WO2013183618A1 - 燃料噴射装置 - Google Patents

燃料噴射装置 Download PDF

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Publication number
WO2013183618A1
WO2013183618A1 PCT/JP2013/065432 JP2013065432W WO2013183618A1 WO 2013183618 A1 WO2013183618 A1 WO 2013183618A1 JP 2013065432 W JP2013065432 W JP 2013065432W WO 2013183618 A1 WO2013183618 A1 WO 2013183618A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel injection
injection valve
air
pilot
main
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/JP2013/065432
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
松山竜佐
小林正佳
堀川敦史
藤原仁志
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.)
Kawasaki Heavy Industries Ltd
Japan Aerospace Exploration Agency JAXA
Kawasaki Motors Ltd
Original Assignee
Kawasaki Heavy Industries Ltd
Japan Aerospace Exploration Agency JAXA
Kawasaki Jukogyo KK
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 Kawasaki Heavy Industries Ltd, Japan Aerospace Exploration Agency JAXA, Kawasaki Jukogyo KK filed Critical Kawasaki Heavy Industries Ltd
Priority to EP13801226.5A priority Critical patent/EP2860454B1/en
Priority to CN201380027505.0A priority patent/CN104334972B/zh
Publication of WO2013183618A1 publication Critical patent/WO2013183618A1/ja
Priority to US14/557,877 priority patent/US10132499B2/en
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
    • F23R3/02—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
    • 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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a fuel injection device provided with a composite fuel injection valve, which is used in, for example, a gas turbine engine or the like and is a combination of a plurality of fuel nozzles.
  • NOx nitrogen oxide
  • the fuel nozzle of a conventional aircraft gas turbine combustor is a diffusion combustion system, and in this system, the combustion reaction is performed in a stoichiometric ratio, so that the flame temperature becomes high. Since NOx emissions have the property of increasing exponentially with the flame temperature, lowering the flame temperature is an effective measure to reduce NOx emissions, but the temperature and pressure of gas turbines are increasing. At present, there is a limit to suppressing NOx emissions by the conventional diffusion combustion method.
  • a lean combustion type fuel injection valve is said to be effective.
  • Lean combustion is a method in which the ratio of fuel to air is reduced and combustion is performed. In lean combustion by this method, the flame temperature can be lowered more than in the conventional diffusion combustion system. On the other hand, the lean combustion method tends to be unstable and incomplete combustion because the flame temperature is low. Therefore, a pilot injection valve is arranged on the inner side and a main injection valve is arranged coaxially on the outer side, and a stable combustion at low output is maintained by using a diffusion combustion system with the pilot injection valve. A concentric fuel injection valve that realizes low NOx by performing lean combustion with the main injection valve in addition to the diffusion combustion in FIG.
  • an object of the present invention is to provide a fuel injection device capable of obtaining high combustion efficiency at both low output and intermediate output while suppressing the generation of smoke due to excessive fuel. It is in.
  • a fuel injection device is a device that supplies fuel to compressed air from a compressor and burns it, and is disposed at the center in the radial direction of the fuel injection device.
  • a pilot fuel injection valve that injects fuel into the combustion chamber; a main fuel injection valve that is disposed on an outer periphery of the pilot combustion injection valve to inject a premixed fuel and air into the combustion chamber; and the pilot fuel injection valve And an air injection unit that injects the compressed air into the combustion chamber.
  • the air injection unit removes the air injection unit from the combustion chamber.
  • said A second opening that is provided on the wall plate and supplies compressed air to an inflow space between the flame holding plate and the partition plate, and the flame holding plate is inclined radially outward with respect to the axis. It has an inclined part inclined in the direction.
  • the second opening may be provided as a through-hole in the axial direction formed in a portion of the partition plate covered with the flame holding plate.
  • the said inclination part is extended substantially parallel to the said partition board.
  • the flame holding plate having the inclined portion effectively prevents interference between the pilot combustion area and the main air flow, and flame holding performance is improved and combustion efficiency is improved. Moreover, since the air supplied from the second opening flows into the inflow space between the flame holding plate and the partition plate and cools the flame holding plate, the flame holding plate is prevented from being burned out. Furthermore, since air is supplied into the combustion chamber from the first opening, it is possible to avoid an excessive fuel state in the pilot combustion region, thereby suppressing the occurrence of smoke.
  • the flame holding plate has a peripheral wall that is connected to the upstream side of the inclined portion and extends in the axial direction to form the outer periphery of the first opening. According to this configuration, the air supplied from the second opening is reliably led out to the radially outer side in the downstream direction without flowing into the inner diameter side, so that the combustion efficiency can be more reliably improved and smoke can be suppressed. be able to.
  • the pilot fuel injection valve and the main injection valve are connected by a partition wall that forms a compressed air storage space downstream of the air injection unit.
  • an inlet for introducing compressed air is formed in the storage space.
  • a compressed air storage space is formed by the partition wall, and the compressed air is injected from the first opening and the second opening through the storage space, so that the compressed air is injected from the first opening and the second opening. Air distribution is made uniform.
  • the pilot fuel injection valve is preferably provided with a swirler that turns compressed air around an axis. According to this configuration, since the fuel injected from the pilot fuel injection valve is diffused radially outward by the swirler, the flame holding performance of the flame holding plate is ensured, and the combustion efficiency is more reliably improved.
  • FIG. 1 shows a combustor CB of a gas turbine engine provided with a fuel injection device 1 according to an embodiment of the present invention.
  • the combustor CB mixes and burns fuel with compressed air CA supplied from a compressor (not shown) of the gas turbine engine, and sends high-temperature and high-pressure combustion gas generated by the combustion to the turbine to drive the turbine. Is.
  • the combustor CB is an annular type, and a combustor housing 7 having an annular inner space is formed by an annular outer casing 3 and an annular inner casing 5 arranged inside the engine rotational axis C. It is composed.
  • An annular combustion cylinder 9 is disposed concentrically with the combustor housing 7 in the annular inner space of the combustor housing 7.
  • the combustion cylinder 9 is composed of an annular outer liner 11 and an annular inner liner 13 arranged concentrically on the inside thereof, and an annular combustion chamber 15 is formed inside.
  • a plurality of fuel injection devices 1 for injecting fuel into the combustion chamber 15 are arranged on the top wall of the combustion cylinder 9 concentrically with the engine rotation axis C, that is, in the circumferential direction of the combustion cylinder 9 at equal intervals. ing.
  • Each fuel injection device 1 includes a pilot injection valve 21 and a main injection valve 23.
  • the main injection valve 23 is provided concentrically with the axis C1 of the pilot injection valve 21 so as to surround the outer periphery of the pilot injection valve 21, and generates premixed gas.
  • Each fuel injection device 1 is supported on the combustor housing 7 by a stem portion 26 attached to the combustor housing 7.
  • An ignition plug IG for igniting through the outer casing 3 and the outer liner 11 is provided so as to face the radial direction of the combustion cylinder 9 and the tip is close to the fuel injection device 1.
  • compressed air CA fed from the compressor is passed through a plurality of air intake pipes 27 arranged at equal intervals around the engine rotation axis C in the circumferential direction. be introduced.
  • the introduced compressed air CA is supplied to the fuel injection device 1 and supplied into the combustion chamber 15 from a plurality of air inlets formed in the outer liner 11 and the inner liner 13 of the combustion cylinder 9.
  • the stem portion 26 forms a fuel pipe unit U.
  • the fuel pipe unit U is a first fuel supply system F 1 that supplies fuel for diffusion combustion to the pilot injection valve 21 and a lean fuel supply to the main injection valve 23.
  • a second fuel supply system F2 for supplying fuel for mixed combustion.
  • FIG. 2 shows the details of the structure of the fuel injection device 1.
  • the fuel injection device 1 includes the pilot fuel injection valve 21 located in the central portion in the radial direction and the main fuel injection valve disposed on the outer side in the radial direction of the fuel injection device 1, that is, on the outer periphery of the pilot fuel injection valve 21. And an air injection unit 25 provided between the outlet end portion of the pilot fuel injection valve 21 and the main fuel injection valve 23.
  • the pilot fuel injection valve 21 is connected to the stem portion 26 to inject fuel, and is provided on the radially outer side of the pilot fuel injection block 31 to supply compressed air CA. And a tapered pilot nozzle 37 that forms a pilot flow path 35 that premixes the fuel from the pilot fuel injection block 31 and the compressed air CA from the air supply unit 33 and injects it into the combustion chamber 15. .
  • a fuel supply passage 39 serving as a fuel passage is formed in the central portion in the radial direction.
  • the fuel supply passage 39 of the pilot fuel injection block 31 communicates with a first fuel introduction passage 41 formed in the stem portion 26 and serving as a fuel passage.
  • the inner cylindrical body 43 is disposed on the radially outer side of the pilot fuel injection block 31, the outer cylindrical body 45 is disposed on the radially outer side of the inner cylindrical body 43, and the outer cylindrical body is further disposed.
  • a cylindrical pilot shroud 47 having a downstream tip formed as the pilot nozzle 37 is disposed on the radially outer side of 45.
  • the distal end portions (downstream end portions) of the inner cylindrical body 43 and the outer cylindrical body 45 are each formed in a tapered shape that decreases in diameter toward the downstream side.
  • the pilot fuel injection block 31 is provided with a plurality of fuel injection holes 49 extending in the radial direction.
  • a pilot inner air passage 53 is formed between the inner cylindrical body 43 and the outer cylindrical body 45, and a pilot outer air passage 55 is formed between the outer cylindrical body 45 and the pilot shroud 47. ing. These air passages 53 and 55 form an air supply part 33.
  • a pilot inner swirler S ⁇ b> 1 and a pilot outer swirler S ⁇ b> 2 are provided in the upstream portion of each air passage 53, 55 to rotate the compressed air CA around its axis. The fuel injected from the fuel injection holes 49 is sent to the downstream side together with the compressed air CA flowing in from the air passages 53 and 55.
  • An air injection unit 25 is formed between the pilot shroud 47 and a main inner shroud 61 that forms an inner peripheral wall of the main fuel injection valve 23 and is disposed on the radially outer side of the pilot shroud 47.
  • the pilot shroud 47 of the pilot fuel injection valve 21 and the main inner shroud 61 of the main fuel injection valve 23 are connected by an annular partition wall 63.
  • the partition wall 63 is integrally formed with the main inner shroud 61 and is provided at an axial position near the outlet end portion 37 a of the pilot nozzle 37 of the pilot shroud 47.
  • the partition wall 63 is provided with outlet ports 65 that are through holes in the axial direction at a plurality of locations in the circumferential direction.
  • the compressed air CA that has passed through the compressed air passage 67 of the compressed air CA formed on the upstream side of the partition wall 63 through the outlet 65 of the partition wall 63 is a storage space 69 formed on the downstream side of the partition wall 63. Is derived.
  • the downstream end of the main inner shroud 61 that forms the air injection unit 25 is formed in a shape whose diameter increases toward the downstream.
  • An annular partition plate 71 is provided at the downstream end of the main inner shroud 61 so as to incline in the upstream direction on the radially inner side.
  • the partition plate 71 partitions the combustion chamber 15 and the air injection unit 25.
  • a flame holding plate 73 is attached to the inner diameter side end of the partition plate 71.
  • the flame-holding plate 73 has a cylindrical peripheral wall portion 73a extending in the axial direction, and an inclined portion 73b whose diameter increases from the downstream end of the peripheral wall portion toward the downstream side. That is, the inclined portion of the flame-holding plate 73 is inclined in the radially outward and downstream direction with respect to the axial center.
  • a peripheral wall 73 a of the flame holding plate 73 is attached to the inner diameter side end of the partition plate 71.
  • the inclined portion 73 b of the flame holding plate 73 extends at an inclination angle substantially parallel to the partition plate 71 with a gap between the inclined plate 73 and the partition plate 71.
  • the inclined portion 73 b of the flame holding plate 73 covers the downstream side of the inner diameter side end portion of the partition plate 71 with a gap between the inclined plate 73 and the partition plate 71.
  • a radially annular gap is formed between the flame holding plate 73 and the downstream end portion of the pilot nozzle 37, and this gap is a first opening that opens to the downstream side.
  • An injection opening 75 is formed.
  • an outer diameter side air injection opening 77 that is a second opening penetrating in the axial direction is formed in a portion of the partition plate 71 covered with the flame holding plate 73.
  • a part of the compressed air CA led out to the storage space 69 is injected along the axial direction from the inner diameter side air injection opening 75 into the combustion chamber 15, and the remaining part is outer diameter side air injection.
  • the injection port 79 a that is the downstream end of the inflow space 79 is radially outward in the combustion chamber 15. It is injected towards.
  • the main fuel injection valve 23 compresses the premixed gas passage 81 from the upstream side in the axial direction in the annular premixed gas passage 81 that guides the premixed gas to the combustion chamber 15 and injects it.
  • a cylindrical main outer shroud 86 forming a main nozzle is concentrically disposed outside the main inner shroud 61, and a main premixed air passage 81 is formed between the main inner shroud 61 and the main outer shroud 86. Has been.
  • the premixed air passage 81, the main outer air passage 83, and the main inner air passage 85 form a main flow passage 87 that generates premixed air in the main fuel injection valve 23.
  • the main outer air passage 83 and the main inner air passage 85 are respectively provided with a main outer swirler SW3 and a main inner swirler SW4 for turning the compressed air CAa, CAr around the axis.
  • the main fuel injection valve 23 is provided with a plurality of main fuel injection holes 89 for injecting fuel from the upstream side in the axial direction into the main inner air passage 85.
  • the plurality of main fuel injection holes 89 are disposed radially inward of the main outer air passage 83 at equal intervals in the circumferential direction around the axis C1.
  • Each main fuel injection hole 89 is formed as a through-hole provided at the center of a cylindrical main fuel injection block 93 that protrudes from the annular fuel introduction chamber 91 toward the downstream side in the axial direction.
  • the main fuel injection block 93 is provided so as to face an axial through hole 97 provided in a flange-shaped partition wall 95 that forms the front wall (upstream side wall) of the main inner air passage 85.
  • the annular gap between the main fuel injection block 93 and each through hole 97 of the flange-shaped partition wall 95 formed in this way is an air passage outside the fuel injection device 1 and
  • a guide air supply passage 99 is formed which communicates with the compressed air passage 67 and injects the compressed air CA into the main inner air passage 85 from the upstream side in the axial direction. That is, the guide air supply passage 99 injects the compressed air CAr from the upstream side in the axial direction into the main inner air passage 85 so as to follow the flow of the fuel F from the main fuel injection hole 89 of the main fuel injection block 93. .
  • the first valve unit which is an upstream structure including the pilot injection block 31 of the pilot fuel injection valve 21 and the main injection block 93 of the main fuel injection valve 23. 101 is supported by the combustor housing 3 via a stem portion 27, and a second valve unit 103, which is a downstream structure including the pilot nozzle 37 and the main nozzle, is disposed downstream of the main outer shroud 86. It is supported by the combustion cylinder 9 via a support flange 105 provided on the outer periphery of the side end.
  • the first valve unit and the second valve unit 103 are assembled separately, and then the fuel injection device 1 is assembled by fitting the first valve unit 101 into the second valve unit 103. In this way, the first valve unit 101 is formed to be detachable from the second valve unit 103.
  • the pilot fuel in the combustion chamber 15 is generated by the fuel F injected from the pilot fuel injection valve 21 and the air A1 injected from the inner diameter side air injection opening 75 which is the first opening.
  • a pilot combustion zone S is formed in a portion on the downstream side of the injection valve 21.
  • the air injected from the main fuel injection valve 23 forms a main air flow MA outside the pilot combustion zone S.
  • the flame holding plate 73 Since the flame holding plate 73 has the inclined portion 73b that is inclined radially outward and downstream with respect to the axis, interference between the pilot combustion region S and the main air flow MA is effectively prevented, In the pilot combustion zone S, the flame is reliably held and the combustion efficiency is improved. Therefore, combustion efficiency can be improved not only at medium output but also at low output. Moreover, since the air A2 supplied from the outer diameter side air injection opening 77 which is the second opening flows into the inflow space 79 between the flame holding plate 73 and the partition plate 71, the flame holding plate 73 is cooled. Burnout of the flame holding plate 73 is prevented. In order to prevent interference between the pilot combustion zone S and the main air flow MA more reliably, the flame holding plate 73 is preferably separated from the partition plate 71 by 0.7 to 2.0 mm. More preferably, the distance is about 0 mm.
  • the flame holding plate 73 is provided with a peripheral wall 73 a that is connected to the upstream side of the inclined portion 73 b and extends in the axial direction to form the outer periphery of the inner diameter side air injection opening 75.
  • the supplied air is reliably led out in the radially outward and obliquely downstream direction without flowing into the inner diameter side. Therefore, it is possible to improve combustion efficiency and suppress smoke more reliably.
  • the pilot fuel injection valve 21 and the main injection valve 23 are connected by a partition wall 63 that forms a compressed air CA storage space 69 on the downstream side of the air injection unit 25.
  • an inlet 65 for introducing compressed air into the storage space 69 is formed in the partition wall 63.
  • the fuel injected from the pilot fuel injection valve 21 is reliably diffused radially outward by the pilot inner swirler SW1 and the pilot outer swirler SW2 provided in the pilot fuel injection valve 21. Thereby, the flame holding property in the flame holding plate 73 is ensured, and the combustion efficiency is further improved.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
PCT/JP2013/065432 2012-06-07 2013-06-04 燃料噴射装置 Ceased WO2013183618A1 (ja)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13801226.5A EP2860454B1 (en) 2012-06-07 2013-06-04 Fuel injection device
CN201380027505.0A CN104334972B (zh) 2012-06-07 2013-06-04 燃料喷射装置
US14/557,877 US10132499B2 (en) 2012-06-07 2014-12-02 Fuel injection device

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2012-129681 2012-06-07
JP2012129681A JP5924618B2 (ja) 2012-06-07 2012-06-07 燃料噴射装置

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US14/557,877 Continuation US10132499B2 (en) 2012-06-07 2014-12-02 Fuel injection device

Publications (1)

Publication Number Publication Date
WO2013183618A1 true WO2013183618A1 (ja) 2013-12-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2013/065432 Ceased WO2013183618A1 (ja) 2012-06-07 2013-06-04 燃料噴射装置

Country Status (5)

Country Link
US (1) US10132499B2 (enExample)
EP (1) EP2860454B1 (enExample)
JP (1) JP5924618B2 (enExample)
CN (1) CN104334972B (enExample)
WO (1) WO2013183618A1 (enExample)

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WO2015178149A1 (ja) * 2014-05-23 2015-11-26 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器及びガスタービン
EP3184782A4 (en) * 2014-08-18 2018-04-11 Kawasaki Jukogyo Kabushiki Kaisha Fuel injection device
WO2019043751A1 (ja) * 2017-08-28 2019-03-07 川崎重工業株式会社 燃料噴射装置

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US10591164B2 (en) 2015-03-12 2020-03-17 General Electric Company Fuel nozzle for a gas turbine engine
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JP2018146193A (ja) * 2017-03-08 2018-09-20 トヨタ自動車株式会社 液体燃料用バーナー
JP6934359B2 (ja) * 2017-08-21 2021-09-15 三菱パワー株式会社 燃焼器及びその燃焼器を備えるガスタービン
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US20150082797A1 (en) 2015-03-26
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