WO2023176570A1 - ガスタービン燃焼器及びガスタービン - Google Patents

ガスタービン燃焼器及びガスタービン Download PDF

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Publication number
WO2023176570A1
WO2023176570A1 PCT/JP2023/008476 JP2023008476W WO2023176570A1 WO 2023176570 A1 WO2023176570 A1 WO 2023176570A1 JP 2023008476 W JP2023008476 W JP 2023008476W WO 2023176570 A1 WO2023176570 A1 WO 2023176570A1
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WO
WIPO (PCT)
Prior art keywords
combustion
region
central axis
combustion tube
gas turbine
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/JP2023/008476
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
康弘 和田
一幾 阿部
啓太 柚木
祥平 沼田
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Mitsubishi Power Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd, Mitsubishi Power Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to US18/842,911 priority Critical patent/US20250180209A1/en
Priority to JP2024507776A priority patent/JP7736911B2/ja
Priority to CN202380025549.3A priority patent/CN118829827A/zh
Priority to DE112023000565.6T priority patent/DE112023000565T5/de
Priority to KR1020247030057A priority patent/KR20240149927A/ko
Publication of WO2023176570A1 publication Critical patent/WO2023176570A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/08—Purpose of the control system to produce clean exhaust gases
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants

Definitions

  • the present disclosure relates to gas turbine combustors and gas turbines.
  • This application claims priority based on Japanese Patent Application No. 2022-039453 filed with the Japan Patent Office on March 14, 2022, the contents of which are incorporated herein.
  • a combustor used in a gas turbine includes, for example, a fuel nozzle to which fuel can be supplied, and a combustion tube in which a combustion region through which combustion gas generated by combustion of fuel can flow is formed.
  • the fuel supplied from the fuel nozzle becomes fuel gas through combustion, and drives a turbine provided downstream through the combustion region of the combustion tube.
  • Patent Document 1 proposes that by providing a throttle member on the inner wall surface of the combustion cylinder of the combustor, combustion gas in the vicinity of the inner wall surface flows toward the center, thereby reducing high-temperature combustion. It is disclosed that it can be mixed with gas to promote combustion and suppress the generation of carbon monoxide.
  • At least one embodiment of the present disclosure provides a gas turbine combustor and a gas turbine that can suitably suppress the generation of carbon monoxide even during partial load operation of the gas turbine.
  • the purpose is to
  • a gas turbine combustor includes: a combustion cylinder having a combustion region formed inside thereof through which combustion gas generated by combustion of fuel can flow, and a combustion tube having a jetting portion forming a jetting port for the combustion gas formed at a downstream end; a plurality of throttle portions provided on an inner wall surface of the combustion tube at intervals in the circumferential direction and protruding toward the inside of the combustion tube; Equipped with The central axis of the combustion tube includes an upstream central axis that extends linearly in an upstream region of the combustion tube, and extends in a direction different from the direction in which the upstream central axis extends at the jetting portion.
  • the combustion tube is a virtual plane that is orthogonal to a virtual plane that includes the central axis from the upstream region to the jetting section, and includes the central axis from the upstream region to the jetting section. including a first area and a second area with a virtual plane as a boundary; A straight line extending the upstream central axis passes through the first region in the jetting portion, The total projected area of the constricted portions existing in the second region when viewed from the extending direction of the central axis is the sum of the projected areas of the constricted portions present in the first region viewed from the extending direction of the central axis. larger than the total projected area when
  • a gas turbine combustor according to at least one embodiment of the present disclosure, a combustion cylinder having a combustion region formed inside thereof through which combustion gas generated by combustion of fuel can flow, and a combustion tube having a jetting portion forming a jetting port for the combustion gas formed at a downstream end; a plurality of throttle portions provided on an inner wall surface of the combustion tube at intervals in the circumferential direction and protruding toward the inside of the combustion tube; Equipped with The central axis of the combustion tube includes an upstream central axis that extends linearly in an upstream region of the combustion tube, and extends in a direction different from the direction in which the upstream central axis extends at the jetting portion.
  • the combustion tube is a virtual plane that is orthogonal to a virtual plane that includes the central axis from the upstream region to the jetting section, and includes the central axis from the upstream region to the jetting section. including a first area and a second area with a virtual plane as a boundary;
  • the distance traced along the inner wall surface within the virtual plane from the position corresponding to the reference position on the upstream central axis line to the air outlet is longer in the second area than in the first area.
  • the total projected area of the constricted portions existing in the second region when viewed from the extending direction of the central axis is the sum of the projected areas of the constricted portions present in the first region viewed from the extending direction of the central axis. larger than the total projected area when
  • the gas turbine includes: a compressor that generates compressed air; A gas turbine combustor having the configuration of (1) or (2) above, a turbine rotationally driven by combustion gas generated by the gas turbine combustor; Equipped with
  • a gas turbine combustor and a gas turbine that can suitably suppress the generation of carbon monoxide even during partial load operation of the gas turbine.
  • FIG. 1 is a diagram schematically showing the configuration of a gas turbine according to an embodiment of the present disclosure.
  • FIG. 2 is a diagram for explaining the configuration around a combustor of a gas turbine.
  • FIG. 3 is a cross-sectional view showing an example of the shape of a combustion tube.
  • FIG. 3A is a schematic diagram showing the positional relationship between the shape of the inner wall surface and the shape of the inner circumferential surface of the outlet on the upstream side of the combustion tube shown in FIG. 3A.
  • FIG. 7 is a cross-sectional view showing another example of the shape of the combustion tube.
  • 4A is a schematic diagram showing the positional relationship between the shape of the inner wall surface and the shape of the inner circumferential surface of the outlet on the upstream side of the combustion tube shown in FIG.
  • FIG. FIG. 3 is a view of an example of a throttle member according to some embodiments having a throttle portion, viewed from the downstream side in the axial direction.
  • FIG. 6 is a perspective view of a portion of the aperture member shown in FIG. 5;
  • FIG. 3 is a schematic diagram of a combustion cylinder expanded in the circumferential direction to show an example of the arrangement position of a throttle portion.
  • FIG. 7 is a schematic view of the combustion cylinder expanded in the circumferential direction to show another example of the arrangement position of the throttle part.
  • FIG. 7 is a schematic diagram in which the combustion tube is expanded in the circumferential direction to show still another example of the arrangement position of the throttle portion.
  • FIG. 7 is a schematic diagram in which the combustion tube is expanded in the circumferential direction to show still another example of the arrangement position of the throttle portion.
  • FIG. 7 is a schematic diagram in which the combustion tube is expanded in the circumferential direction to show still another example of the arrangement position of the throttle portion.
  • FIG. 7 is a schematic diagram in which the combustion tube is expanded in the circumferential direction to show still another example of the arrangement position of the throttle portion.
  • FIG. 3B is a view taken along arrows VIII-VIII in FIG. 3A. It is a figure for showing an example of the composition for cooling a constriction part.
  • FIG. 6 is a diagram for explaining variations in the shape of the aperture part.
  • FIG. 6 is a diagram for explaining variations in the shape of the aperture part.
  • FIG. 6 is a diagram for explaining variations in the shape of the aperture part.
  • FIG. 6 is a diagram for explaining variations in the shape of the aperture part.
  • expressions such as “same,””equal,” and “homogeneous” that indicate that things are in an equal state do not only mean that things are exactly equal, but also have tolerances or differences in the degree to which the same function can be obtained. It also represents the existing state.
  • expressions expressing shapes such as squares and cylinders do not only refer to shapes such as squares and cylinders in a strict geometric sense, but also include uneven parts and chamfers to the extent that the same effect can be obtained. Shapes including parts, etc. shall also be expressed.
  • the expressions “comprising,”"comprising,””comprising,””containing,” or “having" one component are not exclusive expressions that exclude the presence of other components.
  • FIG. 1 is a diagram schematically showing the configuration of a gas turbine according to an embodiment of the present disclosure.
  • FIG. 2 is a diagram for explaining the configuration around the combustor of the gas turbine.
  • the gas turbine 1 As shown in FIG. 1, the gas turbine 1 according to the present embodiment includes a compressor 2, a combustor (gas turbine combustor) 3, and a turbine 4, and drives an external device such as a generator G. It is something to do. In the case of the gas turbine 1 for power generation, a generator G is connected to the rotor 5.
  • the compressor 2 takes in atmospheric air, which is external air, compresses it, and supplies the compressed air to one or more combustors 3 .
  • the combustor 3 uses air compressed by the compressor 2 to combust fuel supplied from the outside, thereby generating high-temperature gas (combustion gas).
  • a plurality of combustors 3 are arranged annularly around the rotor 5.
  • an oil fuel (liquid fuel) that is a flammable liquid is used as the fuel, but a gaseous fuel that is a flammable gas may be used as the fuel.
  • the turbine 4 generates rotational driving force by receiving the high-temperature combustion gas generated by the combustor 3, and outputs the generated rotational driving force to the compressor 2 and external equipment.
  • a combustor installation space 8 for the combustor 3 is provided within the vehicle compartment 7.
  • the combustor installation space 8 is located between the outlet of the compressor 2 on the axially upstream side and the inlet of the turbine 4 on the axially downstream side.
  • the combustor 3 is arranged in the combustor installation space 8, and compressed air flows into the combustor 3 from one end side of the combustor 3.
  • the combustor 3 is supplied with fuel from the outside, mixes the fuel and air, generates high-temperature combustion gas, and uses the combustion gas to rotate the turbine 4 on the downstream side.
  • the combustor 3 includes a nozzle section 10 and a combustion tube 20.
  • the combustion tube 20 includes an inner tube 12 and a transition tube 14. Note that the inner tube 12 and the tail tube 14 may be integrally formed.
  • the combustion tube 20 has a combustion chamber 18 inside thereof in which fuel injected from the main nozzle 64 and the pilot nozzle 54 is combusted. That is, the fuel is mixed with compressed air supplied from the compressor 2 in the combustion region within the combustion tube 20 and then combusted, thereby generating combustion gas. Combustion gas is supplied to the turbine 4 via the combustion tube 20.
  • the nozzle section 10 includes a pilot burner 50 and a plurality of main burners (premix combustion burners) 60.
  • the pilot burner 50 is arranged along the central axis AX of the combustion tube 20.
  • a plurality of main burners 60 are arranged so as to surround the pilot burner 50 and to be spaced apart from each other in the circumferential direction of the combustion tube 20 .
  • the pilot burner 50 includes a pilot nozzle 54 connected to a fuel port 52, a pilot nozzle tube 56 arranged to surround the pilot nozzle 54, and a swirler (not shown) provided around the outer periphery of the pilot nozzle 54. are doing.
  • the main burner 60 includes a main nozzle 64 connected to a fuel port 62, a main nozzle tube 66 arranged to surround the main nozzle 64, and a swirler (not shown) provided around the outer periphery of the main nozzle 64. are doing.
  • compressed air generated by the compressor 2 is supplied into the combustor installation space 8 and further flows into the main nozzle pipe 66 from the combustor installation space 8.
  • This compressed air and the fuel supplied from the fuel port 62 are premixed within the main nozzle tube 66.
  • the premixed gas mainly forms a swirling flow by a swirler (not shown) and flows into the inner cylinder 12.
  • the compressed air and the fuel injected from the pilot burner 50 through the fuel port 52 are mixed, ignited by a pilot flame (not shown), and combusted to generate combustion gas.
  • the premixed mixture that has flowed into the inner cylinder 12 from each main burner 60 is ignited and combusted. That is, the pilot flame generated by the pilot fuel injected from the pilot burner 50 can perform flame stabilization for stably burning the premixed mixture (premixed fuel) from the main burner 60.
  • upstream side the side where the fuel nozzle (pilot nozzle 54, main nozzle 64) is provided with respect to the combustion tube 20 described above is referred to as the upstream side
  • downstream side the side where the combustion tube 20 is provided with the fuel nozzle as a reference
  • the direction along the central axis AX of the combustion tube 20 is also simply referred to as the axial direction
  • the circumferential direction around the central axis AX is also simply referred to as the circumferential direction
  • the radial direction around the central axis AX is also simply referred to as the radial direction.
  • the main flow of combustion gas flowing within the combustion tube 20 is appropriately referred to as a "mainstream".
  • FIG. 3A is a cross-sectional view showing an example of the shape of the combustion tube.
  • FIG. 3B shows the shape of the inner wall surface on the upstream side of the combustion tube and the inner peripheral surface of the nozzle when the combustion tube shown in FIG. 3A is viewed from the downstream side along the first central axis on the upstream side of the combustion tube. It is a typical diagram showing the positional relationship with a shape.
  • FIG. 4A is a sectional view showing another example of the shape of the combustion tube.
  • FIG. 4B shows the shape of the inner wall surface on the upstream side of the combustion tube and the inner peripheral surface of the nozzle when the combustion tube shown in FIG. 4A is viewed from the downstream side along the first central axis on the upstream side of the combustion tube. It is a typical diagram showing the positional relationship with a shape.
  • the combustion tube 20 has a blowout portion 20e that forms a combustion gas blowout port 20d formed at the downstream end. .
  • the central axis AX of the combustion tube 20 extends in different directions between the first central axis AX1 on the upstream side of the combustion tube 20 and the second central axis AX2 at the jetting portion 20e.
  • FIGS. 3A and 4A show a cross section appearing on a virtual plane Pv1 including the central axis AX from the upstream region of the combustion tube 20 to the jetting portion 20e.
  • the inner cylinder 12 has an inner circumferential surface of a cylinder centered on a first central axis AX1 extending linearly. It has a wall surface 12i.
  • the transition piece 14 has an extension direction of the central axis AX at least at the connection part with the inner cylinder 12 and a central axis at the jetting part 20e. It has a bent shape that is different from AX (second central axis AX2).
  • the transition piece 14 has a cross-sectional shape perpendicular to the central axis AX that gradually changes along the central axis AX from a circular shape at the connection part with the inner cylinder 12 to a partially annular shape at the jetting part 20e. is formed.
  • the transition piece 14 becomes more in-line with the central axis AX toward the downstream side in a cross section parallel to the virtual plane Pv1. The shape changes to a flattened shape so that the distance from the wall surface 14i gradually becomes shorter.
  • the transition piece 14 is a virtual plane orthogonal to the above-described virtual plane Pv1, and has an ejection part from an upstream region. It includes a first region R1 and a second region R2 with a virtual plane Pv2 including the central axis AX up to 20e as a boundary.
  • the virtual plane Pv2 is a plane that includes the central axis AX from the upstream region to the jetting portion 20e and is perpendicular to the paper plane in FIGS. 3A and 4A. That is, in FIGS.
  • the central axis AX corresponds to the cross section of the virtual plane Pv2 appearing on the paper surface of FIGS. 3A and 4A.
  • the first region R1 is defined as downstream of the first central axis AX1 (upstream central axis) on the upstream side of the combustion tube 20, of the two regions separated across the central axis AX in FIGS. 3A and 4A. This is the region through which the straight line L1 extending to the side passes in the spouting portion 20e (see FIGS. 3B and 4B).
  • the first region R1 is a virtual area from the position corresponding to the reference position Pr on the first central axis AX1 to the air outlet 20d, of the two regions separated across the central axis AX in FIGS. 3A and 4A. This is the region where the distance traced along the inner wall surface 20i within the plane Pv1 is longer.
  • the inner wall surface 20i of the combustion tube 20 in the first region R1 shown in FIGS. 3A and 4A is moved from the position corresponding to the reference position Pr on the first central axis AX1 to the air outlet 20d.
  • the distance X1 is the distance X2 that is traced from the position corresponding to the reference position Pr on the first central axis AX1 to the outlet 20d on the inner wall surface 20i of the combustion tube 20 in the second region R2 shown in FIGS. 3A and 4A.
  • the reference position Pr on the first central axis AX1 may be, for example, the tip position of the fuel nozzle (pilot nozzle 54, main nozzle 64) on the first central axis AX1, and may be located upstream or downstream of the inner cylinder 12. It may be located at the side end.
  • the first region R1 is a region above the center axis AX in the drawing
  • the second region R2 is a region below the center axis AX in the drawing
  • the first region R1 is a region below the central axis AX in the drawing
  • the second region R2 is a region above the central axis AX in the drawing.
  • a plurality of combustors are provided on the inner wall surface 20i of the combustion tube 20 at intervals in the circumferential direction, A constricted portion 71 that protrudes toward the housing is provided.
  • the throttle portion 71 is for guiding relatively low-temperature combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20.
  • the relatively low-temperature combustion gas flowing near the inner wall surface 20i mixes with the relatively high-temperature combustion gas flowing in the center of the combustion tube 20, thereby promoting combustion. Details of the aperture section 71 will be explained in detail later.
  • the temperature deviation of the combustion gas occurs in the circumferential direction due to the influence of the shape of the region on the downstream side of the combustion tube. Specifically, if the throttle portion 71, which will be described in detail later, is not provided, in a relatively downstream region of the transition piece 14, the second region R2 is relatively more radial than the first region R1. It was found that the temperature of the combustion gas tends to be lower in the outer region.
  • the total projected area of the throttle portion 71 existing in the second region R2 when viewed from the direction in which the central axis AX extends S2 is set to be larger than the total projected area S1 when the aperture portion 71 existing in the first region R1 is viewed from the direction in which the central axis AX extends.
  • the total projected area S2 of the aperture portions 71 present in the second region R2 when viewed from the direction in which the central axis AX extends is calculated by calculating the total projected area S2 of the aperture portions 71 present in the first region R1 in the direction in which the central axis AX extends.
  • the combustion gas flows closer to the inner wall surface 20i of the combustion tube 20. It becomes easier to be guided towards the center of the area.
  • the relatively low-temperature combustion gas mixes with the high-temperature combustion gas in the second region R2, thereby further promoting combustion. Therefore, the difference between the temperature of the combustion gas in the second region R2 and the temperature of the combustion gas in the first region R1 can be suppressed, and carbon monoxide generation can be suitably suppressed even during partial load operation of the gas turbine 1. It can be suppressed.
  • the relatively low temperature combustion gas mixes with the high temperature combustion gas in the second region R2 to further promote combustion. Therefore, the difference between the temperature of the combustion gas in the second region R2 and the temperature of the combustion gas in the first region R1 can be suppressed, and carbon monoxide generation can be suitably suppressed even during partial load operation of the gas turbine 1. It can be suppressed.
  • the projected area of each of the aperture parts 71 when viewed from the extending direction of the central axis AX is the tangential direction of the central axis AX at a position on the central axis AX that is closest to each of the aperture parts 71. This is the projected area of each aperture section 71 when viewed from .
  • the projected area of the aperture portion 71 when viewed from the extending direction of the central axis AX is also simply referred to as the projected area.
  • FIG. 5 is a view of an example of a throttle member 70 according to some embodiments having a throttle portion 71, as viewed from the downstream side in the axial direction.
  • FIG. 6 is a perspective view of a portion of the aperture member 70 shown in FIG.
  • the aperture member 70 includes an annular ring portion 72 and a plurality of protrusions formed on the ring portion 72 at intervals in the circumferential direction. 71.
  • the aperture part 71 has a shape in which a protrusion that protrudes in the axial direction with respect to the ring part 72 is bent radially inward.
  • FIG. 5 is a view of an example of a throttle member 70 according to some embodiments having a throttle portion 71, as viewed from the downstream side in the axial direction.
  • FIG. 6 is a perspective view of a portion of the aperture member 70 shown in FIG.
  • the aperture member 70 includes an annular ring portion 72 and a plurality of protrusions formed on the ring portion 72 at intervals in
  • the two intersection positions of the throttle member 70 and the above-mentioned virtual plane Pv1 are defined as 0 degrees and 180 degrees as angular positions in the circumferential direction. do.
  • the angular position existing in the first region R1 is set to 0 degrees
  • the angular position existing in the second region R2 is set to 180 degrees.
  • FIG. 7A is a schematic view of the combustion tube 20 expanded in the circumferential direction to show an example of the arrangement position of the throttle part 71, and shows the arrangement of the throttle part 71 of the throttle member 70 shown in FIG. .
  • FIG. 7B is a schematic diagram of the combustion tube 20 expanded in the circumferential direction to show another example of the arrangement position of the throttle part 71.
  • FIG. 7C is a schematic diagram in which the combustion tube 20 is expanded in the circumferential direction to show still another example of the arrangement position of the throttle part 71.
  • FIG. 7D is a schematic diagram in which the combustion tube 20 is expanded in the circumferential direction to show still another example of the arrangement position of the throttle part 71.
  • FIG. 7A is a schematic view of the combustion tube 20 expanded in the circumferential direction to show an example of the arrangement position of the throttle part 71, and shows the arrangement of the throttle part 71 of the throttle member 70 shown in FIG.
  • FIG. 7B is a schematic diagram of the combustion tube 20 expanded in the circum
  • FIG. 7E is a schematic diagram of the combustion tube 20 expanded in the circumferential direction to show still another example of the arrangement position of the throttle part 71.
  • FIG. 7F is a schematic diagram in which the combustion tube 20 is expanded in the circumferential direction to show still another example of the arrangement position of the throttle part 71.
  • the total value S2 of the projected areas of the aperture parts 71 existing in the second region R2 is larger than the total value S1 of the projected areas of the aperture parts 71 existing in the first region R1. is also becoming larger.
  • the number of aperture parts 71 hereinafter also referred to as first aperture parts 711
  • the number of aperture parts 71 hereinafter referred to as second aperture parts 711
  • Each constriction part 71 is formed so that the protrusion height h2 of the second constriction part 712 is higher than the protrusion height h1 of the first constriction part 711. has been done.
  • the number of first constricted parts 711 and the number of second constricted parts 712 are the same, but the circumferential size w1 of the first constricted parts 711 is larger than that of the second constricted parts 711.
  • Each constricted portion 71 is formed such that the circumferential size w2 of is larger.
  • the projected area of each of the first aperture parts 711 and the projected area of each of the second aperture parts 712 are the same, but in the second region, there are By arranging the second aperture part 712, the total value S2 of the projected area of the aperture part 71 existing in the second region R2 is larger than the total value S1 of the projected area of the aperture part 71 existing in the first region R1. It is configured to be.
  • the second throttle part 712 located on the upstream side in the axial direction and the second throttle part 712 located on the downstream side in the axial direction are located at the same circumferential position.
  • the second constriction section 712 disposed on the axial upstream side and the second constriction section 712 disposed on the axial downstream side are disposed at different circumferential positions.
  • each constriction part 71 is formed such that the protrusion height h2 of the second constriction part 712 is higher than the protrusion height h1 of the first constriction part 711. .
  • second aperture portions 712 are further arranged at different positions in the axial direction in the second region.
  • the second throttle part 712 located on the upstream side in the axial direction and the second throttle part 712 located on the downstream side in the axial direction are located at the same circumferential position.
  • the second constriction section 712 disposed on the axial upstream side and the second constriction section 712 disposed on the axial downstream side are disposed at different circumferential positions.
  • the second throttle part 712 on the upstream side in the axial direction is preferably arranged in the inner cylinder 12, and the second throttle part 712 on the downstream side in the axial direction is preferably arranged in the transition pipe 14 ( (See FIGS. 3A and 4A).
  • the height of the combustion tube 20 in the radial direction of at least one of the second throttle portions 712 is adjusted.
  • the height (protrusion height h2) is preferably higher than the radial height (protrusion height h1) of the first constricted portion 711. This makes it easier to guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 toward the center of the combustion tube 20, making it easier to mix with the high-temperature combustion gas and promote combustion. .
  • the protrusion height h2 of at least one of the second throttle parts 712 is the same as that of the first throttle part 711. It is preferable that the protrusion height h1 is 1.5 times or more and 3.0 times or less.
  • the protrusion height h2 of the second constriction part 712 is 1.5 times or more the protrusion height h1 of the first aperture part 711.
  • the circumferential size w2 of at least one of the second throttle parts 712 is equal to the circumferential size of the first throttle part 711. It may be larger than w1. This makes it easier to guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 toward the center of the combustion tube 20, making it easier to mix with the high-temperature combustion gas and promote combustion. .
  • the upstream surface of the throttle portion 71 is inclined so as to approach the central axis AX toward the downstream side of the combustion tube 20. It is preferable that it is an inclined surface 71u.
  • the angle ⁇ 2 at which the inclined surface 71u of at least one of the second aperture parts 712 inclines with respect to the inner wall surface 20i is greater than the angle ⁇ 1 which the inclined surface 71u of the first aperture part 711 inclines with respect to the inner wall surface 20i. The bigger the better.
  • the angle ⁇ 2 at which the inclined surface 71u of at least one of the second aperture parts 712 inclines with respect to the inner wall surface 20i is made larger than the angle ⁇ 1 which the inclined surface 71u of the first aperture part 711 inclines with respect to the inner wall surface 20i.
  • the angle ⁇ 2 at which the inclined surface 71u of at least one of the second throttle portions 712 is inclined with respect to the inner wall surface 20i is preferably 50 degrees or more and 85 degrees or less.
  • the angle ⁇ 2 at which the inclined surface 71u of at least one of the second throttle portions 712 is inclined with respect to the inner wall surface 20i to 50 degrees or more and 85 degrees or less, the influence on the mainstream flow of combustion gas can be suppressed.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 can be guided toward the center of the combustion tube 20 and mixed with the high-temperature combustion gas to promote combustion.
  • FIG. 8 is a view taken along arrows VIII-VIII in FIG. 3A, and the transition piece 14 is not shown.
  • the combustor 3 according to some embodiments includes a plurality of main nozzles 64 arranged at intervals in the circumferential direction within the combustion tube 20 (inner tube 12), as shown in FIG. 8, for example. At least one of the throttle portions 71 is preferably located between two circumferentially adjacent main nozzles 64 when viewed from the extending direction of the central axis AX.
  • the temperature of the combustion gas is lower in the region between two main nozzles 64 adjacent in the circumferential direction when viewed from the extending direction of the central axis AX than in the region overlapping with the main nozzles 64 when viewed from the extending direction of the central axis AX. It tends to be lower.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 is guided toward the center of the combustion tube 20 at a position where the temperature of the combustion gas tends to be low when viewed from above, and is mixed with high-temperature combustion gas. Can promote combustion.
  • the second throttle portion 712 is located at a first position P1 along the central axis AX, and It is preferable that the position along the central axis AX is provided at a second position P2 different from the first position P1 (downstream of the first position P1).
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 can be guided toward the center of the combustion tube 20 by the second throttle portion 712 provided at the first position P1 and the second position P2.
  • more of the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 can be mixed with high-temperature combustion gas to promote combustion.
  • the combustion tube 20 includes an inner tube 12 and a transition tube 14 disposed on the downstream side of the inner tube 12. You can stay there.
  • the first position P1 may be a position within the inner cylinder 12.
  • the second position P2 may be a position within the transition piece 14.
  • a gap 13 is formed at the connection part between the inner cylinder 12 and the transition piece 14, and compressed air flows through the gap 13. It is configured to be introduced into the combustion tube 20 as cooling air. Therefore, by providing the throttle part 71 (second throttle part 712) on the inner wall surface 14i of the transition piece 14, it is possible to suppress a decrease in the temperature of the combustion gas in the region downstream of the second position P2.
  • the arrangement position in the circumferential direction is different from that of the throttle part 712.
  • the second constriction part 712 provided at the second position P2 may be arranged at a different position in the circumferential direction from the second constriction part 712 provided at the first position P1.
  • the combustion gas is guided by the second throttle part 712 provided at the second position P2, compared to the case where the second throttle part 712 provided at the first position P1 and the second throttle part 712 are arranged at the same position in the circumferential direction. It was found to be more effective.
  • the second constriction part 712 provided at the second position P2 By making the arrangement position in the circumferential direction of the second constriction part 712 provided at the second position P2 different from that of the second constriction part 712 provided at the first position P1, the second constriction part 712 provided at the second position P2 The effect of guiding the combustion gas can be enhanced by the two constricted portions 712.
  • FIG. 9 is a diagram showing an example of a configuration for cooling the throttle part 71, and is a schematic cross-sectional view of the vicinity of the throttle part 71 viewed from the circumferential direction.
  • the combustion tube 20 is located at a position where it overlaps with the throttle part 71 when viewed radially outward from the central axis AX, that is, a position where it overlaps with the throttle part 71 in the axial direction. It is preferable to have a through hole 23 that opens to.
  • the air (compressed air) flowing outside the combustion tube 20 can flow toward the throttle part 71 via the through hole 23, and the throttle part 71 exposed to high temperature combustion gas can be cooled.
  • the through-hole 23 may be provided so as to correspond to all the aperture parts 71, and at least the second aperture part 712 has a larger projected area than the first aperture part 711. 712 may be provided.
  • FIGS. 10A and 10B are diagrams for explaining variations in the shape of the constricted portion 71, and are diagrams schematically showing the shape of the constricted portion 71 when viewed from the axial direction.
  • a protrusion 71b that further protrudes radially inward may be provided at the radially inner end 71a of the throttle portion 71.
  • the protrusion 71b may be provided at one location as shown in FIG. 10A, or may be provided at multiple locations (two locations in the example shown in FIG. 10B) at intervals in the circumferential direction as shown in FIG. 10B. good.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 is directed to the combustion tube 20.
  • the number of vortices of combustion gas generated can be increased, and more combustion gas flowing near the inner wall surface 20i of the combustion tube 20 is mixed with high-temperature combustion gas to promote combustion. can.
  • a through hole 71c penetrating in the axial direction may be provided in the constricted portion 71.
  • the area where the through hole 71c is provided in the circumferential direction and the area where the through hole 71c is not provided direct the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20. Since the guiding effects are different, it is possible to increase the number of vortices of the combustion gas that are generated by guiding the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20. Combustion gas flowing near the inner wall surface 20i of 20 can be mixed with more high-temperature combustion gas to promote combustion.
  • the present disclosure is not limited to the embodiments described above, and also includes forms in which modifications are added to the embodiments described above, and forms in which these forms are appropriately combined.
  • the total projected area S2 of the aperture portions 71 existing in the second region R2 is the same as that of the aperture portions 71 present in the first region R1. They may be combined as appropriate so that the total projected area is larger than S1.
  • the second constriction portions 712 are provided in two rows in the axial direction, but may be provided in three or more rows.
  • a gas turbine combustor (combustor 3) according to at least one embodiment of the present disclosure has a combustion region formed inside through which combustion gas generated by combustion of fuel can flow, and a combustion region at a downstream end thereof.
  • a combustion tube 20 having a blowout portion 20e forming a blowout port 20d for the formed combustion gas, and a plurality of combustion tubes 20 provided at intervals in the circumferential direction on the inner wall surface 20i of the combustion tube 20 and protruding toward the inside of the combustion tube 20.
  • a constriction section 71 is provided.
  • the central axis AX of the combustion tube 20 includes an upstream central axis (first central axis AX1) extending linearly in the upstream region of the combustion tube 20, and an upstream central axis (first central axis AX1) extending linearly in the upstream region of the combustion tube 20. It extends in a direction different from the direction in which the central axis AX1) extends.
  • the combustion tube 20 is a virtual plane that is orthogonal to a virtual plane Pv1 that includes the central axis AX from the upstream region to the jetting portion 20e, and is a virtual plane that includes the central axis AX from the upstream region to the jetting portion 20e.
  • a straight line L1 that is an extension of the upstream central axis (first central axis AX1) passes through the first region R1 at the jetting portion 20e.
  • the total projected area S2 of the aperture part 71 (second aperture part 712) present in the second region R2 when viewed from the extending direction of the central axis AX is It is larger than the total value S1 of the projected area when the first aperture part 711) is viewed from the extending direction of the central axis AX.
  • the total projected area S2 of the aperture part 71 (second aperture part 712) existing in the second region R2 when viewed from the direction in which the central axis AX extends is set to the first region R2.
  • the aperture part 71 (first aperture part 711) present in R1 larger than the total projected area S1 when viewed from the direction in which the central axis AX extends
  • the second region R2 is larger than the first region R1.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 is more easily guided toward the center of the combustion tube 20.
  • the relatively low-temperature combustion gas mixes with the high-temperature combustion gas in the second region R2, thereby further promoting combustion.
  • the difference between the temperature of the combustion gas in the second region R2 and the temperature of the combustion gas in the first region R1 can be suppressed, and carbon monoxide generation can be suitably suppressed even during partial load operation of the gas turbine 1. It can be suppressed.
  • the gas turbine combustor (combustor 3) has a combustion region formed inside through which combustion gas generated by combustion of fuel can flow, and a combustion region at the downstream end.
  • a combustion tube 20 having a blowout portion 20e forming a blowout port 20d for the formed combustion gas, and a plurality of combustion tubes 20 provided at intervals in the circumferential direction on the inner wall surface 20i of the combustion tube 20 and protruding toward the inside of the combustion tube 20.
  • a constriction section 71 is provided.
  • the central axis AX of the combustion tube 20 includes an upstream central axis (first central axis AX1) extending linearly in the upstream region of the combustion tube 20, and an upstream central axis (first central axis AX1) extending linearly in the upstream region of the combustion tube 20. It extends in a direction different from the direction in which the central axis AX1) extends.
  • the combustion tube 20 is a virtual plane that is orthogonal to a virtual plane Pv1 that includes the central axis AX from the upstream region to the jetting portion 20e, and is a virtual plane that includes the central axis AX from the upstream region to the jetting portion 20e.
  • first region R1 It includes a first region R1 and a second region R2 with plane Pv2 as a boundary.
  • the distance traced along the inner wall surface 20i within the virtual plane Pv1 from the position corresponding to the reference position on the upstream central axis line (first central axis line AX1) to the air outlet is longer than the first area R1.
  • Region R2 is shorter.
  • the total projected area S2 of the aperture part 71 (second aperture part 712) present in the second region R2 when viewed from the extending direction of the central axis AX is It is larger than the total value S1 of the projected area when the first aperture part 711) is viewed from the extending direction of the central axis AX.
  • the total projected area S2 of the aperture part 71 (second aperture part 712) existing in the second region R2 when viewed from the direction in which the central axis AX extends is set to the first region R2.
  • the second region R2 is larger than the first region R1.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 is more easily guided toward the center of the combustion tube 20.
  • the relatively low-temperature combustion gas mixes with the high-temperature combustion gas in the second region R2, thereby further promoting combustion.
  • the difference between the temperature of the combustion gas in the second region R2 and the temperature of the combustion gas in the first region R1 can be suppressed, and carbon monoxide generation can be suitably suppressed even during partial load operation of the gas turbine 1. It can be suppressed.
  • the diameter of the combustion tube 20 for at least one of the throttle parts 71 (second throttle parts 712) existing in the second region R2 The height in the radial direction (protrusion height h2) is preferably higher than the height in the radial direction (protrusion height h1) of the constricted portion 71 (first constricted portion 711) present in the first region R1.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 is easily guided toward the center of the combustion tube 20, and mixed with the high-temperature combustion gas. This makes it easier to promote combustion.
  • the height in the radial direction of the combustion tube 20 for at least one of the throttle portions 71 (second throttle portions 712) present in the second region R2 is 1.5 times or more and 3.0 times or less of the radial height (protrusion height h1) of the constriction part 71 (first constriction part 711) existing in the first region R1. Good to have.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 is directed to the center of the combustion tube 20 while suppressing the influence on the mainstream flow of the combustion gas. It can be guided towards the target and mixed with hot combustion gases to promote combustion.
  • the combustion tube for at least one of the throttle parts 71 (second throttle parts 712) existing in the second region R2 The circumferential size w2 of 20 may be larger than the circumferential size w1 of the constricted portion 71 (first constricted portion 711) present in the first region R1.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 is easily guided toward the center of the combustion tube 20, and mixed with high-temperature combustion gas. This makes it easier to promote combustion.
  • the upstream side surface (slanted surface 71u) of the throttle portion 71 is centered toward the downstream side of the combustion tube 20.
  • the inclined surface 71u may be inclined so as to approach the axis AX.
  • the angle ⁇ 2 at which the inclined surface 71u of at least one of the narrowed portions 71 (second narrowed portions 712) existing in the second region R2 is inclined with respect to the inner wall surface 20i is determined by It is preferable that the inclined surface 71u of the first aperture part 711) is larger than the angle ⁇ 1 at which the inclined surface 71u is inclined with respect to the inner wall surface 20i.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 is easily guided toward the center of the combustion tube 20, and mixed with the high-temperature combustion gas. This makes it easier to promote combustion.
  • the inclined surface 71u of at least one of the aperture parts 71 (second aperture parts 712) present in the second region R2 is relative to the inner wall surface 20i.
  • the angle ⁇ 2 of inclination is preferably 50 degrees or more and 85 degrees or less.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 is directed to the center of the combustion tube 20 while suppressing the influence on the mainstream flow of the combustion gas. It can be guided towards the target and mixed with hot combustion gases to promote combustion.
  • a plurality of fuel nozzles may be provided. At least one of the throttle portions 71 is preferably located between two circumferentially adjacent fuel nozzles (main nozzles 64) when viewed from the extending direction of the central axis AX.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 is transferred to the combustion tube 20 at a position where the temperature of the combustion gas tends to be low when viewed from the extending direction of the central axis AX. It can be guided toward the center and mixed with hot combustion gas to promote combustion.
  • the aperture part 71 (second aperture part 712) existing in the second region R2 is arranged along the central axis AX.
  • the first position P1 and the position along the central axis AX may be provided at a second position P2 different from the first position P1.
  • the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 is combusted by the throttle part 71 (second throttle part 712) provided at the first position P1 and the second position P2. Since it can be guided toward the center of the cylinder 20, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 in the second region R2 can be mixed with more high-temperature combustion gas to promote combustion.
  • the combustion tube 20 is arranged on the downstream side of the first combustion tube (inner tube 12) and the first combustion tube (inner tube 12). It may also include a second combustion tube (transition tube 14).
  • the first position P1 may be a position within the first combustion cylinder (inner cylinder 12).
  • the second position P2 may be a position within the second combustion tube (transition tube 14).
  • Cooling air may be introduced from the connection between the first combustion tube (inner tube 12) and the second combustion tube (transition tube 14).
  • the constriction part 71 (second constriction part 712) is provided on the inner wall surface 14i of the second combustion tube (transition tube 14)
  • the combustion gas will flow in the region downstream of the second position P2.
  • temperature drop can be suppressed.
  • the configuration (10) above it is possible to suppress a decrease in the temperature of the combustion gas in the region downstream of the second position P2.
  • the aperture portion 71 (second aperture portion 712) present in the second region R2 is provided at the second position P2.
  • the aperture part 71 (second aperture part 712) located at the first position P1 is the aperture part 71 (second aperture part 712) provided at the first position P1 among the aperture part 71 (second aperture part 712) existing in the second region R2. 712) in the circumferential arrangement position.
  • the effect of guiding the combustion gas can be enhanced by the throttle part 71 (second throttle part 712) provided at the second position P2.
  • the combustion tube 20 overlaps the throttle portion 71 when viewed radially outward from the central axis AX. It is preferable to have a through hole 23 that opens at a position where the through hole 23 is opened.
  • the air (compressed air) flowing outside the combustion tube 20 can flow toward the throttle part 71 through the through hole 23, and the throttle part 71 is exposed to high-temperature combustion gas. can be cooled.
  • a gas turbine 1 includes a compressor 2 that generates compressed air, and a gas turbine combustor (combustor 3) configured as described in any one of (1) to (12) above. and a turbine 4 rotationally driven by combustion gas generated by a gas turbine combustor (combustor 3).
  • the relatively low temperature combustion gas mixes with the high temperature combustion gas in the second region R2, thereby further promoting combustion. Therefore, the difference between the temperature of the combustion gas in the second region R2 and the temperature of the combustion gas in the first region R1 can be suppressed, and carbon monoxide generation can be suitably suppressed even during partial load operation of the gas turbine 1. It can be suppressed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
PCT/JP2023/008476 2022-03-14 2023-03-07 ガスタービン燃焼器及びガスタービン Ceased WO2023176570A1 (ja)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US18/842,911 US20250180209A1 (en) 2022-03-14 2023-03-07 Gas turbine combustor and gas turbine
JP2024507776A JP7736911B2 (ja) 2022-03-14 2023-03-07 ガスタービン燃焼器及びガスタービン
CN202380025549.3A CN118829827A (zh) 2022-03-14 2023-03-07 燃气涡轮机燃烧器及燃气涡轮机
DE112023000565.6T DE112023000565T5 (de) 2022-03-14 2023-03-07 Gasturbinenbrennkammer und gasturbine
KR1020247030057A KR20240149927A (ko) 2022-03-14 2023-03-07 가스 터빈 연소기 및 가스 터빈

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JP2022-039453 2022-03-14
JP2022039453 2022-03-14

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Cited By (1)

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Publication number Priority date Publication date Assignee Title
WO2025229806A1 (ja) * 2024-04-30 2025-11-06 三菱パワー株式会社 燃焼器、及びこれを備えるガスタービン

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011102669A (ja) * 2009-11-10 2011-05-26 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器及びガスタービン
WO2016047397A1 (ja) * 2014-09-25 2016-03-31 三菱日立パワーシステムズ株式会社 燃焼器、及びこれを備えるガスタービン
JP2017180899A (ja) * 2016-03-29 2017-10-05 三菱日立パワーシステムズ株式会社 燃焼器、燃焼器の性能向上方法
WO2021201093A1 (ja) * 2020-03-31 2021-10-07 三菱重工業株式会社 ガスタービンの燃焼器、及び、ガスタービン

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Publication number Priority date Publication date Assignee Title
JP7512772B2 (ja) 2020-08-28 2024-07-09 ニデックパワートレインシステムズ株式会社 ポンプ

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011102669A (ja) * 2009-11-10 2011-05-26 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器及びガスタービン
WO2016047397A1 (ja) * 2014-09-25 2016-03-31 三菱日立パワーシステムズ株式会社 燃焼器、及びこれを備えるガスタービン
JP2017180899A (ja) * 2016-03-29 2017-10-05 三菱日立パワーシステムズ株式会社 燃焼器、燃焼器の性能向上方法
WO2021201093A1 (ja) * 2020-03-31 2021-10-07 三菱重工業株式会社 ガスタービンの燃焼器、及び、ガスタービン

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2025229806A1 (ja) * 2024-04-30 2025-11-06 三菱パワー株式会社 燃焼器、及びこれを備えるガスタービン

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KR20240149927A (ko) 2024-10-15
JP7736911B2 (ja) 2025-09-09

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