EP1777459A2 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP1777459A2
EP1777459A2 EP06255437A EP06255437A EP1777459A2 EP 1777459 A2 EP1777459 A2 EP 1777459A2 EP 06255437 A EP06255437 A EP 06255437A EP 06255437 A EP06255437 A EP 06255437A EP 1777459 A2 EP1777459 A2 EP 1777459A2
Authority
EP
European Patent Office
Prior art keywords
fuel supply
additive
premixed
fuel
combustor
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.)
Withdrawn
Application number
EP06255437A
Other languages
German (de)
English (en)
Other versions
EP1777459A3 (fr
Inventor
Kiyoshi Matsumoto
Yasuhiro Kinoshita
Atsushi Okuto
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
Kawasaki Motors Ltd
Original Assignee
Kawasaki Heavy Industries Ltd
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, Kawasaki Jukogyo KK filed Critical Kawasaki Heavy Industries Ltd
Publication of EP1777459A2 publication Critical patent/EP1777459A2/fr
Publication of EP1777459A3 publication Critical patent/EP1777459A3/fr
Withdrawn legal-status Critical Current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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—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

Definitions

  • the present invention relates to a combustor for a gas turbine engine. More specifically, the present invention relates to a combustor for a gas turbine engine, capable of making the combustor of the gas turbine engine achieve desired stable, low-pollution combustion under partial load.
  • Private power generation equipment has progressively come into wide use recently, and gas turbine engines are used widely as power units for private power generation equipment. Different time zones have different power demands, respectively, on private power generation equipment. Therefore, private power generation equipment does not operate always in a maximum-load operating mode and are often required to operate in a partial-load operating mode.
  • the gas turbine engine for private power generation equipment is required to maintain satisfactorily stable combustion and to reduce the rate of emission of harmful gases including NO x (nitrogen oxides) and CO (carbon monoxide) for environmental conservation.
  • NO x nitrogen oxides
  • CO carbon monoxide
  • the first method needs an additional mechanism for injecting water or steam into the combustion chamber.
  • the additional mechanism enlarges the gas turbine engine and the gas turbine engine cannot reduce the rate of NO x emission greatly so as to compensate for the disadvantage of the additional mechanism.
  • the second method can reduce the rate of NO x emission in a wide range of load on the gas turbine engine even in lean premixed combustion having a narrow stable combustion range, work necessary for extraction reduces the thermal efficiency of the gas turbine engine.
  • the present invention has been made in view of those problems in the related art and it is therefore an object of the present invention to provide a combustor for a gas turbine engine, capable of achieving stable combustion and of reducing the rate of emission of harmful substances, such as NO x and CO, in a wide range of load without enlarging the gas turbine engine, without complicating the constitution of the gas turbine engine and without reducing the thermal efficiency of the gas turbine engine.
  • a combustor for a gas turbine engine of a lean premixed combustion type includes: a fuel jetting device configured to jet a premixed fuel into a combustion chamber so that the premixed fuel burns in a premixed combustion zone which is formed in the combustion chamber; and an additive fuel supply unit disposed downstream of the premixed combustion zone so as to additionally supply fuel into the combustion chamber, the additive fuel supply unit including first and second additive fuel supply devices disposed in a two-stage arrangement such that the second additive fuel supply device is positioned downstream of the first additive fuel supply device.
  • a main air passage formed in a liner head to supply air into the premixed combustion zone has a sectional area not lager than a sum of sectional areas of air passages in the first and second additive fuel supply devices of the additive fuel supply unit.
  • a sectional area of an air passage in the first additive fuel supply device is not larger than a sectional area of an air passage in the second additive fuel supply device.
  • the first and second additive fuel supply devices of the additive fuel supply unit are respectively provided with diffusion nozzles to supply fuel.
  • the combustor according to the present invention for a gas turbine engine achieves desired stable, low-pollution combustion under load varying in a wide load range and discharges an exhaust gas including reduced amount of harmful substances, such as NO x and CO.
  • a combustor in a preferred embodiment according to the present invention will be described by way of example with reference to Figs. 1 and 2.
  • the combustor U has a combustor casing including a flow sleeve 1, namely, an outer sleeve, and an inner tube 2, namely, an inner sleeve, extended inside the flow sleeve 1.
  • One end of the flow sleeve 1 and one end of the inner tube 2 are closed by an end wall 3.
  • the other end of the flow sleeve 1 is an air inlet 1a and the other end of the inner tube 2 is an exhaust outlet 2a.
  • the interior of the inner tube 2 is divided into a liner head 4 on the side of the end wall 3 and a combustion chamber 5 on the side of the exhaust outlet 2a by a partition wall 2b having a shape resembling an annular plate disposed at a predetermined longitudinal position.
  • the liner head 4 is provided with a predetermined number of openings 4a through which combustion air taken through the air inlet 1a into the flow sleeve 1 flows into the inner tube 2.
  • a fuel jetting device 6 is disposed inside the liner head 4. The fuel jetting device 6 prepares a premixed fuel by mixing fuel supplied by a fuel supply system, not shown, and combustion air and jets the premixed fuel into the combustion chamber 5. The premixed fuel jetted by the fuel jetting device 6 burns in a predetermined premixed combustion zone V in the combustion chamber 5.
  • the combustor U is provided with a two-stage additive fuel supply unit 7 in addition to the fuel jetting device 6.
  • the two-stage additive fuel supply unit 7 supplies fuel additionally into the combustion chamber 5 while the gas turbine engine is in a partial-load operation.
  • a character F indicates diffusion flames, namely, premixed flames.
  • the fuel jetting device 6 includes a pilot combustion unit 10 in a central part of an inner opening of the partition wall 2b disposed on the upstream side of the combustion chamber 5, and a main combustion unit 20 surrounding the pilot combustion unit 10.
  • the pilot combustion unit 10 has a central pilot fuel nozzle 11, and a combustion air passage 12 surrounding the pilot fuel nozzle 11. A premixed fuel produced by mixing fuel jetted through the pilot fuel nozzle 11 and combustion air is jetted into the combustion chamber 5.
  • the pilot fuel nozzle 11 has a closed end and a side wall provided with radial jetting holes 11a. Fuel is jetted radially through the radial jetting holes 11a.
  • the combustion air passage 12 is defined by the outside surface of the pilot fuel nozzle 11 and the inside surface of an inner hat-shaped tube 13 surrounding the pilot fuel nozzle 11.
  • a swirler 14 is disposed at a predetermined position in the combustion air passage 12. The fuel jetted into the combustion air passage 12 through the pilot fuel nozzle 11 is mixed into swirling combustion air currents produced by the swirler 14. The premixed fuel flows into the combustion chamber 5.
  • the main combustion unit 20 includes a main fuel nozzle 21 and a main premixed fuel passage 22.
  • the main fuel nozzle 21 surrounds the inner hat-shaped tube 13. The fuel is jetted through the main fuel nozzle 21 toward the inlet 22a of the premixed fuel passage 22.
  • the main premixed fuel passage 22 is defined by the outside surface of the inner hat-shaped tube 13 and an outer hat-shaped tube 23 of a diameter greater than that of the inner hat-shaped tube 13. A space between the flanges of the hat-shaped tubes 13 and 23 forms the inlet 22a of the premixed fuel passage 22.
  • a swirler 24 is disposed in the inlet 22a of the premixed fuel passage 22.
  • the open end of the outer hat-shaped tube 23 is joined to the inside edge of the partition wall 2b disposed inside the inner tube 2 to form a premixed fuel outlet 22b, namely, the outlet of the main premixed fuel passage.
  • a premixed fuel produced by mixing the fuel jetted through the main fuel nozzle 21 and combustion air is swirled.
  • the swirling premixed fuel is jetted through the premixed fuel outlet 22b into the premixed combustion zone V.
  • the present specification defines the sum of the respective sectional areas of the main premixed fuel passage 22 and the swirler 14 as a main air passage area S.
  • the main air passage area S is determined such that the air-fuel ratio of the premixed fuel in the premixed combustion zone V while the gas turbine engine is in a partial-load operation under a predetermined load, such as a load equal to 50% of a maximum load, is nearly equal to the limited air-fuel ratio for an operation under a predetermined load nearly equal to a maximum load, such as a load equal to 80% of the maximum load.
  • the main air passage area S is smaller than an ordinary main air passage area.
  • the two-stage additive fuel supply unit 7 supplies fuel additionally for after burning into a predetermined zone downstream of the premixed combustion zone V, in which stable low-NO x , low-CO combustion is carried out, in the combustion chamber 5 during a partial-load operation to suppress the generation of NO x .
  • the two-stage additive fuel supply unit 7 has a predetermined number of additive fuel supply tubes 31 penetrate parts corresponding to the predetermined zone of the inner tube 2 defining the combustion chamber 5, and additive fuel supply nozzles 32 having end parts of a predetermined length inserted into the additive fuel supply tubes 31.
  • the additive fuel supply nozzles 32 may be either of diffusion nozzles as shown in Fig. 1 and premixed combustion nozzles, not shown.
  • the two-stage additive fuel supply unit 7 includes a first additive fuel supply device 7A and a second additive fuel supply device 7B.
  • the first additive fuel supply device 7a and the second additive fuel supply device 7B are disposed at a first longitudinal distance L1 and a second longitudinal distance L2, respectively, from the premixed fuel outlet 22b.
  • the distance L2 is greater than the distance L1.
  • the first distance L1, the second distance L2, the numbers of the tubes 31 and the additive fuel supply nozzles 32 of the additive fuel supply devices 7a and 7B, the pattern of arrangement, such as a straight pattern or a zigzag pattern, of the additive fuel supply nozzles 32, the ratio between the main air passage area S and the sum of the sectional areas of the air passages of the two-stage additive fuel supply unit 7, and the ratio between the respective sectional areas of the first additive fuel supply device 7A and the second additive fuel supply device 7B are selectively determined so that the rate of emission of NO x and CO may be small and stable combustion can be achieved.
  • the ratio D1 of the main air passage area S to the total sectional area of the two-stage additive fuel supply unit 7 is, for example, 5/5
  • the ratio D2 of the total sectional area of the first additive fuel supply device 7A to the total sectional area of the second additive fuel supply device 7B is, for example, 4/6.
  • the ratio D1 is reduced to 4/6 or such to widen the range of low-load operation.
  • the ratio D2 is reduced to 3/7 or such to widen the range of low-load operation.
  • the main air passage area S of the combustor U in this embodiment is determined so that the combustor U can achieve stable combustion at a low rate of emission of NO x and CO while the gas turbine engine is in a partial-load operation, and the fuel additionally supplied by the two-stage additive fuel supply unit 7 burns in the combustion chamber 5. Therefore, a proper air-fuel ratio in accordance with a given load can be determined so that the generation of NO x and CO can be suppressed.
  • the combustor U can maintain stable combustion at a low rate of emission of NO x and CO for the operation of the gas turbine in a wide load range.
  • FIG. 2 Shown in Fig. 2 are load characteristics of NO x and CO concentrations of the exhaust gas discharged from a combustor in the comparative example provided with only the first additive fuel supply device 7A and load characteristics of NO x and CO concentrations of the exhaust gas discharged from a combustor in the present example provided with the first additive fuel supply device 7A and the second additive fuel supply device 7B.
  • H1 shows the allowable upper limit of NO x concentration
  • H2 shows the allowable upper limit of CO concentration.
  • the NO x concentration of the exhaust gas discharged from the combustor in the present example is lower than that of the exhaust gas discharged from the combustor in the comparative example in the entire load range.
  • the additive fuel supply devices 7A and 7B are effective in reducing the NO x and the CO concentration of the exhaust gas.
  • the CO concentration of the exhaust gas discharged from the combustor in the present example is below the allowable upper limit H2 of CO concentration in the entire load range, which proves that the additive fuel supply devices 7A and 7B are effective in reducing the CO concentration of the exhaust gas.
  • the CO concentration of the exhaust gas generated by the combustor in the comparative example is higher than the allowable upper limit H2 of CO concentration at loads below a predetermined load E1. Therefore, the combustor in the comparative example should not be operated at loads below the predetermined load E1 from the viewpoint of environmental conservation.
  • the two-stage additive fuel supply unit 7 including the additive fuel supply devices 7A and 7B expands the load range in which the combustor can operate without causing problems in environmental conservation.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP06255437A 2005-10-24 2006-10-23 Chambre de combustion pour turbine à gaz Withdrawn EP1777459A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2005308380A JP2007113888A (ja) 2005-10-24 2005-10-24 ガスタービンエンジンの燃焼器構造

Publications (2)

Publication Number Publication Date
EP1777459A2 true EP1777459A2 (fr) 2007-04-25
EP1777459A3 EP1777459A3 (fr) 2009-10-07

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US (1) US20070089419A1 (fr)
EP (1) EP1777459A3 (fr)
JP (1) JP2007113888A (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2446164A (en) * 2007-02-05 2008-08-06 Ntnu Technology Transfer As Gas Turbine Emissions Reduction with Premixed and Diffusion Combustion
WO2009038625A3 (fr) * 2007-09-14 2010-05-06 Siemens Energy, Inc. Système de combustion axial à étages multiples
WO2013043076A1 (fr) * 2011-09-22 2013-03-28 General Electric Company Brûleur et procédé d'alimentation en combustible d'un brûleur
EP2914907B1 (fr) * 2012-11-02 2018-07-04 Exxonmobil Upstream Research Company Système et procédé pour combustion par diffusion à l'aide d'un mélange de combustible-diluant dans un système de turbine à gaz à recirculation de gaz d'échappement st chiométrique

Families Citing this family (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8387398B2 (en) 2007-09-14 2013-03-05 Siemens Energy, Inc. Apparatus and method for controlling the secondary injection of fuel
US8689559B2 (en) * 2009-03-30 2014-04-08 General Electric Company Secondary combustion system for reducing the level of emissions generated by a turbomachine
WO2013002664A1 (fr) * 2011-06-28 2013-01-03 General Electric Company Injection pauvre retardée rationnelle
US8919137B2 (en) * 2011-08-05 2014-12-30 General Electric Company Assemblies and apparatus related to integrating late lean injection into combustion turbine engines
CN103917826B (zh) * 2011-11-17 2016-08-24 通用电气公司 涡轮机燃烧器组件和操作涡轮机的方法
US20130213046A1 (en) * 2012-02-16 2013-08-22 General Electric Company Late lean injection system
US10378456B2 (en) 2012-10-01 2019-08-13 Ansaldo Energia Switzerland AG Method of operating a multi-stage flamesheet combustor
US9347669B2 (en) 2012-10-01 2016-05-24 Alstom Technology Ltd. Variable length combustor dome extension for improved operability
US10060630B2 (en) 2012-10-01 2018-08-28 Ansaldo Energia Ip Uk Limited Flamesheet combustor contoured liner
US9897317B2 (en) 2012-10-01 2018-02-20 Ansaldo Energia Ip Uk Limited Thermally free liner retention mechanism
US20150184858A1 (en) * 2012-10-01 2015-07-02 Peter John Stuttford Method of operating a multi-stage flamesheet combustor
JP6033887B2 (ja) * 2012-12-13 2016-11-30 川崎重工業株式会社 マルチ燃料対応のガスタービン燃焼器
EP3008391B1 (fr) * 2013-06-11 2020-05-06 United Technologies Corporation Chambre de combustion à étagement axial pour un moteur à turbine à gaz
US20150052905A1 (en) * 2013-08-20 2015-02-26 General Electric Company Pulse Width Modulation for Control of Late Lean Liquid Injection Velocity
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US20150167980A1 (en) * 2013-12-18 2015-06-18 Jared M. Pent Axial stage injection dual frequency resonator for a combustor of a gas turbine engine
EP2955445B1 (fr) 2014-06-12 2019-11-27 Kawasaki Jukogyo Kabushiki Kaisha Chambre de combustion de turbine a gaz operant avec differents types de carburants
JP6516996B2 (ja) * 2014-10-10 2019-05-22 川崎重工業株式会社 燃焼器及びガスタービンエンジン
JP2016109309A (ja) * 2014-12-02 2016-06-20 川崎重工業株式会社 ガスタービン用燃焼器、及びガスタービン
JP5993046B2 (ja) * 2015-02-13 2016-09-14 川崎重工業株式会社 マルチ燃料対応のガスタービン燃焼器
US10480792B2 (en) * 2015-03-06 2019-11-19 General Electric Company Fuel staging in a gas turbine engine
WO2017027349A1 (fr) * 2015-08-07 2017-02-16 Red Valve Company, Inc. Collier d'écoulement libre pour soupapes de commande
JP6039033B2 (ja) * 2015-09-24 2016-12-07 新潟原動機株式会社 ガスタービン燃焼器
US9989260B2 (en) * 2015-12-22 2018-06-05 General Electric Company Staged fuel and air injection in combustion systems of gas turbines
US9938903B2 (en) * 2015-12-22 2018-04-10 General Electric Company Staged fuel and air injection in combustion systems of gas turbines
CN105423344B (zh) * 2016-01-12 2017-12-29 西北工业大学 一种地面燃机燃烧室的火焰筒结构
US10584880B2 (en) * 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10605459B2 (en) * 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10584876B2 (en) * 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US11187415B2 (en) * 2017-12-11 2021-11-30 General Electric Company Fuel injection assemblies for axial fuel staging in gas turbine combustors
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11846426B2 (en) 2021-06-24 2023-12-19 General Electric Company Gas turbine combustor having secondary fuel nozzles with plural passages for injecting a diluent and a fuel
CN114353121B (zh) * 2022-01-18 2022-12-20 上海交通大学 一种用于燃气轮机的多喷嘴燃料注入方法
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages
DE102022208339A1 (de) * 2022-08-10 2024-02-15 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung zum Betrieb mit flüssigem und/oder gasförmigem Kraftstoff, Gasturbinenanordnung und Verfahren

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1793640A (en) * 1926-04-26 1931-02-24 Holzwarth Gas Turbine Co Combustion engine
US2679295A (en) * 1949-12-30 1954-05-25 Gen Electric Helicopter blade jet combustion chamber
BE503026A (fr) * 1950-07-17
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
US4910957A (en) * 1988-07-13 1990-03-27 Prutech Ii Staged lean premix low nox hot wall gas turbine combustor with improved turndown capability
GB9023004D0 (en) * 1990-10-23 1990-12-05 Rolls Royce Plc A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber
EP0540167A1 (fr) * 1991-09-27 1993-05-05 General Electric Company Chambre de combustion avec prémélange en cascade à émission réduite en NOx
US5452574A (en) * 1994-01-14 1995-09-26 Solar Turbines Incorporated Gas turbine engine catalytic and primary combustor arrangement having selective air flow control
JP2950720B2 (ja) * 1994-02-24 1999-09-20 株式会社東芝 ガスタービン燃焼装置およびその燃焼制御方法
DE4416650A1 (de) * 1994-05-11 1995-11-16 Abb Management Ag Verbrennungsverfahren für atmosphärische Feuerungsanlagen
DE4441235A1 (de) * 1994-11-19 1996-05-23 Abb Management Ag Brennkammer mit Mehrstufenverbrennung
US6047550A (en) * 1996-05-02 2000-04-11 General Electric Co. Premixing dry low NOx emissions combustor with lean direct injection of gas fuel
GB9609317D0 (en) * 1996-05-03 1996-07-10 Rolls Royce Plc A combustion chamber and a method of operation thereof
FR2779807B1 (fr) * 1998-06-11 2000-07-13 Inst Francais Du Petrole Chambre de combustion de turbine a gaz a geometrie variable
GB9818160D0 (en) * 1998-08-21 1998-10-14 Rolls Royce Plc A combustion chamber
GB9911867D0 (en) * 1999-05-22 1999-07-21 Rolls Royce Plc A combustion chamber assembly and a method of operating a combustion chamber assembly
GB9915770D0 (en) * 1999-07-07 1999-09-08 Rolls Royce Plc A combustion chamber
US20060107667A1 (en) * 2004-11-22 2006-05-25 Haynes Joel M Trapped vortex combustor cavity manifold for gas turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2446164A (en) * 2007-02-05 2008-08-06 Ntnu Technology Transfer As Gas Turbine Emissions Reduction with Premixed and Diffusion Combustion
WO2009038625A3 (fr) * 2007-09-14 2010-05-06 Siemens Energy, Inc. Système de combustion axial à étages multiples
US7886539B2 (en) 2007-09-14 2011-02-15 Siemens Energy, Inc. Multi-stage axial combustion system
WO2013043076A1 (fr) * 2011-09-22 2013-03-28 General Electric Company Brûleur et procédé d'alimentation en combustible d'un brûleur
US9388987B2 (en) 2011-09-22 2016-07-12 General Electric Company Combustor and method for supplying fuel to a combustor
DE112011105655B4 (de) 2011-09-22 2023-05-25 General Electric Company Brenner und Verfahren zur Brennstoffzufuhr zu einem Brenner
EP2914907B1 (fr) * 2012-11-02 2018-07-04 Exxonmobil Upstream Research Company Système et procédé pour combustion par diffusion à l'aide d'un mélange de combustible-diluant dans un système de turbine à gaz à recirculation de gaz d'échappement st chiométrique

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Publication number Publication date
JP2007113888A (ja) 2007-05-10
EP1777459A3 (fr) 2009-10-07
US20070089419A1 (en) 2007-04-26

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