EP2503240A1 - Gasturbinenbrenner - Google Patents

Gasturbinenbrenner Download PDF

Info

Publication number
EP2503240A1
EP2503240A1 EP11159121A EP11159121A EP2503240A1 EP 2503240 A1 EP2503240 A1 EP 2503240A1 EP 11159121 A EP11159121 A EP 11159121A EP 11159121 A EP11159121 A EP 11159121A EP 2503240 A1 EP2503240 A1 EP 2503240A1
Authority
EP
European Patent Office
Prior art keywords
channel
gas
fuel
exit
inner cavity
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Withdrawn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
EP11159121A
Other languages
English (en)
French (fr)
Inventor
Andreas Karlsson
Vladimir Milosavljevic
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP11159121A priority Critical patent/EP2503240A1/de
Publication of EP2503240A1 publication Critical patent/EP2503240A1/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Withdrawn legal-status Critical Current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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • the present invention refers to a gas turbine burner comprising:
  • Gas turbine engines comprising a gas turbine burner of the incipiently mentioned type are employed in a variety of applications, for example stationary power generation, military automotive application, marine application and as industrial drives to name only some examples.
  • Some major fields of development deal with respectively the decreasing of fuel consumption, lowering emissions - especially NOx (nitrogen oxides) or reducing noise, improving fuel flexibility, lengthening lifetime of the components of the gas turbine and increasing reliability and availability of the gas turbine and its components.
  • NOx nitrogen oxides
  • Most of the above objectives are depending on one to another and reveal to be contradictive.
  • the efficiency may be increased by an increase of the operating temperature, which on the other hand has the effect that NOx emissions are increased and the expected lifetime of the hot gas components is reduced.
  • One objective of the invention is the reduction of emissions without lowering the efficiency.
  • a further objective is the increase of stability without increasing fuel consumption.
  • Still a further objective of the invention is to increase fuel flexibility with regard to the amount of fuel consumed by the burner.
  • the main combustion room is an enclosure confined by main combustion room walls comprising means for supply of oxygen containing gas and fuel.
  • the oxygen containing gas can be air and can be premixed with the fuel before entering the main combustion room and burning in the main combustion zone contained by the main combustion room.
  • the main combustion room comprises an exhaust for ejecting the hot combustion gas preferably in a downstream located turbine for conversion of the kinetic energy contained in the hot combustion gas into the motion of a turbine rotor.
  • the main combustion room can comprise a recirculation zone, by which at least a part of the combustion gas generated in the main combustion zone is recirculated with a fresh mixture of fuel and oxygen containing gas to generate further hot combustion gas to be processed in the downstream turbine.
  • the gas channel according to the invention needs not to be the only fuel and oxygen containing gas supply to the main combustion zone but preferably is only one of several possible fuel and gas supplies.
  • the fuel injection element according to the invention is basically a protrusion from the confining channel wall and can be of any shape.
  • An essential feature of said fuel injection element is that at least two nozzles respectively two sets of nozzles are supplied with fuel to be injected into the fuel gas channel from two different and separate cavities.
  • Each one of said cavities supplies fuel - preferably a gaseous fuel to a specific set of nozzles.
  • the specific geometry and location of the nozzles and the geometric specifications of the channel as well as the aerodynamic parameters of the flow of said oxygen containing gas may be the input for a computational fluid dynamic analysis leading a person with ordinary skill in the art to the specific geometric design based on the idea of the invention.
  • the first inner cavity may advantageously be connected to a buffer room by a first fuel channel and the second inner cavity may advantageously be connected to said buffer room by a second fuel channel, wherein the first fuel channel is provided with a first throttle and the second fuel channel is provided with a second throttle to imprint a certain pressure drop on the flow through said first and second fuel channel respectively.
  • Said respective throttles provided in said fuel channels conducting fuel to the inner cavities maybe of fixed cross sectional area size and chosen according to a specific operation point intended for the gas turbine burner. To obtain a higher degree of flexibility these throttles maybe adjustable.
  • One preferred embodiment is a manually adjustable throttle. To adjust the throttle during operation to specific conditions the throttles maybe provided as automatic valves controlled by a specific control unit.
  • the cross section area of the opening of the throttle is chosen or adjusted such that an exit area of the respective throttle is at least three times bigger than the sum of the exit areas of the nozzles in which the respective connected inner cavity joins into.
  • said control unit can be made to fulfill this design rule, too.
  • the exit area of the throttle is hereby defined as the smallest cross sectional area with regard to the flow direction through the throttle. Referring to the sum of the exit areas of the nozzles, this parameter can be determined as the sum of the respective smallest cross section with regard to the flow through the set of nozzles assigned to a specific inner cavity. Said proportion of the exit areas leads to a sufficient pressure drop during the ejection of the fuel into said gas channel, which leads to better predictability of fuel pressures in the inner cavities respectively.
  • Another preferred embodiment may be provided with a reduction of the cross sectional area of the gas channel in downstream direction upstream of the fuel injection element. This way the gas is accelerated before the fuel is injected into the gas flow, leading to a better mixing.
  • the gas channel may be provided with swirler wings to imprint a certain velocity distribution on the gas flow through the gas channel improving the mixing of fuel and said oxygen containing gas further.
  • Said velocity distribution should comprise a swirl, preferably a circumferential velocity component with regard to a central axis. Further beneficial the imprinted velocity distribution might positively affect the mixing in the main combustion zone.
  • a further preferred embodiment provides the fuel injection elements as swirler wings itself to improve the mixing in the gas channel and in said main combustion zone downstream.
  • a still further preferred embodiment may provide the gas channel or gas channels as channels of annular cross section surrounding a pilot burner coaxially, which pilot burner may comprise a pilot combustion room, which is discharging a pilot combustion gas generated in the pilot combustion room through a constricted pilot exit throat into said main combustion room, wherein the pilot exit throat is coaxially surrounded by the annular shaped gas channel exit.
  • the hot combustion gas from the pilot combustion room mixing with the fuel and oxygen containing gas from the surrounding gas channel exit stabilizes the combustion in the main combustion room.
  • the gas channel may advantageously be connected to an oxygen containing gas collector by a perforated channel wall, which perforation is made such that jets of oxygen containing gas hit the surrounded pilot burner for the purpose of heat exchange.
  • a perforated channel wall which perforation is made such that jets of oxygen containing gas hit the surrounded pilot burner for the purpose of heat exchange.
  • Figure 1 shows a gas turbine burner GTB comprising a main combustion room MCR containing a main combustion zone MCZ enclosed by main combustion room walls MCRW.
  • the main combustion room MCR is supplied with a mixture of fuel F and air AE through a main supply MS.
  • an exhaust EX is provided, through which exhaust combustion gas ECG is discharged.
  • a forward stagnation point SP located on a central axis AX indicates the location, where recirculated combustion gas CG is axially decelerated to an axial velocity of 0.
  • a pilot burner PB is part of the gas turbine burner GTB and generates a mixture of fuel F and free radicals supplied as a hot gas meeting the recirculated combustion gas CG at the forward stagnation point SP.
  • Said pilot burner PB comprises a pilot combustion room PCR containing a pilot combustion zone PCZ, generating heat and free radicals, which are discharged through a constricted pilot exit throat PET into the main combustion room MCR.
  • a flame front FF starts at the forward stagnation point SP, where the recirculated combustion gas CG meets the heat an free radicals HERA generated by said pilot burner PB.
  • the pilot burner PB is surrounded coaxially by a gas channel GC of annular cross section, discharging an air fuel mixture AFM into the main combustion room MCR through an annular gas channel exit GCE arranged coaxially around the pilot exit throat PET.
  • said flame front FF progresses from the forward stagnation point SP along the gas channel exit GCE and along the main supply exits MSE, which are also arranged coaxially to the pilot exit throat PET.
  • the main supply MS comprises several annular shaped exits MSE divided from each other by partition plates PP.
  • the flame front FF establishes from the forward stagnation point SP extending along the gas channel exit GCE and the exit of the main supply MSE due to the increased oxygen concentration in these areas discharging into the main combustion zone MCZ.
  • the gas channel GC surrounding the pilot burner PB is supplied with an oxygen containing gas OCG, collected in an oxygen containing gas collector OCGC,which is preferably air AE through a perforation PF of channel walls CW confining said gas channel GC.
  • Said perforation PF of the channel wall CW is designed such that the oxygen containing gas OCG hits the surrounded pilot burner for the purpose of heat exchange. This way the oxygen containing gas OCG is preheated and the pilot burner wall is cooled accordingly.
  • Downstream said perforation PF the oxygen containing gas OCG enters a part of the gas channel GC, which is reduced with regard to the cross section area CA leading to an acceleration of the oxygen containing gas OCG.
  • Fuel injection elements FIE are provided as swirler wings SW injecting fuel into the accelerated flow of oxygen containing gas OCG and giving this flow a swirl before discharging into the main combustion zone MCZ.
  • the fuel injection elements FIE comprise inner cavities IC, respectively a first inner cavity IC1 and a second inner cavity IC2 for each fuel injection element FIE respectively swirler wing SW.
  • the inner cavities IC are respectively supplied with fuel F from a buffer room BR through a first fuel channel FC1 respectively a second fuel channel FC2.
  • the inner cavities IC join into nozzles NO with nozzle openings NO1 respectively NO2.
  • NO2 fuel F is discharged into the gas channel GCto mix with the oxygen containing gas OCG which is simultaneously provided with a swirl from the swirler wings SW.
  • the first fuel channel FC1 is provided with a first throttle TH1, through which a pressure drop from the buffer room BR to the first inner cavity IC1 is imprinted on the fuel flow.
  • a second throttle TH2 is provided in the second fuel channel FC2 for an according purpose.
  • An exit area EATH1 of the first throttle is at least three times bigger than the sum of the exit areas of saidfirst nozzles NO1.
  • the according relation is established between an exit area EAFC2 of the second throttle TH2 with regard the sum of the exit areas of the second nozzle NO2 respectively set of second nozzles N02.
  • the throttles TH1, TH2 can be provided as adjustable throttles or throttles of fixed size. Further the throttles TH1, TH2 can be manually adjustable or automatically adjustable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP11159121A 2011-03-22 2011-03-22 Gasturbinenbrenner Withdrawn EP2503240A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11159121A EP2503240A1 (de) 2011-03-22 2011-03-22 Gasturbinenbrenner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11159121A EP2503240A1 (de) 2011-03-22 2011-03-22 Gasturbinenbrenner

Publications (1)

Publication Number Publication Date
EP2503240A1 true EP2503240A1 (de) 2012-09-26

Family

ID=44763759

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11159121A Withdrawn EP2503240A1 (de) 2011-03-22 2011-03-22 Gasturbinenbrenner

Country Status (1)

Country Link
EP (1) EP2503240A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015067482A1 (en) * 2013-11-08 2015-05-14 Siemens Aktiengesellschaft Gas turbine burner having separately controllable fuel stages in pilot burner swirl vanes
WO2015165680A1 (en) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Burner with adjustable radial fuel profile
RU2669439C1 (ru) * 2015-04-08 2018-10-11 Сименс Акциенгезелльшафт Система горелок

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5351477A (en) * 1993-12-21 1994-10-04 General Electric Company Dual fuel mixer for gas turbine combustor
DE19839085A1 (de) * 1998-08-27 2000-03-02 Siemens Ag Brenneranordnung mit primärem und sekundärem Pilotbrenner
EP2107310A1 (de) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Brenner
US20100319353A1 (en) * 2009-06-18 2010-12-23 John Charles Intile Multiple Fuel Circuits for Syngas/NG DLN in a Premixed Nozzle

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5351477A (en) * 1993-12-21 1994-10-04 General Electric Company Dual fuel mixer for gas turbine combustor
DE19839085A1 (de) * 1998-08-27 2000-03-02 Siemens Ag Brenneranordnung mit primärem und sekundärem Pilotbrenner
EP2107310A1 (de) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Brenner
US20100319353A1 (en) * 2009-06-18 2010-12-23 John Charles Intile Multiple Fuel Circuits for Syngas/NG DLN in a Premixed Nozzle

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015067482A1 (en) * 2013-11-08 2015-05-14 Siemens Aktiengesellschaft Gas turbine burner having separately controllable fuel stages in pilot burner swirl vanes
WO2015165680A1 (en) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Burner with adjustable radial fuel profile
RU2669439C1 (ru) * 2015-04-08 2018-10-11 Сименс Акциенгезелльшафт Система горелок

Similar Documents

Publication Publication Date Title
CN102032598B (zh) 一种带多旋流中间稳焰级的周向分级低污染燃烧室
CN101375101B (zh) 燃气涡轮发动机燃烧器以及燃气涡轮发动机燃烧器漩流区域内混合燃料和空气的方法
US9599343B2 (en) Fuel nozzle for use in a turbine engine and method of assembly
CN100554785C (zh) 用于对燃气轮机中的空气和气体进行混合的燃烧管及方法
JP6937573B2 (ja) ガスタービンの燃焼システムにおける段階的な燃料および空気噴射
EP2436979A1 (de) Brenner für eine Gasturbine
CN101349425B (zh) 用于冷却低NOx燃烧器中的燃烧室/文丘里管的装置/方法
US9261279B2 (en) Liquid cartridge with passively fueled premixed air blast circuit for gas operation
JP2002031343A (ja) 燃料噴出部材、バーナ、燃焼器の予混合ノズル、燃焼器、ガスタービン及びジェットエンジン
CN104534515B (zh) 燃气轮机燃烧室头部结构
US20150040576A1 (en) Counter swirl doublet combustor
CN104373962A (zh) 一种燃气轮机燃烧室叶片进气旋流喷嘴
CN105588144B (zh) 用于燃气轮机燃烧室的火焰稳燃装置及火焰稳燃方法
KR20160030051A (ko) 가스 터빈의 연소기를 위한 희석 가스 또는 공기 혼합기
JP2017116250A (ja) ガスタービンにおける燃料噴射器および段階的燃料噴射システム
CN104566476B (zh) 燃气轮机燃烧室头部结构及其燃烧组织方法
EP2503240A1 (de) Gasturbinenbrenner
EP2743588A1 (de) Ausgesparte Kraftstoffeinspritzerpositionierung
US9677766B2 (en) Fuel nozzle for use in a turbine engine and method of assembly
CN111288490A (zh) 一种分散凸台处高温回流区的燃烧室装置
EP3224544A1 (de) Brennstofflanze mit mittel zur interaktion mit einem luftstrom und zur verbesserung des bruches eines ausgestossenen strahles aus flüssigem brennstoff
CN212057380U (zh) 一种分散凸台处高温回流区的燃烧室装置
EP2503241A1 (de) Gasturbinenbrenner
CN104534513B (zh) 燃气轮机燃烧室旋射流混合喷嘴
EP2503244A1 (de) Gasturbinenbrenner

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: A1

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

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

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: 20130327