EP2592349A2 - Brennkammer und Verfahren zur Versorgung einer Brennkammer mit Brennstoff - Google Patents

Brennkammer und Verfahren zur Versorgung einer Brennkammer mit Brennstoff Download PDF

Info

Publication number
EP2592349A2
EP2592349A2 EP12192137.3A EP12192137A EP2592349A2 EP 2592349 A2 EP2592349 A2 EP 2592349A2 EP 12192137 A EP12192137 A EP 12192137A EP 2592349 A2 EP2592349 A2 EP 2592349A2
Authority
EP
European Patent Office
Prior art keywords
fuel
tube bundle
combustor
end cap
fluid communication
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Withdrawn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
EP12192137.3A
Other languages
English (en)
French (fr)
Inventor
Patrick Benedict Melton
lll James Harold Westmoreland
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
Publication of EP2592349A2 publication Critical patent/EP2592349A2/de
Withdrawn legal-status Critical Current

Links

Images

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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses

Definitions

  • the present invention generally involves a combustor and method for supplying fuel to a combustor.
  • Combustors are commonly used in industrial and power generation operations to ignite fuel to produce combustion gases having a high temperature and pressure.
  • gas turbines typically include one or more combustors to generate power or thrust.
  • a typical gas turbine used to generate electrical power includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear.
  • Ambient air may be supplied to the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state.
  • the compressed working fluid exits the compressor and flows through one or more nozzles into a combustion chamber in each combustor where the compressed working fluid mixes with fuel and ignites to generate combustion gases having a high temperature and pressure.
  • the combustion gases expand in the turbine to produce work. For example, expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce electricity.
  • combustion gas temperatures generally improve the thermodynamic efficiency of the combustor.
  • higher combustion gas temperatures also promote flashback or flame holding conditions in which the combustion flame migrates towards the fuel being supplied by the nozzles, possibly causing severe damage to the nozzles in a relatively short amount of time.
  • localized hot streaks in the combustion chamber may increase the disassociation rate of diatomic nitrogen, increasing the production of nitrogen oxides (NO X ) at higher combustion gas temperatures.
  • lower combustion gas temperatures associated with reduced fuel flow and/or part load operation (turndown) generally reduce the chemical reaction rates of the combustion gases, increasing the production of carbon monoxide and unburned hydrocarbons.
  • a plurality of tubes may be radially arranged in an end cap to provide fluid communication for the working fluid and fuel flowing through the end cap and into the combustion chamber.
  • the tubes enhance mixing between the working fluid and fuel to reduce hot streaks that can be problematic with higher combustion gas temperatures.
  • the tubes are effective at preventing flashback or flame holding and/or reducing NO X production, particularly at higher operating levels.
  • an improved combustor and method for supplying fuel to the tubes that allows for staged fueling and/or operation of the tubes at varying operational levels with both liquid and gaseous fuels would be useful.
  • One aspect of the present invention is a combustor that includes an end cap that extends radially across at least a portion of the combustor, wherein the end cap comprises an upstream surface axially separated from a downstream surface.
  • a casing circumferentially surrounds at least a portion of the end cap to define an annular passage between the end cap and the casing.
  • a first tube bundle extends from the upstream surface through the downstream surface to provide fluid communication through the end cap.
  • a first fuel conduit is in fluid communication with the first tube bundle to supply fuel through the annular passage to the first tube bundle, and a liquid fuel supply is in fluid communication with the first tube bundle through the first fuel conduit.
  • a combustor that includes an end cap that extends radially across at least a portion of the combustor, wherein the end cap comprises an upstream surface axially separated from a downstream surface.
  • a casing circumferentially surrounds at least a portion of the end cap to define an annular passage between the end cap and the casing.
  • a plurality of tubes extend from the upstream surface through the downstream surface to provide fluid communication through the end cap.
  • a barrier extends axially through the end cap to separate the plurality of tubes into a first tube bundle and a second tube bundle.
  • a first fuel conduit is in fluid communication with the first tube bundle to supply fuel through the annular passage to the first tube bundle, and a liquid fuel supply is in fluid communication with the first tube bundle through the first fuel conduit.
  • the present invention also includes a method for supplying fuel to a combustor that includes flowing a working fluid through a first tube bundle that extends axially through an end cap that extends radially across at least a portion of the combustor. The method further includes flowing a liquid fuel through an annular passage surrounding the end cap and into the first tube bundle.
  • Various embodiments of the present invention provide a combustor and method for supplying fuel to a combustor.
  • a plurality of tubes may be arranged in an end cap to provide fluid communication for a working fluid to flow through the end cap and into a combustion chamber.
  • a liquid fuel may be supplied through an annular passage that surrounds the end cap and sprayed or injected into one or more tubes.
  • the tubes may be grouped into multiple tube bundles that enable the combustor to be operated using liquid and/or gaseous fuels over a wide range of operating conditions without exceeding design margins associated with flashback, flame holding, and/or emissions limits.
  • Fig. 1 shows a simplified cross-section view of an exemplary combustor 10 according to one embodiment of the present invention
  • Fig. 2 provides a downstream axial view of the combustor 10 shown in Fig. 1
  • a casing 12 and an end cover 14 generally surround the combustor 10 to contain a working fluid 16 flowing to the combustor 10.
  • An end cap 18 may extend radially across at least a portion of the combustor 10, and the casing 12 may circumferentially surround at least a portion of the end cap 18 to define an annular passage 20 between the end cap 18 and the casing 12.
  • the end cap 18 and a liner 22 may define at least a portion of a combustion chamber 24 downstream from the end cap 18.
  • the working fluid 16 may flow through the annular passage 20 along the outside of the liner 22 to provide convective cooling to the liner 22.
  • the working fluid 16 may reverse direction to flow through the end cap 18 and into the combustion chamber 24.
  • the end cap 18 may include an upstream surface 26 axially separated from a downstream surface 28, and a plurality of tubes 30 may extend axially from the upstream surface 26 to the downstream surface 28 to provide fluid communication through the end cap 18.
  • the particular shape, size, number, and arrangement of the tubes 30 may vary according to particular embodiments.
  • the tubes 30 are generally illustrated as having a cylindrical shape; however, alternate embodiments within the scope of the present invention may include tubes having virtually any geometric cross-section.
  • the tubes 30 may be radially arranged across the end cap 18 in one or more tube bundles of various shapes and sizes, with each tube bundle having one or more separate fuel supplies.
  • multiple tubes 30 may be radially arranged around a single tube bundle, or multiple tube bundles may be radially arranged across the end cap 18.
  • One or more fuel conduits may provide one or more fuels to each tube bundle, and the type, fuel content, and reactivity of the fuel may vary for each fuel conduit or tube bundle. In this manner, different fuels, different fuel types, and/or different fuel flow rates may be supplied to one or more tube bundles to allow for staged fueling of the tubes 30 over a wide range of operating conditions.
  • a cap shield 32 may circumferentially surround the upstream and downstream surfaces 26, 28 to define a fuel plenum inside the end cap 18.
  • a barrier 34 may extend generally axially through the end cap 18 to separate the fuel plenum and tubes into first and second fuel plenums 36, 38 and first and second tube bundles 40, 42.
  • First and second fuel conduits 44, 46 may extend radially through the casing 12 to supply fuel through the annular passage 20 to the first and second tube bundles 40, 42, respectively.
  • a liquid fuel supply 48 outside of the combustor 10 may supply liquid fuel to the first fuel conduit 44.
  • the first fuel conduit 44 may include a radially extending fuel line 50 for each tube 30 in the first tube bundle 40.
  • Each radially extending fuel line 50 may terminate at a fuel port 52 upstream from each tube 30 in the first tube bundle 40, and each fuel port 52 may be aligned with an axial centerline of each tube 30 in the first tube bundle 40.
  • the first fuel conduit 44 may provide fluid communication between the liquid fuel supply 48 and the first tube bundle 40, and the fuel ports 52 may spray the liquid fuel into each tube 30 in the first tube bundle 40 to atomize and mix the liquid fuel with the working fluid flowing through the tubes 30.
  • the second fuel conduit 46 may similarly provide fluid communication between another fuel supply (not shown) and the second tube bundle 42. Specifically, the second fuel conduit 46 may extend radially through the casing 12, annular passage 20, and cap shield 32 to supply fuel to the second fuel plenum 38.
  • One or more of the tubes 30 in the second tube bundle 42 may include a fuel passage 54 that provides fluid communication through the tube 30 from the second fuel plenum 38.
  • the fuel passages 54 may be angled radially, axially, and/or azimuthally to project and/or impart swirl to the fuel flowing through the fuel passages 54 and into the tubes 30.
  • the fuel from the second fuel conduit 46 may flow around the tubes 30 in the second tube bundle 42 to provide convective cooling to the second tube bundle 42 before flowing through the fuel passages 54 and mixing with the working fluid.
  • the fuel-working fluid mixture from the second tube bundle 42 may then flow into the combustion chamber 24.
  • the combustor 10 may further include a third fuel conduit in fluid communication with one or more tube bundles.
  • a third fuel conduit 56 may supply fuel through the annular passage 20 to the first tube bundle 40.
  • One or more of the tubes 30 in the first tube bundle 40 may include a fuel passage 54 that provides fluid communication through the tube 30 from the first fuel plenum 36 as previously described. In this manner, the fuel from the third fuel conduit 56 may flow around the tubes 30 in the first tube bundle 40 to provide convective cooling to the first tube bundle 40 before flowing through the fuel passages 54 and mixing with the working fluid. The fuel-working fluid mixture from the first tube bundle 40 may then flow into the combustion chamber 24.
  • At least one of an airfoil 58 or vane may surround at least a portion of the first, second, and/or third fuel conduits 44, 46, 56 in the annular passage 20 to reduce flow resistance of the working fluid flowing across the fuel conduits 44, 46, 56 in the annular passage 20.
  • the airfoil 58 or vane may be angled to impart swirl to the working fluid flowing through the annular passage 20.
  • the end cap 18 may further include one or more expansion joints or bellows between the upstream and downstream surfaces 26, 28 to allow for thermal expansion of the tubes 30 between the upstream and downstream surfaces 26, 28.
  • an expansion joint 60 in the cap shield 32 and/or barrier 34 may allow for axial displacement of the upstream and downstream surfaces 26, 28 as the first and second tube bundles 40, 42 expand and contract.
  • Fig. 3 shows a simplified cross-section view of an alternate embodiment of the present invention
  • Fig. 4 provides a downstream axial view of the combustor 10 shown in Fig. 3
  • the combustor 10 again includes a casing 12, end cover 14, end cap 18, annular passage 20, liner 22, combustion chamber 24, first and second tube bundles 40, 42, and various fuel conduits 44, 46, 58 as previously described with respect to the embodiment shown in Figs. 1 and 2 .
  • the combustor 10 includes a fourth fuel conduit 62 that extends axially through the end cover 14 to provide fluid communication through the upstream surface 26 of the end cap 18.
  • a shroud 64 may circumferentially surround the fourth fuel conduit 62, and one or more swirler vanes 66 may extend radially between the shroud 64 and the fourth fuel conduit 62.
  • the fourth fuel conduit 62 may supply additional fuel through the upstream surface 26 to mix with working fluid 16 flowing though the shroud 64, and the swirler vanes 66 may impart swirl to the fuel-working fluid mixture prior to entering the combustion chamber 24.
  • the method may include flowing the working fluid 16 through the first tube bundle 40 and flowing the liquid fuel through the annular passage 20 surrounding the end cap 18 and into the first tube bundle 40.
  • the method may include spraying the liquid fuel into the axial center of each tube 30 in the first tube bundle 40 and/or supplying the same or different fuel through other fuel conduits 46, 56 to the first and/or second tube bundles 40, 42.
  • the method may include flowing the same or different fuel axially through yet another fuel conduit 62 and shroud 64 that provides fluid communication through the end cap 18 and into the combustion chamber 24.
  • Each embodiment thus provides very flexible methods for providing staged fueling to various locations across the combustor 10 to enable the combustor 10 to operate over a wide range of operating conditions without exceeding design margins associated with flashback, flame holding, and/or emissions limits.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP12192137.3A 2011-11-11 2012-11-09 Brennkammer und Verfahren zur Versorgung einer Brennkammer mit Brennstoff Withdrawn EP2592349A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/294,284 US20130122437A1 (en) 2011-11-11 2011-11-11 Combustor and method for supplying fuel to a combustor

Publications (1)

Publication Number Publication Date
EP2592349A2 true EP2592349A2 (de) 2013-05-15

Family

ID=47226019

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12192137.3A Withdrawn EP2592349A2 (de) 2011-11-11 2012-11-09 Brennkammer und Verfahren zur Versorgung einer Brennkammer mit Brennstoff

Country Status (3)

Country Link
US (1) US20130122437A1 (de)
EP (1) EP2592349A2 (de)
CN (1) CN103104934A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115727354A (zh) * 2022-11-11 2023-03-03 中国航发哈尔滨东安发动机有限公司 一种飞行器用涡扇发动机火焰筒结构

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130122436A1 (en) * 2011-11-11 2013-05-16 General Electric Company Combustor and method for supplying fuel to a combustor
US9677766B2 (en) * 2012-11-28 2017-06-13 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
JP5940227B2 (ja) * 2013-11-05 2016-06-29 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
KR102474179B1 (ko) * 2021-01-15 2022-12-06 두산에너빌리티 주식회사 멀티튜브를 갖는 연소기 및 이를 포함하는 가스터빈

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2565843A (en) * 1949-06-02 1951-08-28 Elliott Co Multiple tubular combustion chamber
US3943705A (en) * 1974-11-15 1976-03-16 Westinghouse Electric Corporation Wide range catalytic combustor
US4052144A (en) * 1976-03-31 1977-10-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fuel combustor
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
US4112676A (en) * 1977-04-05 1978-09-12 Westinghouse Electric Corp. Hybrid combustor with staged injection of pre-mixed fuel
US4262482A (en) * 1977-11-17 1981-04-21 Roffe Gerald A Apparatus for the premixed gas phase combustion of liquid fuels
JPS61195214A (ja) * 1985-02-22 1986-08-29 Hitachi Ltd ガスタ−ビン燃焼器の空気流量調整機構
JPH0663646B2 (ja) * 1985-10-11 1994-08-22 株式会社日立製作所 ガスタ−ビン用燃焼器
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type
US5000004A (en) * 1988-08-16 1991-03-19 Kabushiki Kaisha Toshiba Gas turbine combustor
JP2544470B2 (ja) * 1989-02-03 1996-10-16 株式会社日立製作所 ガスタ―ビン燃焼器及びその運転方法
US5226287A (en) * 1991-07-19 1993-07-13 General Electric Company Compressor stall recovery apparatus
US5235814A (en) * 1991-08-01 1993-08-17 General Electric Company Flashback resistant fuel staged premixed combustor
EP0540167A1 (de) * 1991-09-27 1993-05-05 General Electric Company Gestufte Vormischbrennkammer mit niedrigem NOx-Ausstoss
US5263325A (en) * 1991-12-16 1993-11-23 United Technologies Corporation Low NOx combustion
JPH05203146A (ja) * 1992-01-29 1993-08-10 Hitachi Ltd ガスタービン燃焼器及びガスタービン発電装置
DE19524213A1 (de) * 1995-07-03 1997-01-09 Abb Management Ag Brennstoffzuführung für Gasturbinen mit Ringbrennkammer
US5881756A (en) * 1995-12-22 1999-03-16 Institute Of Gas Technology Process and apparatus for homogeneous mixing of gaseous fluids
US5927076A (en) * 1996-10-22 1999-07-27 Westinghouse Electric Corporation Multiple venturi ultra-low nox combustor
JP2000303856A (ja) * 1999-04-19 2000-10-31 Toshikatsu Maeda ジェツトポンプ式タービン
US6536216B2 (en) * 2000-12-08 2003-03-25 General Electric Company Apparatus for injecting fuel into gas turbine engines
US7003961B2 (en) * 2001-07-23 2006-02-28 Ramgen Power Systems, Inc. Trapped vortex combustor
JP4134311B2 (ja) * 2002-03-08 2008-08-20 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器
US6761033B2 (en) * 2002-07-18 2004-07-13 Hitachi, Ltd. Gas turbine combustor with fuel-air pre-mixer and pre-mixing method for low NOx combustion
JP3940705B2 (ja) * 2003-06-19 2007-07-04 株式会社日立製作所 ガスタービン燃焼器及びその燃料供給方法
US20080078183A1 (en) * 2006-10-03 2008-04-03 General Electric Company Liquid fuel enhancement for natural gas swirl stabilized nozzle and method
US8539773B2 (en) * 2009-02-04 2013-09-24 General Electric Company Premixed direct injection nozzle for highly reactive fuels
US20110072826A1 (en) * 2009-09-25 2011-03-31 General Electric Company Can to can modal decoupling using can-level fuel splits
JP5103454B2 (ja) * 2009-09-30 2012-12-19 株式会社日立製作所 燃焼器
US8800289B2 (en) * 2010-09-08 2014-08-12 General Electric Company Apparatus and method for mixing fuel in a gas turbine nozzle
US8984887B2 (en) * 2011-09-25 2015-03-24 General Electric Company Combustor and method for supplying fuel to a combustor
US8801428B2 (en) * 2011-10-04 2014-08-12 General Electric Company Combustor and method for supplying fuel to a combustor
US8550809B2 (en) * 2011-10-20 2013-10-08 General Electric Company Combustor and method for conditioning flow through a combustor
US9341376B2 (en) * 2012-02-20 2016-05-17 General Electric Company Combustor and method for supplying fuel to a combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115727354A (zh) * 2022-11-11 2023-03-03 中国航发哈尔滨东安发动机有限公司 一种飞行器用涡扇发动机火焰筒结构

Also Published As

Publication number Publication date
CN103104934A (zh) 2013-05-15
US20130122437A1 (en) 2013-05-16

Similar Documents

Publication Publication Date Title
US8801428B2 (en) Combustor and method for supplying fuel to a combustor
US9341376B2 (en) Combustor and method for supplying fuel to a combustor
US8984887B2 (en) Combustor and method for supplying fuel to a combustor
US8904798B2 (en) Combustor
CN106051825B (zh) 包括引导喷嘴的燃料喷嘴组件
EP3171088B1 (de) Gebündelte rohrbrennstoffdüsenanordnung mit flüssigbrennstofffähigkeit
EP2657611B1 (de) System zur Versorgung einer Brennkammer mit Brennstoff
US9151500B2 (en) System for supplying a fuel and a working fluid through a liner to a combustion chamber
US8511086B1 (en) System and method for reducing combustion dynamics in a combustor
US8550809B2 (en) Combustor and method for conditioning flow through a combustor
CN106066048B (zh) 预混引导喷嘴
EP2634488B1 (de) System und Verfahren zur Verringerung der Verbrennungsdynamik in einer Turbomaschine
EP2592345B1 (de) Brennkammer und Verfahren zur Versorgung einer Brennkammer mit Brennstoff
US20130283802A1 (en) Combustor
EP2592349A2 (de) Brennkammer und Verfahren zur Versorgung einer Brennkammer mit Brennstoff
EP2613089B1 (de) Brennkammer und Verfahren zur Brennstoffverteilung in der Brennkammer
US10746101B2 (en) Annular fuel manifold with a deflector

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20150602