EP0269824B1 - Kombinierter Diffusions- und Vormischpilotbrenner - Google Patents

Kombinierter Diffusions- und Vormischpilotbrenner Download PDF

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Publication number
EP0269824B1
EP0269824B1 EP19870115434 EP87115434A EP0269824B1 EP 0269824 B1 EP0269824 B1 EP 0269824B1 EP 19870115434 EP19870115434 EP 19870115434 EP 87115434 A EP87115434 A EP 87115434A EP 0269824 B1 EP0269824 B1 EP 0269824B1
Authority
EP
European Patent Office
Prior art keywords
fuel
premix
diffusion
nozzle
combustor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP19870115434
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English (en)
French (fr)
Other versions
EP0269824A3 (en
EP0269824A2 (de
Inventor
Jennifer Waslo
Masayoshi Kuwata
Roy Marshall Washam
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
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP0269824A2 publication Critical patent/EP0269824A2/de
Publication of EP0269824A3 publication Critical patent/EP0269824A3/en
Application granted granted Critical
Publication of EP0269824B1 publication Critical patent/EP0269824B1/de
Expired legal-status Critical Current

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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D11/00Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/005Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34Feeding into different combustion zones
    • F23R3/346Feeding into different combustion zones for staged combustion

Definitions

  • This invention relates to gas turbine combustors; and, in particular, to improvements in gas turbine combustors for the further diminishment of air pollutants such as nitrogen oxides (NOx).
  • NOx nitrogen oxides
  • the specific configuration of the present invention includes an annular array of primary nozzles each of which discharges into the primary combustion chamber and a combined diffusion and premix nozzle which discharges into the second combustion chamber.
  • These nozzles may all be described as diffusion nozzles in that each nozzle has an axial fuel delivery pipe and is surrounded at its discharge end by an air swirler which provides air for combustion to the fuel nozzle discharge.
  • the present inventors have discovered that reduction in the production of NOx can be achieved by using such a combined premix and diffusion nozzle. In operation, a relatively small amount of fuel is used to sustain a diffusion pilot whereas a premix section of the nozzle provides additional fuel for ignition of the main fuel supply from the upstream primary nozzles directed into the primary combustion chamber.
  • the present invention is especially applicable to gas turbine combustors of the type which include two combustion chambers separated by a venturi throat region.
  • An annular array of primary nozzles discharge fuel into an upstream or primary combustion chamber whereas a single central nozzle discharges fuel into a downstream or second combustion chamber.
  • the method of operation dictates that while under base load, the primary nozzles are flamed out whereas the single central combined diffusion and premix nozzle supports combustion of premix fuel from the primary nozzles.
  • the single central combined diffusion and premix nozzle reduces the fuel flow to the central diffusion flame from approximately 20 percent of the total fuel flow to about 2 percent of the total fuel flow for the entire combustor.
  • the design thus simultaneously minimizes the percentage of total fuel flow in the combuster that burns as a diffusion flame (with high NOx emissions) but allows sufficient heat input to ignite the main premixed flow by using the pilot premixed flow (which has low NOx emissions).
  • a combined diffusion and premix nozzle comprising:
  • a gas turbine 12 includes a compressor 14, a combustor 16 and a turbine 18 represented by a single blade. Although it is not specifically shown, it is well known that the turbine is drivingly connected to the compressor along a common axis.
  • the compressor pressurizes inlet air which is then turned in direction or reversed flowed to the combustor where it is used to cool the combustor and also used to provide air to the combustion process.
  • the gas turbine includes a plurality of combustors (one shown) which are located about the periphery of the gas turbine. In one particular gas turbine model there are fourteen such combustors disposed about the periphery of the gas turbine.
  • a transition duct 20 connects the outlet end of its particular combustor with the inlet end of the turbine to deliver the hot products of the combustion process to the turbine.
  • each combustor comprises a primary or pustream combustion chamber 24 and a second or downstream combustoin chamber 26 separated by a venturi throat region 28.
  • the combustor is surrounded by a combustor flow sleeve 30 which channels compressor discharge air flow to the combustor.
  • the combustor is further surrounded by an outer casing 31 which is bolted to the turbine casing 32.
  • Primary nozzles 36 provide fuel delivery to the upstream combustor 24 and are arranged in an annular array around a central secondary nozzle 38.
  • each combustor may include six primary nozzles and one secondary nozzle.
  • fuel is delivered to the nozzles through plumbing 42 in a manner well known in the art and fully described in the aforementioned patent. Ignition in the primary combustor is caused by spark plug 48 not shown in Figure 2 and in adjacent combustors by means of crossfire tubes 50 also well known in the art.
  • a diffusion nozzle 36 includes a fuel delivery nozzle 54 and an annular swirler 56.
  • the nozzle 54 delivers only fuel which is then subsequently mixed with swirler air for combustion.
  • the secondary nozzle is also a diffusion nozzle as will be explained further.
  • the dual stage, dual mode combustor is designed to operate in a premix mode such that all of the primary nozzles are simply mixing fuel and air to be ignited by the diffusion flame supported by the second or central diffusion nozzle.
  • this premixing of the primary nozzle fuel and ignition by the secondary diffusion nozzle led to a lower NOx output in the combustor.
  • a satisfactory pilot flame for the main premix flow from the upstream premix (primary) nozzles may be sustained by using a minimal diffusion pilot in combination with a central nozzle premix chamber.
  • the invention simultaneously minimized the percentage of total fuel in the combustor that burns as a diffusion flame (with high NOx emissions) whilie allowing sufficient heat input to ignite the main premixed flow by using the premixed secondary or pilot flow.
  • the combined nozzle includes a diffusion pilot 62 having a fuel delivery pipe 64.
  • the fuel delivery pipe has an axial pipe 66 and a plurality of radial, blind ended fuel distribution tubes 68 which extend radially outwardly from the axial pipe.
  • the fuel distribution tubes each include a plurality of fuel discharge holes 70 which are directed downstream toward the discharge end of the combined nozzle.
  • the fuel distribution holes are sized so as to obtain the desired percentage of fuel flow in to the premix chamber to be hereinafter described.
  • the diffusion pilot 62 further includes an air delivery pipe 74 coaxial with and surrounding the fuel delivery axial pipe 66.
  • the air input into the air delivery pipe is compressor discharge air which is reverse flowed around the combustor into the volume 76 defined by the flow sleeve 30 and the combustion chamber liner 78.
  • the diffusion pilot includes at its discharge end a first swirler annulus or diffusion pilot swirler 82 for the purpose of directing air delivery pipe discharge air to the diffusion pilot flame.
  • a premix chamber 84 is defined by a sleeve like truncated cone 85 which surrounds the diffusion pilot and includes a discharge end (see flow arrows) terminating adjacent the diffusion pilot discharge end. Compressor discharge air is also reverse flowed into the premix chamber from volume 76 in a manner similar to the air delivery pipe.
  • the plurality of radial fuel distribution tubes 68 extend through the air delivery pipe 74 and into the premix chamber annulus such that the fuel and air are mixed and delivered to a second swirler or premix chamber swirler 86 between the diffusion pilot and the premix chamber truncated cone 85.
  • a third swirler or central nozzle swirler 90 is located downstream from the discharge end of the combined diffusion and premix nozzle. This swirler is located between an extension or cup 92 on the discharge end of the pilot and the centerbody wall 95 of the primary combustion chamber. Compressor air is also reverse flowed to this swirler from the volume 76 surrounding the combustion liners. The purpose of this third swirler is to provide stability for the diffusion and premix nozzle flame when combining with the primary premix flow from the primary combustor.
  • the required design of the swirlers 82, 86 and 90 would be known to practitioners in the combustion art and therefore requires no further description.
  • the premix chamber or truncated cone is formed of any metal suitable to use within the gas turbine environment.
  • fuel flow and combustion is initiated in the primary combustor until a predetermined mid-range load. At that time, fuel flow is split between the primary nozzles and the combined diffusion and premix nozzle to reach a desired load whereas ignition of the combined diffusion and premix nozzle is established.
  • Fuel flow to the primary nozzles is then terminated to extinguish burning in the primary combustor. Fuel flow then is reestablished in the primary nozzles which then act as main premix chambers for the primary nozzle fuel main premix flow. At this point, according to prior practice, a diffusion flame using approximately twenty percent of the total combustor fuel flow would be left to produce a relatively high NOx output.
  • the foregoing invention produces less NOx while providing an opportunity to add to the fuel flow through the combined diffusion and premix nozzle because of the lower NOx output whereas the turn down ratio or the ability to operate under varying conditions is considerably widened because the diffusion pilot is subject to the premix flow of the pilot rather than the total overall premix flow from the surrounding primary nozzles.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)

Claims (5)

1. Kombinierte Diffusor- und Vormischdüse (100) enthaltend:
eine Diffusorsteuerung (62) mit einer Brennstoffzufuhrleitung (64), die eine axiale Leitung (66) mit einem Einlaßende und einem Auslaßende aufweist, einer Luftzufuhrleitung (74), die koaxial mit der axialen Leitung ist und die axiale Leitung umgibt, und einem ersten Verwirbler-Ringraum (82), der an dem Auslaßende der axialen Leitung (66) zwischen der axialen Leitung und der umgebenden Luftzufuhrleitung (74) angeordnet ist, dadurch gekennzeichnet, daß die Brennstoffzufuhrleitung (64) ferner mehrere radiale Brennstoffverteilungsrohre (68) aufweist, die von der axialen Leitung (66) nach außen ragen und stromabwärts von dem Einlaßende der axialen Leitung angeordnet sind, wobei die radialen Brennstoffverteilungsrohre sich über den Umfang der Luftverteilungsleitung (74) hinaus erstrecken, und daß die Düse ferner enthält eine Vormischkammer (84), die die Diffusorsteuerung (62) umgibt und ein Einlaßende und ein Auslaßende aufweist, wobei sich die radialen Brennstoffverteilungsrohre (68) in die Vormischkammer (84) erstrecken, wenigstens ein Brennstoffauslaßloch (70) in wenigstens einem radialen Brennstoffverteilungsrohr (68), wobei das Brennstoffauslaßloch (70) auf das Auslaßende der Vormischkammer (84) gerichtet ist, und einen zweiten Verwirbler-Ringraum (86) am Auslaßende der Vormischkammer (84) zwischen der Luftverteilungsleitung (74) und der umgebenden Vormischkammer (84).
2. Gasturbinenbrenner enthaltend erste (24) und zweite (26) Brennkammern, die durch einen Halsbereich (28) miteinander verbunden sind, der eine verkleinerte Abmessung im Vergleich zu den ersten und zweiten Brennkammern hat, mehrere diffusorartige, primäre Brennstoffdüsen (36) in einer ringförmigen Anordnung stromaufwärts von der ersten Brennkammer (24) zum Einführen von Brennstoff in die erste Brennkammer, wobei jede Diffusordüse (36) einen ringförmigen Verwirbler (56) zum Einführen von Druckluft in die erste Brennkammer (24) aufweist zum Erzeugen eines brennbaren Brennstoff/Luft-Gemisches, und eine kombinierte Diffusor- und Vormischdüse (100), die stromaufwärts von der zweiten Brennkammer (26) angeordnet ist, dadurch gekennzeichnet, daß die kombinierte Diffusor- und Vormischdüse nach Anspruch 1 aufgebaut ist.
3. Brenner nach Anspruch 2, dadurch gekennzeichnet, daß die Vormischkammer (84) ein abgestumpfter Kegel ist.
4. Brenner nach Anspruch 2, wobei die kombinierte Diffusor- und Vormischdüse (100) in dem Zentrum der ringförmigen Anordnung der mehreren primären Düsen (36) angeordnet ist und daß er ferner einen dritten Verwirbler (90) zwischen der kombinierten Diffusor- und Vormischdüse (100) und einer umgebenden Zentralkörperwand (95) aufweist.
5. Brenner nach Anspruch 4, dadurch gekennzeichnet, daß er einen Becher (92) der stromaufwärts von dem Auslaßende der kombinierten Diffusor- und Vormischdüse (100) und der Zentralkörperwand (95), die die zentrale Brennstoffdüse umgibt, angeordnet ist und der dritte Verwirbler-Ringraum (90) zwischen der Zentralkörperwand (95) und dem Becher (92) angeordnet ist.
EP19870115434 1986-11-25 1987-10-21 Kombinierter Diffusions- und Vormischpilotbrenner Expired EP0269824B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US93488586A 1986-11-25 1986-11-25
US934885 1986-11-25

Publications (3)

Publication Number Publication Date
EP0269824A2 EP0269824A2 (de) 1988-06-08
EP0269824A3 EP0269824A3 (en) 1988-07-06
EP0269824B1 true EP0269824B1 (de) 1990-12-19

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ID=25466234

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870115434 Expired EP0269824B1 (de) 1986-11-25 1987-10-21 Kombinierter Diffusions- und Vormischpilotbrenner

Country Status (4)

Country Link
EP (1) EP0269824B1 (de)
JP (1) JP2831641B2 (de)
DE (1) DE3766807D1 (de)
NO (1) NO166340C (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130008167A1 (en) * 2011-07-07 2013-01-10 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor

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US5193346A (en) * 1986-11-25 1993-03-16 General Electric Company Premixed secondary fuel nozzle with integral swirler
DE68923413T2 (de) * 1988-09-07 1996-04-04 Hitachi Ltd Kraftstoff-Luftvormischvorrichtung für eine Gasturbine.
JPH0772616B2 (ja) * 1989-05-24 1995-08-02 株式会社日立製作所 燃焼器及びその運転方法
US5125227A (en) * 1990-07-10 1992-06-30 General Electric Company Movable combustion system for a gas turbine
EP0488556B1 (de) * 1990-11-27 1997-07-16 General Electric Company Sekundäre Vormischbrennstoffdüse mit integrierter Verwirbelungsvorrichtung
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5318436A (en) * 1991-11-14 1994-06-07 United Technologies Corporation Low NOx combustion piloted by low NOx pilots
RU2031229C1 (ru) * 1992-03-09 1995-03-20 Анатолий Михайлович Рахмаилов Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель
US5267851A (en) * 1992-03-16 1993-12-07 General Electric Company Swirl gutters for isolating flow fields for combustion enhancement at non-baseload operating conditions
US5259184A (en) * 1992-03-30 1993-11-09 General Electric Company Dry low NOx single stage dual mode combustor construction for a gas turbine
IT1255613B (it) * 1992-09-24 1995-11-09 Eniricerche Spa Sistema di combustione a basse emissioni inquinanti per turbine a gas
US5410884A (en) * 1992-10-19 1995-05-02 Mitsubishi Jukogyo Kabushiki Kaisha Combustor for gas turbines with diverging pilot nozzle cone
US5435126A (en) * 1994-03-14 1995-07-25 General Electric Company Fuel nozzle for a turbine having dual capability for diffusion and premix combustion and methods of operation
JP3183053B2 (ja) * 1994-07-20 2001-07-03 株式会社日立製作所 ガスタービン燃焼器及びガスタービン
DE19542644B4 (de) * 1995-11-17 2008-12-11 Alstom Vormischverbrennung
US6539721B2 (en) 2001-07-10 2003-04-01 Pratt & Whitney Canada Corp. Gas-liquid premixer
US8156743B2 (en) * 2006-05-04 2012-04-17 General Electric Company Method and arrangement for expanding a primary and secondary flame in a combustor
JP5193088B2 (ja) * 2009-02-20 2013-05-08 三菱重工業株式会社 燃焼器及びガスタービン
US8919673B2 (en) * 2010-04-14 2014-12-30 General Electric Company Apparatus and method for a fuel nozzle
US9016039B2 (en) * 2012-04-05 2015-04-28 General Electric Company Combustor and method for supplying fuel to a combustor

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DE3241162A1 (de) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130008167A1 (en) * 2011-07-07 2013-01-10 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
US9003800B2 (en) * 2011-07-07 2015-04-14 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
US10197284B2 (en) 2011-07-07 2019-02-05 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor

Also Published As

Publication number Publication date
EP0269824A3 (en) 1988-07-06
JP2831641B2 (ja) 1998-12-02
EP0269824A2 (de) 1988-06-08
NO874893D0 (no) 1987-11-24
DE3766807D1 (de) 1991-01-31
NO166340B (no) 1991-03-25
NO874893L (no) 1988-05-26
JPH01137117A (ja) 1989-05-30
NO166340C (no) 1991-07-03

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