US20130189632A1 - Fuel nozzel - Google Patents

Fuel nozzel Download PDF

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Publication number
US20130189632A1
US20130189632A1 US13/355,580 US201213355580A US2013189632A1 US 20130189632 A1 US20130189632 A1 US 20130189632A1 US 201213355580 A US201213355580 A US 201213355580A US 2013189632 A1 US2013189632 A1 US 2013189632A1
Authority
US
United States
Prior art keywords
fuel
flow
air
nozzle
fuel nozzle
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.)
Abandoned
Application number
US13/355,580
Other languages
English (en)
Inventor
Arvind Venugopal Menon
Ilya Aleksandrovich Slobodyanskiy
Abinash Baruah
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US13/355,580 priority Critical patent/US20130189632A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Menon, Arvind Venugopal, SLOBODYANSKIY, ILYA ALEKSANDROVICH, BARUAH, ABINASH
Priority to JP2013005861A priority patent/JP2013148341A/ja
Priority to EP20130152025 priority patent/EP2618052A1/fr
Priority to CN2013100231995A priority patent/CN103216849A/zh
Priority to RU2013102632/06A priority patent/RU2013102632A/ru
Publication of US20130189632A1 publication Critical patent/US20130189632A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/386—Nozzle cleaning
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Definitions

  • the present application and the resultant patent relate generally to a gas turbine engine and more particularly relate to a fuel nozzle with a nozzle collar having a number of purge holes therein for improved fuel-air mixing, flame holding resistance, and overall performance.
  • a gas turbine engine may employ one or more fuel nozzles to facilitate fuel-air mixing in a combustor.
  • Each fuel nozzle may direct a flow of fuel, a flow of air, and optional flows of other fluids into the combustor for combustion therein.
  • a combustion flame may flash back and/or hold to a surface of the fuel nozzle. Flame holding may cause significant damage to the fuel nozzles and/or reduce the performance of the fuel nozzles and the overall gas turbine engine.
  • flame holding may occur if a flammable fuel-air mixture resides in a low velocity region in close proximity to a combustion source.
  • low velocity regions generally may be found near the interior walls of the fuel nozzles due to the aerodynamics therein.
  • Such a flammable mixture potentially may result in flame holding inside the fuel nozzles. Flame holding inside fuel nozzles may result in the fuel nozzles burning out, i.e., experiencing flame damage therein.
  • an improved fuel nozzle design may limit or reduce flammable fuel/air mixtures in low velocity regions about the fuel nozzles so as to limit flame holding and the like. Limiting flame holding should improve the overall performance and durability of the fuel nozzles and the gas turbine engine.
  • the present application and the resultant patent thus provide an example of a fuel nozzle for mixing a flow of fuel and a flow of air.
  • the fuel nozzle may include a downstream face, a number of fuel passages positioned about the downstream face for the flow of fuel, and a nozzle collar position about the downstream face.
  • the nozzle collar may include a number of air vanes for the flow of air and one or more purge holes therethrough.
  • the present application and the resultant patent further provide an example of a method of limiting flame holding about a fuel nozzle.
  • the method may include the steps of providing a flow of fuel through a downstream face of the fuel nozzle, providing a flow of air through a number of air vanes of a nozzle collar of the fuel nozzle, mixing the flow of fuel and the flow of air downstream of the fuel nozzle, providing a flow of purge air through a number of purge holes in the air vanes, and limiting the creation of one or more recirculation zones downstream of the fuel nozzle with the flow of purge air.
  • the present application and the resultant patent further provide an example of a combustor for use with a gas turbine engine.
  • the combustor may include a combustion chamber and a number of fuel nozzles positioned about the combustion chamber.
  • Each of the fuel nozzles may include a nozzle collar thereon.
  • the nozzle collar may include one or more air vanes with one or more purge holes for a flow of purge air therethrough.
  • FIG. 1 is a schematic diagram of a gas turbine engine showing a compressor, a combustor, and a turbine.
  • FIG. 2 is a side view of an example of the compressor such as that shown in FIG. 1 .
  • FIG. 3 is a perspective view of an example of a fuel nozzle with a nozzle collar as may be described herein.
  • FIG. 4 is a partial side cross-sectional view of the fuel nozzle with the nozzle collar of FIG. 3 .
  • FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
  • the gas turbine engine 10 may include a compressor 15 .
  • the compressor 15 compresses an incoming flow of air 20 .
  • the compressor 15 delivers the compressed flow of air 20 to a combustor 25 .
  • the combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35 .
  • the gas turbine engine 10 may include any number of combustors 25 .
  • the flow of combustion gases 35 is in turn delivered to a turbine 40 .
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
  • Other configurations and other components may be used herein.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • Other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • FIG. 2 shows an example of the combustor 25 that may be used with the gas turbine engine 10 and the like.
  • the combustor 25 may include a number of fuel nozzles 55 therein. As described above, each of the fuel nozzles 55 may direct a flow of air 20 , a flow of fuel 30 , and optional flows of other fluids into the combustor 25 for combustion therein. Any number of the fuel nozzles 55 may be used in any configuration.
  • the fuel nozzles 55 may be attached to an end cover 60 near a head end 65 of the combustor 25 .
  • the flows of air 20 and fuel 30 may be directed through the end cover 60 and the head end 65 to each of the fuel nozzles 55 so as to distribute a fuel-air mixture therein.
  • the combustor 25 also may include a combustion chamber 70 therein.
  • the combustion chamber 70 may be defined by a combustion casing 75 , a combustion liner 80 , a flow sleeve 85 , and the like.
  • the liner 80 and the flow sleeve 85 may be coaxially positioned with respect to one another so as to define an air pathway 90 for the flow of air 20 therethrough.
  • the combustion chamber 70 may lead to a downstream transition piece 95 .
  • the flows of air 20 and fuel 30 may mix downstream of the fuel nozzles 55 for combustion within the combustion chamber 70 .
  • the flow of combustion gases 35 then may be directed via the transition piece 95 towards the turbine 40 so as to produce useful work therein.
  • Other components and other configuration also may be used herein.
  • FIG. 3 and FIG. 4 show an example of a fuel nozzle 100 as may be described herein.
  • the fuel nozzle 100 may include an outer tube 110 .
  • the outer tube 110 may lead to a downstream face 120 with a fuel nozzle tip 130 .
  • the outer tube 110 may include a number of fuel and air passages therein. Specifically, a number of fuel passages 140 may extend therethrough and may be axially positioned about the downstream face 120 .
  • the fuel passages 140 may be in communication with the flow of fuel 30 .
  • a number of tip outlets 150 also may extend therethrough and may be positioned about the fuel nozzle tip 130 .
  • the tip outlets 150 may be in communication with the flow of fuel 30 , the flow of air 20 , or other types of flows.
  • the flows of fuel 30 extending through the fuel passages 140 and through the tip outlets 150 may be the same and/or different types of fuel flows depending upon the nature of the combustion and other types of parameters. Other components and other configurations also may be used herein.
  • the fuel nozzle 100 also may include a nozzle collar 160 positioned about the downstream end of the outer tube 110 .
  • the nozzle collar 160 may surround the downstream face 120 and the fuel nozzle tip 130 .
  • the nozzle collar 160 may include a number of air vanes 170 .
  • the air vanes 170 may be angled so as to direct the flow of air 20 therethrough and/or to impart swirl therein.
  • the air vanes 170 may have size, shape, or configuration. Any number of the air vanes 170 may be used.
  • the air vanes 170 may direct the flow of air 20 about the fuel passages 140 and the tip outlets 150 .
  • the air vanes 170 may support a downstream ring 180 at the end thereof.
  • Other components and other configurations also may be used herein.
  • a number of recirculation zones 190 may be formed as a result of the interaction between the flows of air 20 and fuel 30 . These recirculation zones 190 may lead to flame holding about the fuel nozzle 100 via a region of low velocity.
  • a number of purge holes 200 may be positioned through the air vanes 170 .
  • the purge holes 200 may have any size, shape, or configuration. Any number of the purge hole 200 may be used herein.
  • the purge holes 200 may be angled and/or multiple angles may be used herein. Additional purge holes 200 also may extend through the downstream ring 180 and/or elsewhere. Other components and other configurations may be used herein.
  • the purge holes 200 thus provide for a flow of purge air 210 therethrough as part of the overall flow of air 20 .
  • the flow of purge air 210 through the purge holes 200 may disrupt the recirculation zones 190 downstream of the fuel nozzles 100 caused by the regions of low velocity or otherwise.
  • the purge holes 200 may be angled such that the purge air 210 disrupts the creation of the recirculation zones 190 in a substantially circumferential direction. Elimination or reduction of these recirculation zones 190 along the circumferential direction should reduce flame holding thereon. As such, the reduction in flame holding should provide the fuel nozzle 100 with improved durability and lifetime.
  • the overall gas turbine engine 100 may have improved emissions and overall improved performance.
  • the use of the purge holes 200 with the flow of purge air 210 therethrough may be original equipment or added as part of a retrofit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
US13/355,580 2012-01-23 2012-01-23 Fuel nozzel Abandoned US20130189632A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US13/355,580 US20130189632A1 (en) 2012-01-23 2012-01-23 Fuel nozzel
JP2013005861A JP2013148341A (ja) 2012-01-23 2013-01-17 燃料ノズル
EP20130152025 EP2618052A1 (fr) 2012-01-23 2013-01-21 Buse de combustible
CN2013100231995A CN103216849A (zh) 2012-01-23 2013-01-22 燃料喷嘴
RU2013102632/06A RU2013102632A (ru) 2012-01-23 2013-01-22 Топливная форсунка, способ ограничения стабилизации пламени и камера сгорания

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/355,580 US20130189632A1 (en) 2012-01-23 2012-01-23 Fuel nozzel

Publications (1)

Publication Number Publication Date
US20130189632A1 true US20130189632A1 (en) 2013-07-25

Family

ID=47563290

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/355,580 Abandoned US20130189632A1 (en) 2012-01-23 2012-01-23 Fuel nozzel

Country Status (5)

Country Link
US (1) US20130189632A1 (fr)
EP (1) EP2618052A1 (fr)
JP (1) JP2013148341A (fr)
CN (1) CN103216849A (fr)
RU (1) RU2013102632A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170045231A1 (en) * 2014-05-02 2017-02-16 Siemens Aktiengesellschaft Combustor burner arrangement
US9803552B2 (en) 2015-10-30 2017-10-31 General Electric Company Turbine engine fuel injection system and methods of assembling the same
WO2022098441A2 (fr) 2020-10-26 2022-05-12 Solar Turbines Incorporated Injecteur de carburant prémélangé résistant au retour de flamme pour un turbomoteur à gaz

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10775048B2 (en) * 2017-03-15 2020-09-15 General Electric Company Fuel nozzle for a gas turbine engine
CN107166435A (zh) * 2017-07-07 2017-09-15 西安富兰克石油技术有限公司 一种多燃料喷嘴、燃料喷出系统及其涡轮发动机

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US4155220A (en) * 1977-01-21 1979-05-22 Westinghouse Electric Corp. Combustion apparatus for a gas turbine engine
US4598553A (en) * 1981-05-12 1986-07-08 Hitachi, Ltd. Combustor for gas turbine
US5193346A (en) * 1986-11-25 1993-03-16 General Electric Company Premixed secondary fuel nozzle with integral swirler
US5345768A (en) * 1993-04-07 1994-09-13 General Electric Company Dual-fuel pre-mixing burner assembly
US6068467A (en) * 1998-02-09 2000-05-30 Mitsubishi Heavy Industries, Ltd. Combustor
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
US6547163B1 (en) * 1999-10-01 2003-04-15 Parker-Hannifin Corporation Hybrid atomizing fuel nozzle
US6655145B2 (en) * 2001-12-20 2003-12-02 Solar Turbings Inc Fuel nozzle for a gas turbine engine
US20050198965A1 (en) * 2004-03-12 2005-09-15 John Henriquez Primary fuel nozzle having dual fuel capability
US7251940B2 (en) * 2004-04-30 2007-08-07 United Technologies Corporation Air assist fuel injector for a combustor
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US20100229556A1 (en) * 2009-03-16 2010-09-16 General Electric Company Turbine fuel nozzle having heat control
US20100269507A1 (en) * 2009-04-23 2010-10-28 Abdul Rafey Khan Radial lean direct injection burner
US20100281871A1 (en) * 2009-05-06 2010-11-11 Mark Allan Hadley Airblown Syngas Fuel Nozzle with Diluent Openings
US20100281869A1 (en) * 2009-05-06 2010-11-11 Mark Allan Hadley Airblown Syngas Fuel Nozzle With Diluent Openings
US20100287937A1 (en) * 2009-05-12 2010-11-18 General Electric Company Automatic fuel nozzle flame-holding quench
US20110005189A1 (en) * 2009-07-08 2011-01-13 General Electric Company Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle
US20110107769A1 (en) * 2009-11-09 2011-05-12 General Electric Company Impingement insert for a turbomachine injector
US20110225973A1 (en) * 2010-03-18 2011-09-22 General Electric Company Combustor with Pre-Mixing Primary Fuel-Nozzle Assembly
US20120011854A1 (en) * 2010-07-13 2012-01-19 Abdul Rafey Khan Flame tolerant secondary fuel nozzle
US8117846B2 (en) * 2006-02-15 2012-02-21 Siemens Aktiengesellschaft Gas turbine burner and method of mixing fuel and air in a swirling area of a gas turbine burner
US20120073302A1 (en) * 2010-09-27 2012-03-29 General Electric Company Fuel nozzle assembly for gas turbine system
US20120175430A1 (en) * 2011-01-06 2012-07-12 General Electric Company System and method for enhancing flow in a nozzle
US20120208135A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120208137A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120208136A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120291447A1 (en) * 2011-05-18 2012-11-22 General Electric Company Combustor nozzle and method for supplying fuel to a combustor
US8408002B2 (en) * 2004-09-10 2013-04-02 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
US20130125553A1 (en) * 2011-11-23 2013-05-23 Donald Mark Bailey Swirler Assembly with Compressor Discharge Injection to Vane Surface

Family Cites Families (4)

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Publication number Priority date Publication date Assignee Title
GB2332509B (en) * 1997-12-19 2002-06-19 Europ Gas Turbines Ltd Fuel/air mixing arrangement for combustion apparatus
GB2373043B (en) * 2001-03-09 2004-09-22 Alstom Power Nv Fuel injector
EP1867925A1 (fr) * 2006-06-12 2007-12-19 Siemens Aktiengesellschaft Brûleur
FR2903169B1 (fr) * 2006-06-29 2011-11-11 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4155220A (en) * 1977-01-21 1979-05-22 Westinghouse Electric Corp. Combustion apparatus for a gas turbine engine
US4598553A (en) * 1981-05-12 1986-07-08 Hitachi, Ltd. Combustor for gas turbine
US5193346A (en) * 1986-11-25 1993-03-16 General Electric Company Premixed secondary fuel nozzle with integral swirler
US5345768A (en) * 1993-04-07 1994-09-13 General Electric Company Dual-fuel pre-mixing burner assembly
US6068467A (en) * 1998-02-09 2000-05-30 Mitsubishi Heavy Industries, Ltd. Combustor
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
US6547163B1 (en) * 1999-10-01 2003-04-15 Parker-Hannifin Corporation Hybrid atomizing fuel nozzle
US6655145B2 (en) * 2001-12-20 2003-12-02 Solar Turbings Inc Fuel nozzle for a gas turbine engine
US20050198965A1 (en) * 2004-03-12 2005-09-15 John Henriquez Primary fuel nozzle having dual fuel capability
US7000403B2 (en) * 2004-03-12 2006-02-21 Power Systems Mfg., Llc Primary fuel nozzle having dual fuel capability
US7251940B2 (en) * 2004-04-30 2007-08-07 United Technologies Corporation Air assist fuel injector for a combustor
US8408002B2 (en) * 2004-09-10 2013-04-02 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
US7677471B2 (en) * 2005-03-17 2010-03-16 Pratt & Whitney Canada Corp. Modular fuel nozzle and method of making
US8117846B2 (en) * 2006-02-15 2012-02-21 Siemens Aktiengesellschaft Gas turbine burner and method of mixing fuel and air in a swirling area of a gas turbine burner
US20090224082A1 (en) * 2007-07-27 2009-09-10 General Electric Company Fuel Nozzle Assemblies and Methods
US8276836B2 (en) * 2007-07-27 2012-10-02 General Electric Company Fuel nozzle assemblies and methods
US20090111063A1 (en) * 2007-10-29 2009-04-30 General Electric Company Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor
US20100064691A1 (en) * 2008-09-15 2010-03-18 Laster Walter R Flashback resistant pre-mixer assembly
US8113000B2 (en) * 2008-09-15 2012-02-14 Siemens Energy, Inc. Flashback resistant pre-mixer assembly
US20100229556A1 (en) * 2009-03-16 2010-09-16 General Electric Company Turbine fuel nozzle having heat control
US8186165B2 (en) * 2009-03-16 2012-05-29 General Electric Company Turbine fuel nozzle having heat control
US20100269507A1 (en) * 2009-04-23 2010-10-28 Abdul Rafey Khan Radial lean direct injection burner
US8256226B2 (en) * 2009-04-23 2012-09-04 General Electric Company Radial lean direct injection burner
US20100281869A1 (en) * 2009-05-06 2010-11-11 Mark Allan Hadley Airblown Syngas Fuel Nozzle With Diluent Openings
US20100281871A1 (en) * 2009-05-06 2010-11-11 Mark Allan Hadley Airblown Syngas Fuel Nozzle with Diluent Openings
US8607570B2 (en) * 2009-05-06 2013-12-17 General Electric Company Airblown syngas fuel nozzle with diluent openings
US20100287937A1 (en) * 2009-05-12 2010-11-18 General Electric Company Automatic fuel nozzle flame-holding quench
US8359870B2 (en) * 2009-05-12 2013-01-29 General Electric Company Automatic fuel nozzle flame-holding quench
US20110005189A1 (en) * 2009-07-08 2011-01-13 General Electric Company Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle
US20110107769A1 (en) * 2009-11-09 2011-05-12 General Electric Company Impingement insert for a turbomachine injector
US20110225973A1 (en) * 2010-03-18 2011-09-22 General Electric Company Combustor with Pre-Mixing Primary Fuel-Nozzle Assembly
US20120011854A1 (en) * 2010-07-13 2012-01-19 Abdul Rafey Khan Flame tolerant secondary fuel nozzle
US8959921B2 (en) * 2010-07-13 2015-02-24 General Electric Company Flame tolerant secondary fuel nozzle
US20120073302A1 (en) * 2010-09-27 2012-03-29 General Electric Company Fuel nozzle assembly for gas turbine system
US20120175430A1 (en) * 2011-01-06 2012-07-12 General Electric Company System and method for enhancing flow in a nozzle
US8579211B2 (en) * 2011-01-06 2013-11-12 General Electric Company System and method for enhancing flow in a nozzle
US20120208135A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120208137A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120208136A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120291447A1 (en) * 2011-05-18 2012-11-22 General Electric Company Combustor nozzle and method for supplying fuel to a combustor
US20130125553A1 (en) * 2011-11-23 2013-05-23 Donald Mark Bailey Swirler Assembly with Compressor Discharge Injection to Vane Surface

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170045231A1 (en) * 2014-05-02 2017-02-16 Siemens Aktiengesellschaft Combustor burner arrangement
US10533748B2 (en) * 2014-05-02 2020-01-14 Siemens Aktiengesellschaft Combustor burner arrangement
US9803552B2 (en) 2015-10-30 2017-10-31 General Electric Company Turbine engine fuel injection system and methods of assembling the same
WO2022098441A2 (fr) 2020-10-26 2022-05-12 Solar Turbines Incorporated Injecteur de carburant prémélangé résistant au retour de flamme pour un turbomoteur à gaz
WO2022098441A3 (fr) * 2020-10-26 2022-08-11 Solar Turbines Incorporated Injecteur de carburant prémélangé résistant au retour de flamme pour un turbomoteur à gaz
US11680709B2 (en) 2020-10-26 2023-06-20 Solar Turbines Incorporated Flashback resistant premixed fuel injector for a gas turbine engine
CN116438407A (zh) * 2020-10-26 2023-07-14 索拉透平公司 用于燃气涡轮发动机的抗回火预混合燃料喷射器

Also Published As

Publication number Publication date
EP2618052A1 (fr) 2013-07-24
JP2013148341A (ja) 2013-08-01
RU2013102632A (ru) 2014-07-27
CN103216849A (zh) 2013-07-24

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