EP0269824B1 - Brûleur combiné à diffusion et à prémélange pour veilleuse - Google Patents

Brûleur combiné à diffusion et à prémélange pour veilleuse 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
Other languages
German (de)
English (en)
Other versions
EP0269824A2 (fr
EP0269824A3 (en
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
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 EP0269824A2 publication Critical patent/EP0269824A2/fr
Publication of EP0269824A3 publication Critical patent/EP0269824A3/en
Application granted granted Critical
Publication of EP0269824B1 publication Critical patent/EP0269824B1/fr
Expired 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
    • F23D11/005—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising means
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding 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. Injecteur combiné (100) de diffusion et de pré- mélange, comprenant:
une veilleuse de diffusion (62) comportant une conduite de fourniture de carburant (64) comprenant une conduite axiale (66) ayant une extrémité d'entrée et une extrémité de décharge; une conduite de fourniture d'air (74) de même axe que la conduite axiale et entourant la conduite axiale, et un premier anneau (82) de dispositifs de tourbillonnement disposé à l'extrémité de décharge de la conduite axiale (66) entre la conduite axiale et la conduite environnante de fourniture d'air (74); caractérisé en ce que:
la conduite de fourniture de carburant (64) comprend en outre une multitude de tubes radiaux de distribution de carburant (68) qui s'étendent vers l'extérieur de la conduite axiale (66) et sont situés dans la direction de l'extrémité d'entrée de la conduite axiale, les tubes radiaux de distribution du carburant (68) s'étendant au-delà de la circonférence de la conduite de fourniture d'air (74); et l'injecteur comporte en outre:
une chambre de pré-mélange (84) entourant la veilleuse de diffusion (62) et présentant une extrémité d'entrée et une extrémité de décharge, les tubes radiaux de distribution du carburant (68) s'étendant jusque dans la chambre de prémélange (84);
au moins un trou de décharge du carburant (70) dans au moins l'un des tubes radiaux de distribution du carburant (68), le trou de décharge du carburant (70) étant dirigé vers l'extrémité de décharge de la chambre de pré-mélange (84) et, un second anneau de dispositifs de tourbillonnement (86) à l'extrémité de décharge de la chambre de pré-mélange (84) entre la conduite de fourniture d'air (74) et la chambre environnante de pré-mélange (84).
2. Dispositif de combustion perfectionné pour turbine à gaz du type comprenant des première (24) et seconde (26) chambres de combustion intercon- nectées par une zone à col (28), la zone à col ayant des dimensions réduites par rapport aux première et seconde chambres de combustion; une multitude d'injecteurs primaires (36) de carburant du type à diffusion dans un réseau annulaire en amont de la première chambre de combustion (24) pour introduire le carburant dans la première chambre de combustion, chacun des injecteurs à diffusion (36) comportant un dispositif annulaire de tourbillonnement (56) pour introduire de l'air pressurisé dans la première chambre de combustion (24) afin de créer un mélange combustible d'air et de carburant; et un injecteur combiné de diffusion et de pré-mélange (100) placé en amont de la seconde chambre de combustion (26); caractérisé en ce que l'injecteur combiné de diffusion et de pré-mélange est tel que revendiqué en revendication 1.
3. Dispositif de combustion selon la revendication 2, caractérisé en outre en ce que la chambre de pré-mélange (84) est un cône tronqué.
4. Dispositif de combustion selon la revendication 2, dans lequel l'injecteur combiné de diffusion et de prémélange (100) est situé au centre du réseau annulaire d'une multitude d'injecteurs primaires (36), et caractérisé en outre en ce qu'il comprend un troisième dispositif de tourbillonnement (90) entre l'injecteur combiné de diffusion et de pré-mélange (100) et une paroi (84) environnante du corps central.
5. Dispositif de combustion selon la revendication 4, caractérisé en outre en ce qu'il comprend: une coupe (92) placée en aval de l'extrémité de décharge de l'injecteur combiné de diffusion et de pré- mélange (100) et de la paroi (95) du corps central entourant l'injecteur central de carburant; et en ce que:
le troisième anneau (90) de dispositifs de tourbillonnement est placé entre la paroi (95) du corps central et la coupe (92).
EP19870115434 1986-11-25 1987-10-21 Brûleur combiné à diffusion et à prémélange pour veilleuse Expired EP0269824B1 (fr)

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 (fr) 1988-06-08
EP0269824A3 EP0269824A3 (en) 1988-07-06
EP0269824B1 true EP0269824B1 (fr) 1990-12-19

Family

ID=25466234

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870115434 Expired EP0269824B1 (fr) 1986-11-25 1987-10-21 Brûleur combiné à diffusion et à prémélange pour veilleuse

Country Status (4)

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

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
EP0358437B1 (fr) * 1988-09-07 1995-07-12 Hitachi, Ltd. Dispositif de prémélange air-carburant pour une turbine à gaz
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 (fr) * 1990-11-27 1997-07-16 General Electric Company Injecteur secondaire de carburant à prémélange avec dispositif de tourbillonnement incorporé
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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US3886728A (en) * 1974-05-01 1975-06-03 Gen Motors Corp Combustor prechamber
US3958416A (en) * 1974-12-12 1976-05-25 General Motors Corporation Combustion apparatus
JPS51123413A (en) * 1975-04-19 1976-10-28 Nissan Motor Co Ltd Combustion system of gas turbine
US4292801A (en) * 1979-07-11 1981-10-06 General Electric Company Dual stage-dual mode low nox combustor
US4389848A (en) * 1981-01-12 1983-06-28 United Technologies Corporation Burner construction for gas turbines
DE3361535D1 (en) * 1982-05-28 1986-01-30 Bbc Brown Boveri & Cie Gas turbine combustion chamber and method of operating it
DE3241162A1 (de) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner
JPS59202324A (ja) * 1983-05-04 1984-11-16 Hitachi Ltd ガスタ−ビン低ＮＯｘ燃焼器

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

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