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US20090249789A1 - Burner tube premixer and method for mixing air and gas in a gas turbine engine - Google Patents

Burner tube premixer and method for mixing air and gas in a gas turbine engine Download PDF

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Publication number
US20090249789A1
US20090249789A1 US12/099,241 US9924108A US2009249789A1 US 20090249789 A1 US20090249789 A1 US 20090249789A1 US 9924108 A US9924108 A US 9924108A US 2009249789 A1 US2009249789 A1 US 2009249789A1
Authority
US
United States
Prior art keywords
fuel
burner
burner tube
air
slots
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
US12/099,241
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English (en)
Inventor
Baifang Zuo
Abdul Rafey Khan
Christian X. Stevenson
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
Individual
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 Individual filed Critical Individual
Priority to US12/099,241 priority Critical patent/US20090249789A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KHAN, ABDUL RAFEY, STEVENSON, CHRISTIAN X., ZUO, BAIFANG
Assigned to ENERGY, UNITED STATES DEPARTMENT OF reassignment ENERGY, UNITED STATES DEPARTMENT OF CONFIRMATORY LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: GENERAL ELECTRIC COMPANY
Priority to JP2009024707A priority patent/JP2009250604A/ja
Priority to FR0950762A priority patent/FR2929688A1/fr
Priority to DE102009003453A priority patent/DE102009003453A1/de
Priority to CNA2009101307158A priority patent/CN101556043A/zh
Publication of US20090249789A1 publication Critical patent/US20090249789A1/en
Abandoned 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the present invention relates to an air fuel mixer for the combustor of a gas turbine engine, and to a method for mixing air and fuel.
  • the primary air polluting emissions usually produced by gas turbines burning conventional hydrocarbon fuels are oxides of nitrogen, carbon monoxide, and unburned hydrocarbons.
  • the oxidation of molecular nitrogen in air breathing engines is highly dependent upon the maximum hot gas temperature in the combustion system reaction zone.
  • the rate of chemical reactions forming oxides of nitrogen (NOx) is an exponential function of temperature. If the temperature of the combustion chamber hot gas is controlled to a sufficiently low level, thermal NOx will not be produced.
  • One method of controlling the temperature of the reaction zone of a combustor below the level at which thermal NOx is formed is to premix fuel and air to a lean mixture prior to combustion.
  • the thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and reduces the temperature rise of the products of combustion to a level where thermal NOx is not formed.
  • the mixture of fuel and air exiting the premixer and entering the reaction zone of the combustor must be very uniform to achieve the desired emissions performance. If regions in the flow field exist where fuel/air mixture strength is significantly richer than average, the products of combustion in these regions will reach a higher temperature than average, and thermal NOx will be formed. This can result in failure to meet NOx emissions objectives depending upon the combination of temperature and residence time. If regions in the flow field exist where the fuel/air mixture strength is significantly leaner than average, then quenching may occur with failure to oxidize hydrocarbons and/or carbon monoxide to equilibrium levels. This can result in failure to meet carbon monoxide (CO) and/or unburned hydrocarbon (UHC) emissions objectives.
  • CO carbon monoxide
  • UHC unburned hydrocarbon
  • a burner for use in a gas turbine engine comprises a burner tube having an inlet end and an outlet end; a plurality of slots formed in the burner tube and configured to introduce air flows tangentially into the burner tube and impart swirl to the air flows; a plurality of fuel passages extending axially along the burner tube; and a plurality of fuel injection holes provided to each fuel passage. At least one of the fuel injection holes of each fuel passage is configured to inject a fuel flow tangentially into the burner tube between air flows of adjacent slots to form a fuel and air co-flow.
  • a method of mixing air and fuel in a burner of a gas turbine includes a burner tube comprising a plurality of slots formed in the burner tube.
  • the method comprises introducing air flows tangentially into the burner tube through the slots and imparting swirl to the air flows; and injecting fuel between air flows of adjacent slots to form fuel and air co-flows.
  • FIG. 1 schematically depicts a perspective of a burner according to an embodiment of the invention
  • FIG. 2 schematically depicts a cross section of the burner of FIG. 1 along 2 - 2 ;
  • FIG. 3 schematically depicts a cross section of the burner of FIG. 1 along 3 - 3 .
  • a burner 2 comprises a burner tube 4 having an inlet end 6 and an outlet end 8 .
  • a flange 10 is provided to the burner tube 4 for mounting the burner 2 into a gas turbine engine. It should be appreciated that the flange 10 may be integrally formed with the burner tube 4 , or may be provided separately. It should also be appreciated that other mounting arrangements may be provided for the burner 2 .
  • a plurality of slots 12 are formed in the burner tube 4 . Air is introduced tangentially into the burner tube 4 through the slots 12 . Each slot 12 has a spiral, or swirling, configuration to impart swirl to combustion air entering the slot 12 .
  • the burner tube 4 comprises a plurality of fuel passages 14 that extend axially along the burner tube 4 .
  • a plurality of fuel injection holes 16 are provided to inject fuel tangentially into the burner tube 4 from the fuel passages 14 .
  • the fuel passages 14 are formed in the burner tube 4 between an exterior wall 36 and an interior wall 30 .
  • a converging central body 18 is provided in the burner tube 4 to accelerate the mixture of air and fuel along the axis of the burner tube 4 and to maintain no flow separation at the surface of the central body 18 .
  • the central body 18 has a central body tip 32 adjacent to the outlet end 8 of the burner tube 4 .
  • the central body 18 also comprises a central passage 20 to allow purge air to flow through the central body 18 to prevent flame holding at the central body 18 , for example at the central body tip 32 .
  • the slots 12 each have a slot end 22 that is tangential to the axis 34 of the burner tube 4 to minimize disturbance in the mixing of the air and fuel.
  • the injected fuel 24 is sandwiched between an air flow 26 from a slot 12 and air flow 28 from another slot 12 .
  • the injected fuel 24 co-flows with the air flows 26 , 28 and is prevented from contacting the interior wall 30 of the burner tube 4 . This will eliminate jet cross flow, which tends to cause flame holding.
  • the tangentially entered fuel and air co-flow layers then flow down axially with quick mixing and dump to the combustor for a stable premixed combustion.
  • the fuel and air co-flows 24 , 26 , 28 radially enter the burner tube 4 .
  • the radial entry of the co-flows 24 , 26 , 28 generates no wake domain inside the burner tube 4 and eliminates any potential flame holding spots.
  • the radial fuel and air co-flows 24 , 26 , 28 also provide axial vortex breaking to ensure good fuel and air mixing.
  • the slot ends 22 are configured to allow the air flows 26 , 28 to enter the burner tube 4 tangentially to the burner tube axis 34 and radially.
  • the central body 18 prevents flame flashback at the center of the burner tube 4 and stabilizes the flame near the central body tip 32 .
  • the burner 2 has simple geometry and may be manufactured at low cost.
  • the burner 2 also provides high efficiency and low emission.
  • the interior wall 30 of the burner tube 4 may also be protected by pure air or an air purge.
  • the burner 2 also provides low air and fuel pressure drop and the gradual axial fuel injection avoids dynamics.
  • the burner 2 may also be used with high hydrogen fuel and syngas.
  • the length and width of the slots 12 , the number of fuel injection holes 16 , the diameter of the fuel injection holes 16 , the locations of the fuel injection holes 16 , and the surface profile of the central body 18 may be designed using Computational Fluid Dynamics (CFD) to provide desired, or enhanced, air/fuel mixing and to avoid autoignition and flame holding in the burner. It should also be appreciated that although the burner has been shown as including, for example, four slots, that any plural number of slots may be provided.
  • CFD Computational Fluid Dynamics

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US12/099,241 2008-04-08 2008-04-08 Burner tube premixer and method for mixing air and gas in a gas turbine engine Abandoned US20090249789A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US12/099,241 US20090249789A1 (en) 2008-04-08 2008-04-08 Burner tube premixer and method for mixing air and gas in a gas turbine engine
JP2009024707A JP2009250604A (ja) 2008-04-08 2009-02-05 ガスタービンエンジン内で空気及びガスを混合するためのバーナ管予混合器及び方法
FR0950762A FR2929688A1 (fr) 2008-04-08 2009-02-06 Premelangeur de tube de bruleur et procede pour melanger de l'air et du gaz dans une turbine a gas.
DE102009003453A DE102009003453A1 (de) 2008-04-08 2009-02-06 Brennrohr-Vormischer und Verfahren zur Gas/Luft-Gemischbildung in einer Gasturbine
CNA2009101307158A CN101556043A (zh) 2008-04-08 2009-02-09 用于在燃气涡轮发动机内混合空气和燃气的燃烧管预混合器和方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/099,241 US20090249789A1 (en) 2008-04-08 2008-04-08 Burner tube premixer and method for mixing air and gas in a gas turbine engine

Publications (1)

Publication Number Publication Date
US20090249789A1 true US20090249789A1 (en) 2009-10-08

Family

ID=41060748

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/099,241 Abandoned US20090249789A1 (en) 2008-04-08 2008-04-08 Burner tube premixer and method for mixing air and gas in a gas turbine engine

Country Status (5)

Country Link
US (1) US20090249789A1 (fr)
JP (1) JP2009250604A (fr)
CN (1) CN101556043A (fr)
DE (1) DE102009003453A1 (fr)
FR (1) FR2929688A1 (fr)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100175381A1 (en) * 2007-04-23 2010-07-15 Nigel Wilbraham Swirler
US20100180600A1 (en) * 2009-01-22 2010-07-22 General Electric Company Nozzle for a turbomachine
US20100186413A1 (en) * 2009-01-23 2010-07-29 General Electric Company Bundled multi-tube nozzle for a turbomachine
US20100192581A1 (en) * 2009-02-04 2010-08-05 General Electricity Company Premixed direct injection nozzle
CN102628593A (zh) * 2011-02-03 2012-08-08 通用电气公司 用于在燃气轮机中混合燃料的装置
EP2808611A1 (fr) * 2013-05-31 2014-12-03 Siemens Aktiengesellschaft Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
US8959921B2 (en) 2010-07-13 2015-02-24 General Electric Company Flame tolerant secondary fuel nozzle
US20150198095A1 (en) * 2014-01-15 2015-07-16 Delavan Inc. Offset stem fuel distributor
CN105318328A (zh) * 2015-01-15 2016-02-10 上海凌云瑞升燃烧设备有限公司 内循环多火焰低nox燃气燃烧器
US9267690B2 (en) 2012-05-29 2016-02-23 General Electric Company Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same
US20160290652A1 (en) * 2013-11-12 2016-10-06 Hanwha Techwin Co., Ltd. Swirler assembly
EP2719952A3 (fr) * 2012-10-09 2017-12-20 General Electric Company Buse de carburant et son procédé d'assemblage
US11015808B2 (en) 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions
US20230130173A1 (en) * 2020-07-17 2023-04-27 Siemens Energy Global GmbH & Co. KG Premixer injector assembly in gas turbine engine
EP4411243A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Injecteur avec carénage et passage annulaire pour moteur à turbine à gaz entraîné par hydrogène
EP4411228A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Injecteur avec conduits d'alimentation tangentiels pour moteur à turbine à gaz à hydrogène
EP4411240A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Dispositif de tourbillonnement d'air combiné et distributeur de carburant

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110173983A1 (en) * 2010-01-15 2011-07-21 General Electric Company Premix fuel nozzle internal flow path enhancement
FR2955375B1 (fr) * 2010-01-18 2012-06-15 Turbomeca Dispositif d'injection et chambre de combustion de turbomachine equipee d'un tel dispositif d'injection
US8590311B2 (en) * 2010-04-28 2013-11-26 General Electric Company Pocketed air and fuel mixing tube
US20120058437A1 (en) * 2010-09-08 2012-03-08 General Electric Company Apparatus and method for mixing fuel in a gas turbine nozzle
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
CN107631323B (zh) * 2017-09-05 2019-12-06 中国联合重型燃气轮机技术有限公司 燃气轮机的喷嘴
CN109237472B (zh) * 2018-06-26 2024-05-17 天时燃烧设备（苏州）有限责任公司 燃烧管组件和燃烧器
KR102607177B1 (ko) * 2022-01-28 2023-11-29 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스터빈

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US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5259184A (en) * 1992-03-30 1993-11-09 General Electric Company Dry low NOx single stage dual mode combustor construction for a gas turbine
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US6216466B1 (en) * 1997-04-10 2001-04-17 European Gas Turbines Limited Fuel-injection arrangement for a gas turbine combustor
US6301899B1 (en) * 1997-03-17 2001-10-16 General Electric Company Mixer having intervane fuel injection
US6438961B2 (en) * 1998-02-10 2002-08-27 General Electric Company Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion
US6684640B2 (en) * 2000-10-23 2004-02-03 Alstom Power N.V. Gas turbine engine combustion system
US6993916B2 (en) * 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
US20090272117A1 (en) * 2006-06-12 2009-11-05 Nigel Wilbraham Burner

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CH680467A5 (fr) * 1989-12-22 1992-08-31 Asea Brown Boveri
SE9304194L (sv) * 1993-12-17 1995-06-18 Abb Stal Ab Bränslespridare
US5671597A (en) * 1994-12-22 1997-09-30 United Technologies Corporation Low nox fuel nozzle assembly
DE59809222D1 (de) * 1998-09-16 2003-09-11 Abb Research Ltd Brenner für einen Wärmeerzeuger
JP3959632B2 (ja) * 2002-09-04 2007-08-15 石川島播磨重工業株式会社 拡散燃焼方式低ＮＯｘ燃焼器
US7065972B2 (en) * 2004-05-21 2006-06-27 Honeywell International, Inc. Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions
DE102005015152A1 (de) * 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer
FR2896031B1 (fr) * 2006-01-09 2008-04-18 Snecma Sa Dispositif d'injection multimode pour chambre de combustion, notamment d'un turboreacteur

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259184A (en) * 1992-03-30 1993-11-09 General Electric Company Dry low NOx single stage dual mode combustor construction for a gas turbine
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US6301899B1 (en) * 1997-03-17 2001-10-16 General Electric Company Mixer having intervane fuel injection
US6216466B1 (en) * 1997-04-10 2001-04-17 European Gas Turbines Limited Fuel-injection arrangement for a gas turbine combustor
US6438961B2 (en) * 1998-02-10 2002-08-27 General Electric Company Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion
US6684640B2 (en) * 2000-10-23 2004-02-03 Alstom Power N.V. Gas turbine engine combustion system
US6993916B2 (en) * 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
US20090272117A1 (en) * 2006-06-12 2009-11-05 Nigel Wilbraham Burner

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100175381A1 (en) * 2007-04-23 2010-07-15 Nigel Wilbraham Swirler
US20100180600A1 (en) * 2009-01-22 2010-07-22 General Electric Company Nozzle for a turbomachine
US8297059B2 (en) 2009-01-22 2012-10-30 General Electric Company Nozzle for a turbomachine
US9140454B2 (en) 2009-01-23 2015-09-22 General Electric Company Bundled multi-tube nozzle for a turbomachine
US20100186413A1 (en) * 2009-01-23 2010-07-29 General Electric Company Bundled multi-tube nozzle for a turbomachine
US20100192581A1 (en) * 2009-02-04 2010-08-05 General Electricity Company Premixed direct injection nozzle
US8539773B2 (en) 2009-02-04 2013-09-24 General Electric Company Premixed direct injection nozzle for highly reactive fuels
US8959921B2 (en) 2010-07-13 2015-02-24 General Electric Company Flame tolerant secondary fuel nozzle
CN102628593A (zh) * 2011-02-03 2012-08-08 通用电气公司 用于在燃气轮机中混合燃料的装置
US11421885B2 (en) 2011-12-13 2022-08-23 General Electric Company System for aerodynamically enhanced premixer for reduced emissions
US11421884B2 (en) 2011-12-13 2022-08-23 General Electric Company System for aerodynamically enhanced premixer for reduced emissions
US11015808B2 (en) 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions
US9267690B2 (en) 2012-05-29 2016-02-23 General Electric Company Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same
EP2719952A3 (fr) * 2012-10-09 2017-12-20 General Electric Company Buse de carburant et son procédé d'assemblage
EP2808611A1 (fr) * 2013-05-31 2014-12-03 Siemens Aktiengesellschaft Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
US20160290652A1 (en) * 2013-11-12 2016-10-06 Hanwha Techwin Co., Ltd. Swirler assembly
US9689571B2 (en) * 2014-01-15 2017-06-27 Delavan Inc. Offset stem fuel distributor
US20150198095A1 (en) * 2014-01-15 2015-07-16 Delavan Inc. Offset stem fuel distributor
CN105318328A (zh) * 2015-01-15 2016-02-10 上海凌云瑞升燃烧设备有限公司 内循环多火焰低nox燃气燃烧器
US20230130173A1 (en) * 2020-07-17 2023-04-27 Siemens Energy Global GmbH & Co. KG Premixer injector assembly in gas turbine engine
US11708974B2 (en) * 2020-07-17 2023-07-25 Siemens Energy Global GmbH & Co. KG Premixer injector assembly in gas turbine engine
EP4411243A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Injecteur avec carénage et passage annulaire pour moteur à turbine à gaz entraîné par hydrogène
EP4411228A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Injecteur avec conduits d'alimentation tangentiels pour moteur à turbine à gaz à hydrogène
EP4411240A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Dispositif de tourbillonnement d'air combiné et distributeur de carburant

Also Published As

Publication number Publication date
CN101556043A (zh) 2009-10-14
FR2929688A1 (fr) 2009-10-09
DE102009003453A1 (de) 2009-10-15
JP2009250604A (ja) 2009-10-29

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ZUO, BAIFANG;KHAN, ABDUL RAFEY;STEVENSON, CHRISTIAN X.;REEL/FRAME:020769/0813

Effective date: 20080404

AS Assignment

Owner name: ENERGY, UNITED STATES DEPARTMENT OF, DISTRICT OF C

Free format text: CONFIRMATORY LICENSE;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:021012/0834

Effective date: 20080512

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION