the first fuel passages respectively extend within the fuel nozzle to a plurality of first fuel outlets formed in the nozzle face.
• the first fuel outlets are arranged circumferentially around the nozzle centerline in a first fuel outlet array.
• the air passages respectively extend within the fuel nozzle to a plurality of air outlets formed in the nozzle face.
• the air outlets are arranged circumferentially around the nozzle centerline in an air outlet array.
• the air outlet array circumscribes the first fuel outlet array.
• a powerplant that includes a fuel nozzle.
• the fuel nozzle extends longitudinally in a first longitudinal direction along a nozzle centerline to a distal end.
• the fuel nozzle includes a nozzle face, a fuel cavity, a plurality of first fuel passages and a plurality of air passages.
• the nozzle face is disposed at the distal end of the fuel nozzle and extends circumferentially around the nozzle centerline.
• the fuel cavity extends circumferentially around the nozzle centerline within the fuel nozzle.
• the first fuel passages respectively extend within the fuel nozzle from the fuel cavity to a plurality of first fuel outlets formed in the nozzle face.
• a centerline of each of the first fuel passages have a trajectory which projects radially outward away from the nozzle centerline in the first longitudinal direction.
• the air passages respectively extend within the fuel nozzle to a plurality of air outlets formed in the nozzle face. The air outlets are located radially outboard of the first fuel outlets.
• a centerline of each of the air passages have a trajectory which projects radially inwards towards the nozzle centerline in the first longitudinal direction.
• the fuel nozzle may also include a plurality of second fuel passages.
• the second fuel passages may respectively extend within the fuel nozzle to a plurality of second fuel outlets formed in the nozzle face.
• the second fuel outlets may be arranged circumferentially around the nozzle centerline in a second fuel outlet array.
• the second fuel outlet array may circumscribe the first fuel outlet array.
• the air outlet array may circumscribe the second fuel outlet array.
• the fuel nozzle may also include a nozzle face disposed at the distal end of the fuel nozzle.
• the first fuel outlets, the second fuel outlets and the air outlets may be located in the nozzle face.
• the nozzle face may be configured as or otherwise include a concave annular surface.
• the first fuel outlets and the second fuel outlets may be disposed in annular section of the nozzle face which slopes radially inward towards the nozzle centerline as the annular section of the nozzle face extends longitudinally along the nozzle centerline in the first longitudinal direction.
• a centerline of a first of the air passages may be within ten degrees of parallel of the annular section of the nozzle face radially between the first of the air passages and the nozzle centerline.
• the annular section of the nozzle face may have a straight line geometry in a reference plane parallel to the nozzle centerline.
• the air outlets may be disposed in an annular section of the nozzle face which slopes radially inward towards the nozzle centerline as the annular section of the nozzle face extends longitudinally along the nozzle centerline in a second longitudinal direction opposite the first longitudinal direction.
• the annular section of the nozzle face may have a curved concave geometry in a reference plane parallel to the nozzle centerline.
• a centerline of a first of the first fuel passages may have a trajectory which projects radially outward away from the nozzle centerline in the first longitudinal direction.
• a centerline of a first of the second fuel passages may have as a trajectory which projects radially outward away from the nozzle centerline in the first longitudinal direction.
• a centerline of a first of the plurality of air passages may have a trajectory which projects radially inward towards the nozzle centerline in the first longitudinal direction.
• the fuel nozzle may be configured to output a first fuel flow from the first fuel outlets swirling in a first circumferential direction about the nozzle centerline.
• the fuel nozzle may be configured to output a second fuel flow from the second fuel outlets swirling in the first circumferential direction about the nozzle centerline.
• the fuel nozzle may be configured to output an airflow from the air outlets swirling in the first circumferential direction about the nozzle centerline.
• the fuel nozzle may be configured to output an airflow from the air outlets swirling in a second circumferential direction about the nozzle centerline which is opposite the first circumferential direction.
• a first of the first fuel outlets may be circumferentially aligned with a first of the second fuel outlets about the nozzle centerline.
• a first of the first fuel outlets may be positioned circumferentially between an adjacent pair of the second fuel outlets about the nozzle centerline.
• the fuel circuit may also include a plurality of third fuel passages.
• the third fuel passages may respectively extend within the fuel nozzle from the fuel cavity to a plurality of third fuel outlets disposed at the distal end of the fuel nozzle.
• the third fuel outlets may be arranged circumferentially about the nozzle centerline in a third fuel outlet array radially outboard of the second fuel outlet array and radially inboard of the air outlet array.
• the apparatus may also include a fuel delivery system comprising a gaseous fuel source.
• the fuel delivery system may be configured to deliver gaseous fuel from the gaseous fuel source to the fuel nozzle for flowing out of the fuel nozzle through the first fuel outlets and/or the second fuel outlets.
• the present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof.
• FIG. 1 illustrates a powerplant 20 for an aircraft.
• the aircraft may be an airplane, a helicopter, a drone (e.g., an unmanned aerial vehicle (UAV)) or any other manned or unmanned aerial vehicle or system.
• the powerplant 20 may be configured as, or otherwise included as part of, a propulsion system for the aircraft.
• the powerplant 20 may also or alternatively be configured as, or otherwise included as part of, an electrical power system for the aircraft.
• the present disclosure is not limited to aircraft applications.
• the powerplant 20, for example may alternatively be configured as, or otherwise included as part of, an electrical power system for ground-based operation (e.g., an industrial powerplant), for aquatic operation, or otherwise.
• the powerplant 20 is described below as an aircraft powerplant.
• the aircraft powerplant 20 of FIG. 1 includes a mechanical load 22 and a core 24 of a gas turbine engine 26, where the engine core 24 is configured to power operation of the mechanical load 22.
• the aircraft powerplant 20 also includes a fuel delivery system 28 for the turbine engine 26 and its engine core 24.
• the mechanical load 22 may be configured as or otherwise include a rotor 30 mechanically driven by the engine core 24.
• This driven rotor 30 may be a bladed propulsor rotor for the aircraft propulsion system.
• the propulsor rotor may be a ducted propulsor rotor or an open propulsor rotor; e.g., an un-ducted propulsor rotor.
• the turbine engine 26 is a turbofan engine
• the ducted propulsor rotor may be a fan rotor 32.
• the open propulsor rotor may be a propeller rotor.
• the open propulsor rotor may be a rotorcraft rotor such as a helicopter main rotor or a helicopter tail rotor.
• the driven rotor 30 may be configured as a generator rotor of an electric power generator for the aircraft electrical power system; e.g., an auxiliary power unit (APU) system.
• APU auxiliary power unit
• the present disclosure is not limited to the foregoing exemplary mechanical loads nor to the foregoing exemplary turbine engines.
• the turbine engine 26, for example may alternatively be configured as a turbojet engine, a propfan engine, a pusher fan engine or any other type of turbine engine operable to power the operation of the mechanical load 22.
• the mechanical load 22 is described below as a fan section 34 of the turbine engine 26
• the driven rotor 30 is described below as the fan rotor 32 within the fan section 34.
• the turbine engine 26 extends axially along an axis 36 from a forward, upstream end of the turbine engine 26 to an aft, downstream end of the turbine engine 26.
• this axis 36 may be a centerline axis of the turbine engine 26 and its members 24 and 32.
• the axis 36 may also be a rotational axis of one or more members of the turbine engine 26 and its engine core 24 including the fan rotor 32 - the driven rotor 30.
• the turbine engine 26 of FIG. 1 includes the fan section 34, a compressor section 38, a combustor section 39 and a turbine section 40.
• the turbine section 40 of FIG. 1 includes a high pressure turbine (HPT) section 40A and a low pressure turbine (LPT) section 40B, which LPT section 40B of FIG. 1 is a power turbine (PT) section for driving rotation of the fan rotor 32.
• HPPT high pressure turbine
• LPT low pressure turbine
• the compressor section 38 includes a compressor rotor 42.
• the HPT section 40A includes a high pressure turbine (HPT) rotor 44.
• the LPT section 40B includes a low pressure turbine (LPT) rotor 46.
• the fan rotor 32, the compressor rotor 42, the HPT rotor 44 and the LPT rotor 46 each respectively include one or more arrays (e.g., stages) of rotor blades, where the rotor blades in each array are arranged circumferentially around and are connected to a respective rotor disk or hub.
• the rotor blades in each array for example, may be formed integral with or mechanically fastened, welded, brazed and/or otherwise attached to the respective rotor disk and/or hub.
• the compressor rotor 42 is coupled to and rotatable with the HPT rotor 44.
• the compressor rotor 42 of FIG. 1 for example, is connected to the HPT rotor 44 by a high speed shaft 48. At least (or only) the compressor rotor 42, the HPT rotor 44 and the high speed shaft 48 collectively form a high speed rotating assembly 50; e.g., a high speed spool of the engine core 24.
• the LPT rotor 46 of FIG. 1 is connected to a low speed shaft 52. At least (or only) the LPT rotor 46 and the low speed shaft 52 collectively form a low speed rotating assembly 54; e.g., a low speed spool / a power turbine spool of the engine core 24.
• This low speed rotating assembly 54 is further coupled to the fan rotor 32 - the driven rotor 30 - through a drivetrain 56.
• This drivetrain 56 may be configured as a geared drivetrain, where a geartrain 58 (e.g., a transmission, a speed change device, an epicyclic geartrain, etc.) is disposed between and operatively couples the fan rotor 32 to the low speed rotating assembly 54 and its LPT rotor 46.
• the fan rotor 32 may rotate at a different (e.g., slower) rotational velocity than the low speed rotating assembly 54 and its LPT rotor 46.
• the drivetrain 56 may alternatively be configured as a direct drive drivetrain, where the geartrain 58 is omitted.
• each of the rotating assemblies 50, 54 and its members as well as the fan rotor 32 may be rotatable about the axis 36.
• the turbine engine 26 of FIG. 1 includes a (e.g., annular) core flowpath 60 and a (e.g., annular) bypass flowpath 62.
• the bypass flowpath 62 is a ducted flowpath within the aircraft powerplant 20 and its turbine engine 26.
• the bypass flowpath 62 may alternatively be an open flowpath where the driven rotor 30 is alternatively configured as the open propulsor rotor, or the bypass flowpath 62 may be omitted where the driven rotor 30 is alternatively configured as the generator rotor.
• the core flowpath 60 extends within the turbine engine 26 and its engine core 24 from an airflow inlet 64 into the core flowpath 60 to a combustion products exhaust 66 from the core flowpath 60.
• the core flowpath 60 extends from the core inlet 64, sequentially through the compressor section 38, the combustor section 39, the HPT section 40A and the LPT section 40B, to the core exhaust 66.
• the bypass flowpath 62 of FIG. 1 extends outside of the engine core 24 thereby bypassing the engine core 24 and its engine sections 38-40B.
• air is directed across the fan rotor 32 (e.g., the propulsor rotor) and into the engine core 24 through the core inlet 64.
• This air entering the core flowpath 60 may be referred to as core air.
• the core air is compressed by the compressor rotor 42 and directed into a combustion chamber 68 (e.g., an annular combustion chamber) within a combustor 70 (e.g., an annular combustor) of the combustor section 39.
• Fuel is injected into the combustion chamber 68 by one or more fuel injectors 72 and mixed with the compressed core air to provide a fuel-air mixture.
• This fuel-air mixture is ignited and combustion products thereof flow through and sequentially drive rotation of the HPT rotor 44 and the LPT rotor 46.
• the rotation of the HPT rotor 44 drives rotation of the compressor rotor 42 and, thus, the compression of the air received from the core inlet 64.
• the rotation of the LPT rotor 46 drives rotation of the fan rotor 32 - the driven rotor 30.
• the rotation of the fan rotor 32 propels some of the air flow thereacross (e.g., the air not entering the engine core 24) through the bypass flowpath 62 to provide engine thrust.
• the driven rotor 30 is alternatively configured as the open propulsor rotor
• the rotation of this open propulsor rotor may propel air outside of the aircraft powerplant 20 and its turbine engine 26.
• the driven rotor 30 is alternatively configured as the generator rotor
• the rotation of this generator rotor may facilitate generation of electricity.
• the fuel delivery system 28 is configured to deliver the fuel to the combustor 70 for combustion as described above.
• the fuel delivered by the fuel delivery system 28 is a gaseous fuel.
• the fuel delivery system 28 of FIG. 2 for example, includes the one or more fuel injectors 72, a gaseous fuel source 74 and a gaseous fuel manifold 76.
• the fuel injectors 72 of FIG. 2 are arranged and may be equispaced circumferentially about the axis 36 in an annular array; e.g., a circular array.
• each of the fuel injectors 72 may extend from an engine case 78, across a diffuser plenum 80 surrounding the combustor 70, to a wall 82 of the combustor 70.
• the combustor wall 82 may be a sidewall of the combustor 70 or a bulkhead of the combustor 70 depending on the specific combustor configuration and/or fuel injector placement.
• Each of the fuel injectors 72 includes a showerhead fuel nozzle 84 mated with the combustor wall 82.
• the fuel nozzle 84 of FIG. 3 projects through (or partially into) a port 86 in the combustor wall 82.
• the fuel nozzle 84 extends longitudinally in a first longitudinal direction along a longitudinal centerline 88 of the fuel nozzle 84 to a distal end 90 (e.g., a tip) of the fuel nozzle 84.
• the fuel nozzle 84 of FIG. 4 projects longitudinally along its nozzle centerline 88 through the respective combustor wall port 86 (see FIG. 3 ) to the nozzle distal end 90, and the nozzle distal end 90 is located within (or adjacent) the combustion chamber 68.
• the fuel nozzle 84 of FIG. 4 includes a concave nozzle face 92, a gaseous fuel circuit 94 and an air circuit 96. This fuel nozzle 84 may also include a center body section 98 (see dashed line).
• the center body section 98 may be configured to provide the fuel nozzle 84 with one or more additional fuel circuits (e.g., a central pilot fuel circuit, an intermediate annular fuel circuit, etc.) and/or at least one additional air circuit (e.g., an inner annular air circuit, a central air blast air circuit, etc.).
• the center body section fuel circuit(s) may receive the gaseous fuel from the same gaseous fuel source as the gaseous fuel circuit 94.
• one or more of the center body section fuel circuit(s) may receive another gaseous or liquid fuel from another fuel source.
• the center body section air circuit may receive the compressed core air from the same source as the air circuit 96.
• a port 99 to a central bore accommodating the center body section 98 may be plugged such that the fuel nozzle 84 only includes the single gaseous fuel circuit 94 and the single air circuit 96.
• the nozzle face 92 is located at (e.g., on, adjacent or proximate) the nozzle distal end 90.
• the nozzle face 92 of FIGS. 4 and 5 includes and is formed by a nozzle inner face surface 100 and a nozzle outer face surface 102.
• the nozzle face 92 and each of its face surfaces 100, 102 extends circumferentially about (e.g., completely around) the nozzle centerline 88.
• the nozzle face 92 and each of its face surfaces 100, 102 may thereby have a full-hoop (e.g., annular) geometry.
• the inner face surface 100 extends radially outward (radially away from the nozzle centerline 88) from an inner edge 104 of the nozzle face 92 to an inner periphery of the outer face surface 102.
• the nozzle face inner edge 104 of FIG. 4 forms the port 99 to the central bore for the center body section 98.
• the inner face surface 100 may have a convoluted (e.g., an inner convex-outer concave, S-shaped, etc.) sectional geometry when viewed in a first reference plane parallel with (e.g., including) the nozzle centerline 88.
• the inner face surface 100 of FIG. 4 for example, includes an annular inner section 106, an annular intermediate section 108 and an annular outer section 110.
• the surface inner section 106 extends radially outward from the nozzle face inner edge 104 to an inner periphery of the surface intermediate section 108, where the two surface sections 106 and 108 meet and are contiguous at an eased (e.g., chamfered, radiused) outside corner.
• the surface inner section 106 also extends longitudinally in the first longitudinal direction (towards the nozzle distal end 90 along the nozzle centerline 88) from the nozzle face inner edge 104 to the inner periphery of the surface intermediate section 108.
• the surface inner section 106 thereby has a radially sloped (e.g., divergent) geometry in the first longitudinal direction; e.g., the surface inner section 106 may be substantially frustoconical.
• the surface inner section 106 of FIG. 4 and, more particularly, a radial mean line of the surface inner section 106 is angularly offset from the nozzle centerline 88 by a non-zero offset angle 112.
• This inner section offset angle 112 may be an acute angle equal to or greater than sixty degrees (60°); e.g., between sixty degrees (60°) and eighty degrees (80°).
• the present disclosure is not limited to such an exemplary surface inner section arrangement.
• the inner section offset angle 112 may be less than sixty degrees (60°) for some select fuel nozzle configurations.
• the surface inner section 106 may be omitted such that the surface intermediate section 108 is an inner section of the inner face surface 100 which forms the face surface inner edge 104.
• the surface intermediate section 108 extends radially outward from an outer periphery of the surface inner section 106 to an inner periphery of the surface outer section 110, where the two surface sections 108 and 110 meet and are contiguous at an eased inside corner.
• the surface intermediate section 108 also extends longitudinally in a second longitudinal direction (away from the nozzle distal end 90 along the nozzle centerline 88, opposite the first longitudinal direction) from the outer periphery of the surface inner section 106 to the inner periphery of the surface outer section 110.
• the surface intermediate section 108 thereby has a radially sloped (e.g., convergent) geometry in the first longitudinal direction; e.g., the surface intermediate section 108 may be substantially frustoconical.
• This surface intermediate section 108 may have a completely or substantially straight line sectional geometry when viewed in the first reference plane.
• the surface intermediate section 108 of FIG. 4 and, more particularly, a radial mean line of the surface intermediate section 108 is angularly offset from the nozzle centerline 88 by a non-zero offset angle 114.
• This intermediate section offset angle 114 may be an acute angle equal to or greater than forty-five degrees (45°) or sixty degrees (60°), for example up to seventy-five degrees (75°).
• the present disclosure is not limited to such an exemplary surface inner section arrangement.
• the surface intermediate section 108 may alternatively have a non-straight line sectional geometry (e.g., a slightly curved, concave and/or convex sectional geometry) for some select fuel nozzle configurations.
• the surface outer section 110 extends radially outward from an outer periphery of the surface intermediate section 108 to an inner periphery of the outer face surface 102, where the two face surfaces 100 and 102 meet and are contiguous at a (e.g., sharp, pointed) outside corner.
• the surface outer section 110 also extends longitudinally in the first longitudinal direction from the outer periphery of the surface intermediate section 108 to the inner periphery of the outer face surface 102.
• the surface outer section 110 thereby has a radially sloped (e.g., divergent) geometry in the first longitudinal direction.
• This surface outer section 110 may have a curved (e.g., concave, partially circular, partially elliptical, etc.) sectional geometry when viewed in the first reference plane.
• a radial chord of the surface outer section 110 is angularly offset from the nozzle centerline 88 by a non-zero offset angle 116.
• This outer section offset angle 116 may be an acute angle between forty-five degrees (45°) or eighty degrees (80°).
• the present disclosure is not limited to such an exemplary surface outer section arrangement.
• the surface outer section 110 for example, may alternatively have a substantially straight line sectional geometry for some select fuel nozzle configurations.
• the outer face surface 102 extends radially outward from an outer periphery of the inner face surface 100 to an outer edge 118 of the nozzle face 92.
• the outer face surface 102 also extends longitudinally in the first longitudinal direction from the outer periphery of the inner face surface 100 to the face surface outer edge 118.
• the outer face surface 102 thereby has a radially sloped (e.g., divergent) geometry in the first longitudinal direction; e.g., the outer face surface 102 may be substantially frustoconical.
• This outer face surface 102 may have a completely or substantially straight line sectional geometry when viewed in the first reference plane.
• This outer face surface offset angle 120 may be an acute angle equal to or greater than sixty degrees (60°), seventy degrees (70°) or eighty degrees (80°).
• the present disclosure is not limited to such an exemplary outer face surface arrangement.
• the outer face surface 102 may alternatively have a non-straight line sectional geometry (e.g., a slightly curved, concave and/or convex sectional geometry) for some select fuel nozzle configurations.
• the outer face surface 102 may be omitted such that the surface outer section 110 forms the face surface outer edge 118.
• the nozzle face 92 of FIG. 4 and its face surfaces 100 and 102 form a recess 122 in the fuel nozzle 84 at its nozzle distal end 90.
• This recess 122 projects longitudinally along the nozzle centerline 88 into the fuel nozzle 84 to the inner face surface 100 and the outer face surface 102.
• the recess 122 extends radially within the fuel nozzle 84 from (a) the surface intermediate section 108 to (b) the surface outer section 110 and the outer face surface 102.
• the recess 122 extends within the fuel nozzle 84 circumferentially about (e.g., completely around) the nozzle centerline 88, providing the recess 122 with a full-hoop (e.g., annular) geometry for example.
• the gaseous fuel circuit 94 of FIG. 4 includes a fuel gallery 124, one or more intermediate fuel passages 126, a fuel cavity 128 and one or more sets of outlet fuel passages 130A-D (generally referred to as "130"); see also FIG. 5 .
• the fuel gallery 124 extends longitudinally within the fuel nozzle 84 between opposing longitudinally sides of the fuel gallery 124.
• the fuel gallery 124 extends radially within the fuel nozzle 84 between an inner side of the fuel gallery 124 and an outer side of the fuel gallery 124.
• the fuel gallery 124 extends circumferentially about (e.g., completely around, or substantially around) the nozzle centerline 88 within the fuel nozzle 84.
• the fuel gallery 124 may thereby have a full-hoop (e.g., annular) geometry, or a substantially full-hoop geometry.
• the intermediate fuel passages 126 are arranged and may be equispaced circumferentially about the nozzle centerline 88 in an annular array; e.g., a circular array. Each of these intermediate fuel passages 126 extends within the fuel nozzle 84 from the fuel gallery 124 to the fuel cavity 128. Each of the intermediate fuel passages 126 thereby fluidly couples the fuel gallery 124 to the fuel cavity 128. More particularly, each of the intermediate fuel passages 126 extends longitudinally along the nozzle centerline 88 from the downstream end of the fuel gallery 124 to an upstream end 132 of the fuel cavity 128. Each of the intermediate fuel passages 126 is fluidly coupled to the fuel cavity 128 at the cavity upstream end 132.
• a centerline of each intermediate fuel passage 126 may be parallel with, or close to parallel with (e.g., within plus/minus five degrees (5°) of) the nozzle centerline 88, when viewed in the first reference plane.
• the fuel cavity 128 extends lengthwise within the fuel nozzle 84 from the cavity upstream end 132 to a downstream end 134 of the fuel cavity 128. More particularly, the fuel cavity 128 extends longitudinally in the first longitudinal direction from the cavity upstream end 132 to the cavity downstream end 134. The fuel cavity 128 also extends radially inward (radially towards the nozzle centerline 88) from the cavity upstream end 132 to the cavity downstream end 134. The fuel cavity 128 thereby has a radially sloped (e.g., convergent) geometry in the first longitudinal direction. The fuel cavity 128 extends widthwise (e.g., radially) from an inner surface 136 of the fuel cavity 128 to an outer surface 138 of the fuel cavity 128.
• Each cavity surface 136, 138 of FIG. 4 has a radially sloped geometry; e.g., each cavity surface 136, 138 may be a frustoconical surface.
• the cavity outer surface 138 radially converges towards the cavity inner surface 136 (when viewed in the first reference plane) as the fuel cavity 128 extends in the first longitudinal direction.
• the fuel cavity 128 extends circumferentially about (e.g., completely around) the nozzle centerline 88 within the fuel nozzle 84, providing the fuel cavity 128 with a full-hoop (e.g., annular) geometry.
• a centerline of any radial section of the fuel cavity 128 is angularly offset from the nozzle centerline 88 by a non-zero offset angle when viewed in the first reference plane.
• This cavity offset angle may be an acute angle equal to or greater than forty-five degrees (45°) or sixty degrees (60°).
• each outlet fuel passage 130A-D extends through a face wall 140 of the fuel nozzle 84 from an inlet 142A-D (generally referred to as "142") into the respective outlet fuel passage 130A-D to an outlet 144A-D (generally referred to as "144") from the respective outlet fuel passage 130A-D.
• the face wall 140 is between and forms (a) the cavity outer surface 138 and (b) the inner face surface sections 106 and 108.
• the fuel passage inlet 142 is disposed in and pierces the cavity outer surface 138.
• the fuel passage outlet 144 is disposed in and pierces the inner face surface 100 and its surface intermediate section 108.
• the outlet fuel passages 130 of FIG. 4 thereby fluidly couple the fuel cavity 128 to the combustion chamber 68 (through the recess 122), where the fuel cavity 128 fluidly couples the intermediate fuel passages 126 to the outlet fuel passages 130.
• the fuel passage outlets 144A-D (associated with each set of the outlet fuel passages 130A-D) are arranged and may be equispaced circumferentially about the nozzle centerline 88 in an annular array 146A-D (generally referred to as "146"); e.g., a circular array.
• 146 annular array
• the inner passage outlet array 146A is disposed at the inner periphery of the surface intermediate section 108.
• the outer passage outlet array 146D is disposed at the outer periphery of the surface intermediate section 108.
• the inner and outer intermediate passage outlet arrays 146B and 146C are disposed sequentially radially between the inner passage outlet array 146A and the outer passage outlet array 146D.
• the inner intermediate passage outlets 144B from the inner intermediate fuel passages 130B are thereby disposed radially outboard of the inner passage outlets 144A from the inner fuel passages 130A.
• the outer intermediate passage outlets 144C from the outer intermediate fuel passages 130C are disposed radially outboard of the inner intermediate passage outlets 144B from the inner intermediate fuel passages 130B.
• the outer passage outlets 144D from the outer fuel passages 130D are disposed radially outboard of the outer intermediate passage outlets 144C from the outer intermediate fuel passages 130C.
• Some or all of the fuel passage outlets 144 (e.g., 144A) in a respective array may each be circumferentially aligned with a respective fuel passage outlet 144 (e.g., 144D) in another respective array (e.g., 146D).
• some or all of the fuel passage outlets 144 (e.g., 144A or 144D) in a respective array may each be positioned circumferentially between a respective adjacent pair of fuel passage outlets 144 (e.g., 144B or 144C) in another respective array (e.g., 146B or 146C).
• a centerline 148A-D (generally referred to as "148") of each outlet fuel passage 130A-D, at least at the respective fuel passage outlet 144A-D, has a trajectory which projects radially outward away from the nozzle centerline 88 in the first longitudinal direction.
• the fuel nozzle 84 is thereby configured to direct a jet of the gaseous fuel out of the respective fuel passage outlet 144 in a radially outward direction along the respective trajectory into the combustion chamber 68 (see FIG. 4 ).
• the fuel passage centerline 148 and its trajectory may be perpendicular to, or within five degrees (5°) or ten degrees (10°) of perpendicular to, the inner face surface 100 and its surface intermediate section 108 when viewed in the first reference plane.
• This fuel passage centerline 148 and its trajectory may be angularly offset from the nozzle centerline 88 by between fifteen degrees (15°) and seventy-five degrees (75°).
• the fuel passage centerline 148 and its trajectory may be tangent to, or within five degrees (5°) or ten degrees (10°) of tangent to, a respective reference circle 150 coaxial with the nozzle centerline 88.
• the tangent direction may generally be in a first circumferential direction (e.g., a clockwise direction) about the nozzle centerline 88 when looking at the fuel nozzle 84 in the second longitudinal direction.
• the fuel nozzle 84 is thereby configured to swirl the gaseous fuel directed out from the respective fuel passage outlets 144 (see also FIG. 5 ) in the first circumferential direction about the nozzle centerline 88.
• FIG. 5 the fuel passage centerline 148 and its trajectory may be tangent to, or within five degrees (5°) or ten degrees (10°) of tangent to, a respective reference circle 150 coaxial with the nozzle centerline 88.
• the tangent direction may generally be in a first circumferential direction (e.g., a clockwise direction) about the nozzle center
• the tangent direction may generally be in a second circumferential direction (e.g., a counterclockwise direction) about the nozzle centerline 88 when looking at the fuel nozzle 84 in the second longitudinal direction.
• the fuel nozzle 84 is thereby configured to swirl the gaseous fuel directed out from the respective fuel passage outlets 144 (see also FIG. 5 ) in the second circumferential direction about the nozzle centerline 88.
• the fuel nozzle 84 may be configured to swirl the gaseous fuel output from all of the fuel passage outlets 144 in a common (the same) circumferential direction.
• the fuel nozzle 84 may be configured to swirl the gaseous fuel output from one or more arrays 146 of the fuel passage outlets 144 in a different direction than one or more other arrays 146 of the fuel passage outlets 144.
• the air circuit 96 is disposed radially outboard of the gaseous fuel circuit 94.
• the gaseous fuel circuit 94 and the center body section 98 of FIG. 4 are configured with a base 152 of the fuel nozzle 84.
• the air circuit 96 of FIG. 4 is configured with an outer peripheral wall 154 (e.g., a flange) of the fuel nozzle 84.
• This nozzle wall 154 is disposed at the nozzle distal end 90 and partially forms the nozzle face 92; e.g., the nozzle wall 154 forms the outer face surface 102 and an outer portion of the inner face surface 100 (e.g., the surface outer section 110).
• the nozzle wall 154 is connected to (e.g., formed integral with or otherwise attached to) the nozzle base 152.
• the nozzle wall 154 of FIG. 4 projects radially outward from the nozzle base 152 to an outer distal end of the nozzle wall 154.
• the air circuit 96 includes one or more circuit air passages 156.
• Each of these circuit air passages 156 extends diagonally inward through the nozzle wall 154 from an internal volume 158 adjacent a backside 160 of the nozzle wall 154 / an outer side 162 of the nozzle base 152 to the nozzle distal end 90 / the inner face surface 100 and its surface outer section 110. More particularly, each circuit air passage 156 of FIG. 4 extends longitudinally in the first longitudinal direction and radially inwards from an inlet 164 into the respective circuit air passage 156 to an outlet 166 from the respective circuit air passage 156. Each air passage inlet 164 is disposed in and pierces the backside 160 of the nozzle wall 154.
• Each air passage outlet 166 is disposed in and pierces the inner face surface 100 and its surface outer section 110.
• the air circuit 96 and its circuit air passages 156 thereby fluidly couple the internal volume 158 to the combustion chamber 68 (e.g., through the recess 122).
• the internal volume 158 may be a cavity within the respective fuel injector 72 which fluidly couples the diffuser plenum 80 to the air circuit 96.
• the internal volume 158 may be the diffuser plenum 80 itself or another air source within the turbine engine 26 and outside of the combustor 70.
• the air passage outlets 166 are arranged and may be equispaced circumferentially about the nozzle centerline 88 in an annular array; e.g., a circular array.
• the air passage outlet array is disposed radially outboard of the outer periphery of the inner face surface 100 and its surface outer section 110.
• the air passage outlets 166 from the circuit air passages 156 are thereby disposed radially outboard of all of the fuel passage outlets 144.
• a centerline 168 of each circuit air passage 156 at least at the respective air passage outlet 166, has a trajectory which projects radially inward towards the nozzle centerline 88 in the first longitudinal direction.
• the fuel nozzle 84 is thereby configured to direct a jet of the compressed core air out of the respective air passage outlet 166 in a radially inward direction along the respective trajectory into the combustion chamber 68.
• the air passage centerline 168 and its trajectory may be parallel with, or within five degrees (5°) or ten degrees (10°) of parallel with, the inner face surface 100 and its surface intermediate section 108 when viewed in the first reference plane.
• the compressed core air output from the circuit air passages 156 and their air passage outlets 166 may provide a buffer between gases within the combustion chamber 68 and the fuel passage outlets 144, which may reduce or prevent flame anchoring on the inner face surface 100 and the fuel passage outlets 144.
• the compressed core air output from the circuit air passages 156 and their air passage outlets 166 may also form a protective layer along the surface intermediate section 108 to minimize or prevent hot gas injection through fuel passage outlets 144.
• the air passage centerline 168 and its trajectory may be tangent to, or within five degrees (5°) or ten degrees (10°) of tangent to, a respective reference circle 170 coaxial with the nozzle centerline 88.
• the tangent direction may generally be in the first circumferential direction about the nozzle centerline 88 when looking at the fuel nozzle 84 in the second longitudinal direction.
• the fuel nozzle 84 is thereby configured to swirl the compressed core air directed out from the respective air passage outlets 166 (see also FIG. 5 ) in the first circumferential direction about the nozzle centerline 88.
• FIG. 5 the respective air passage outlets 166
• the tangent direction may generally be in the second circumferential direction about the nozzle centerline 88 when looking at the fuel nozzle 84 in the second longitudinal direction.
• the fuel nozzle 84 is thereby configured to swirl the compressed core air directed out from the respective air passage outlets 166 (see also FIG. 5 ) in the second circumferential direction about the nozzle centerline 88.
• the fuel nozzle 84 may be configured to swirl the compressed core air output from the air passage outlets 166 in a common (the same) circumferential direction as the gaseous fuel passages 130 from some or all of the fuel passage outlets 144.
• the fuel nozzle 84 may be configured to swirl the compressed core air output from the air passage outlets 166 in a different direction than the gaseous fuel passages 130 from some or all of the fuel passage outlets 144.
• the gaseous fuel source 74 includes a fuel reservoir 172, a fuel flow regulator 174 and a fuel evaporator 176.
• the fuel reservoir 172 is configured to store a quantity of fuel (e.g., in its liquid phase) before, during and/or after aircraft powerplant operation.
• the fuel reservoir 172 may be configured as or otherwise include a tank, a cylinder, a pressure vessel, a bladder or any other type of (e.g., insulated) fuel storage container.
• the fuel flow regulator 174 is configured to direct a flow of the fuel (e.g., in its liquid phase) from the fuel reservoir 172 to the fuel evaporator 176.
• the fuel flow regulator 174 may be configured as or otherwise include a fuel compressor, a fuel pump and/or a fuel valve (or valve system).
• the fuel evaporator 176 is configured to facilitate evaporation of the fuel from its liquid phase to a gaseous phase so as to output the gaseous fuel from an outlet 178 of the gaseous fuel source 74.
• This gaseous fuel source outlet 178 may be fluidly coupled to the gaseous fuel circuit 94 (see FIG. 4 ) in each of the fuel injectors 72 sequentially through the gaseous fuel manifold 76 and a respective gaseous fuel feed passage 180, which gaseous fuel feed passage 180 fluidly couples the gaseous fuel manifold 76 to the fuel gallery 124 (see FIG. 4 ) for example.
• the gaseous fuel may be a non-hydrocarbon gas.
• the gaseous fuel for example, may be or otherwise include hydrogen gas (H 2 gas), and the fuel stored within the fuel reservoir 172 may be liquid hydrogen (liquid H 2 ).
• the gaseous fuel is not limited to non-hydrocarbon gases.
• the gaseous fuel for example, may alternatively by or otherwise include gaseous methane (e.g., natural gas) or propane.
• gaseous methane e.g., natural gas
• propane propane
• use of the non-hydrocarbon gas such as the hydrogen gas may be particularly beneficial for reduction in emissions from the turbine engine 26 (see FIG. 1 ).
• the gaseous fuel may therefore be generally described below as the hydrogen gas for ease of description.
• each fuel nozzle 84 receives the gaseous fuel from the gaseous fuel source 74. Referring to FIG. 4 , this gaseous fuel is directed through the gaseous fuel circuit 94 in each fuel nozzle 84 for injection into the combustion chamber 68. Simultaneously, the air circuit 96 in each fuel nozzle 84 directs a portion of the compressed core air received from the internal volume 158 into the combustion chamber 68. This compressed core air may mix with the flow of the gaseous fuel (e.g., within the combustion chamber 68) to provide the fuel-air mixture for combustion. With the fuel nozzle arrangement of FIG. 4 , the gaseous fuel and the compressed core air may substantially mix downstream of the respective fuel nozzle 84 within the combustion chamber 68.
• the flame shape may also be provided by including at least (or only) one row in the showerhead array of the fuel passage outlets 144 for outputting hydrogen gas (or the like) since such gaseous fuel is relatively light and volatile.
• each fuel nozzle 84 may be formed as a monolithic body.
• Each fuel nozzle 84 may be cast, machined, additively manufactured and/or otherwise formed as a single unitary body. In other embodiments, however, each fuel nozzle 84 may alternatively be formed from a plurality of discretely formed members which are subsequently bonded, mechanically fastened and/or otherwise attached together to form the respective fuel nozzle 84.
• the circuit air passages 156 may be configured to direct the compressed core air along the inner face surface 100 and its surface intermediate section 108. In other embodiments, the circuit air passages 156 may be configured to direct the compressed core air to impinge against the inner face surface 100 and its surface intermediate section 108. With such an arrangement, the compressed core air may purge an area adjacent the inner face surface 100 and its surface intermediate section 108.
• the present disclosure is not limited thereto.
• the number of the arrays of the fuel passage outlets 144 may change based on the volatility of the gaseous fuel; e.g., hydrogen gas versus natural gas.
• the number of the arrays of the fuel passage outlets 144 may also or alternatively change based on flame size and shape parameters. Typically, however, the number of the arrays of the fuel passage outlets 144 will be between one (1) and four (4).
• An example of the fuel nozzle 84 with a single array of the fuel passage outlets 144 is shown in FIG. 9 .
• each outlet fuel passage 130 has a size 182 (e.g., a width, diameter, etc.) and a length 184.
• a ratio between the passage length 184 to the passage size 182 may range from 1: 1 to 3:1.
• the passage size 182 may range from 0.015 inches (0.38 mm) to 0.1 inches (2.54 mm).
• the passage size 182, in particular, is greater than 0.02 inches (0.51 mm) to facilitate deeper fuel penetration and a reduced risk of flame anchoring.
• a ratio of a number of the fuel passage outlets 144 in each array to a number of the air passage outlets 166 may range from 1:4 to 2:1.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Fuel-Injection Apparatus (AREA)

Applications Claiming Priority (1)

Publications (1)

Family

ID=95982393

Family Applications (1)

Country Status (2)

Citations (5)

• 2025
  • 2025-06-12 CA CA3276960A patent/CA3276960A1/en active Pending
  • 2025-06-13 EP EP25182836.4A patent/EP4664009A1/fr active Pending

Patent Citations (5)

Also Published As

Similar Documents

Legal Events