EP0576697B1 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP0576697B1
EP0576697B1 EP92110969A EP92110969A EP0576697B1 EP 0576697 B1 EP0576697 B1 EP 0576697B1 EP 92110969 A EP92110969 A EP 92110969A EP 92110969 A EP92110969 A EP 92110969A EP 0576697 B1 EP0576697 B1 EP 0576697B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
burners
combustion
catalytic
gas
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 - Lifetime
Application number
EP92110969A
Other languages
German (de)
English (en)
Other versions
EP0576697A1 (fr
Inventor
Jakob Dr. Keller
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.)
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to DE59208831T priority Critical patent/DE59208831D1/de
Priority to EP92110969A priority patent/EP0576697B1/fr
Priority to JP5156829A priority patent/JPH06207717A/ja
Priority to US08/083,898 priority patent/US5412938A/en
Publication of EP0576697A1 publication Critical patent/EP0576697A1/fr
Application granted granted Critical
Publication of EP0576697B1 publication Critical patent/EP0576697B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
    • 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 invention relates to the combustion chamber of a gas turbine, in which catalytic burners are used in addition to classic burner types.
  • the combination of diffusion burners and catalytic burners is known. It is used in a kind of mixed operation, whereby the combustion chamber is usually started up to a certain partial load in pure diffusion operation. Then more and more catalytic burners are switched on. The aim is to run the combustion chamber in full-load operation in purely catalytic operation.
  • the catalytic burners are characterized by the fact that they remain operational even with a very lean fuel-air mixture. On the other hand, they also have typical disadvantages such as a lack of multi-fuel capability, slow controllability, problematic ignition and start-up.
  • combustion chambers for gas turbines based on premix burners are known, for example from EP-B1 29 619.
  • a pre-mixing / pre-evaporation process with a large excess of air takes place between the injected fuel and the compressor air before the actual combustion process downstream of a flame holder takes place.
  • the emission values of pollutants from combustion can be significantly reduced.
  • a combustion chamber is known from US-A-4,040,252, in which catalytic afterburner is supplied with the combustion gases of a premix combustion and additional air.
  • the invention tries to avoid all these disadvantages. It is based on the task of creating a measure by means of which the combustion chamber can be operated as close as possible to the lean extinguishing limit, ie in the area in which practically no NO x is produced.
  • the premix burner and the catalytic burner are designed to be interchangeable.
  • This provides a simple means of adapting the burner configuration to the particular combustion chamber operation, for example with regard to fuel or pressure.
  • the aim is to be able to operate the combustion chamber without a catalytic burner in order to take full advantage of the premix combustion.
  • the interchangeability of the different types of burners can thus be regarded as a sensible option for switching on catalytic burners as required, whereby only as many catalytic burners are used as are required for stable operation of the combustion chamber.
  • the catalytic burners are provided with exhaust gas recirculation, the exhaust gas preferably being removed from the combustion chamber.
  • This measure is based on the idea of giving the combustion mixture the minimum temperature necessary for the operation of the catalytic burner. This makes it possible to dispense with the pre-burners that were customary in catalytic burners.
  • the catalytic burners are advantageously arranged in the primary zone of the combustion chamber in highly stressed wall parts, where they perform a kind of heat shield function. This measure makes it possible to dispense with the usual wall cooling at the relevant points, which meets the requirement for the surface to be cooled as little as possible.
  • premix burners 10 and catalytic burners 20 are arranged in the dome-shaped end of a combustion chamber in the combustion chamber wall 1.
  • the latter are located locally at locations that would normally need to be cooled heavily. They essentially consist of the actual catalyst 21, which is surrounded by a bell-shaped housing 22.
  • a fuel feed 23 penetrates the housing wall, gas preferably being used as the fuel.
  • the combustion air is conducted into the interior of the housing via an annular air inlet 24.
  • the combustion air at the outlet of the gas turbine compressor (not shown) generally has a temperature of approximately 350 ° C. This is not enough to keep the catalytic combustion going.
  • the air inlet 24 is therefore designed as a jet pump.
  • hot fuel gas is sucked out of the combustion chamber 25 into the interior of the housing via this jet pump.
  • exhaust nozzles 26 which are distributed around the circumference of the catalytic converter and are cooled by the combustion air.
  • the jet pump and the exhaust gas nozzles are dimensioned in such a way that the amount of exhaust gas sucked in is large enough to safely reach the critical temperature of, for example, 550 ° C. required for the catalyzer.
  • the critical temperature for example, 550 ° C.
  • the schematically shown premix burner 10 according to FIGS. 1 and 2 is a so-called double-cone burner, as is known for example from EP-B1-0 321 809. It essentially consists of two hollow, conical partial bodies 11, 12 which are nested one inside the other in the direction of flow. The respective central axes 13, 14 of the two partial bodies are offset from one another. The adjacent walls of the two partial bodies in their longitudinal extent form tangential slots 15 for the combustion air, which in this way reaches the interior of the burner. A first fuel nozzle 16 for liquid fuel is arranged there. The fuel is injected into the hollow cone at an acute angle. The resulting conical liquid fuel profile is enclosed by the combustion air flowing in tangentially.
  • the concentration of the fuel is continuously reduced in the axial direction due to the mixing with the combustion air.
  • the burner can also be operated with gaseous fuel.
  • gas inflow openings 17 distributed in the longitudinal direction are provided in the region of the tangential slots in the walls of the two partial bodies. In gas operation, the mixture formation begins with the combustion air thus already in the zone of the inlet slots 15. It goes without saying that mixed operation with both types of fuel is also possible in this way.
  • a fuel concentration that is as homogeneous as possible is established over the loaded cross-section.
  • a defined dome-shaped return flow zone is created at the burner outlet, at the tip of which the ignition takes place.
  • the mode of operation of the invention is now explained on the basis of the fuel control curve in FIG. 4.
  • the burner arrangement shown in FIG. 3 is used as the basis for this and the assumption is made that the burners are only switched on or off in groups. In this case, it proves to be expedient to first ignite the internal burners and then gradually start up further external fuel elements.
  • the burners of groups u, v, w, x and y are premix burners, those of group z are catalytic burners.
  • the groups are designated as such in Fig. 3.
  • the diagram does not show the actual starting process of the gas turbine, which begins at approx. 20% engine speed with the initial ignition via the centrally arranged pilot burner 5 and is completed when the engine reaches the nominal engine speed and the synchronization.
  • the required NO x limit values can easily be fallen below.
  • the stability limit is low due to the low flame temperature.
  • the range between ignitability and extinguishing is relatively narrow for the safe operation of the combustion chamber over the full load range.
  • the combustion chamber is started up with 12 burners according to the thickly drawn switching curve from idling to 15% load.
  • the groups u and w are in operation. Due to the increase in gas supply, the excess air figure at 15% load has become so low that burner group v is now switched on while group w is switched off at the same time. There are therefore 15 premix burners in operation.
  • the further control curve when the load is increased is then determined in such a way that the excess air figure is constantly in the same range.
  • group z with the catalytic auxiliary burners is additionally put into operation at 86% load. This results in a driving style directly on the stability limit. It goes without saying that the new measure can be applied not only at full load, but also, if necessary, at partial load. Basically, the catalytic burner can be used to reach operating points that are not possible with pure premix combustion, since the latter must always maintain a certain safety distance from the extinguishing limit.
  • the new way of driving on the extinguishing limit means that the NO x values of 20 ppm that can be achieved today can certainly be significantly undercut.

Claims (5)

  1. Chambre de combustion, en particulier pour des turbines à gaz, dans laquelle des brûleurs à prémélange (10) alimentés parallèlement en air de combustion et des brûleurs catalytiques (20), marchant de préférence au gaz, sont disposés sur une paroi commune (1) de la chambre de combustion, dans laquelle la combustion principale est effectuée avec les brûleurs à prémélange.
  2. Chambre de combustion suivant la revendication 1, caractérisée en ce que les brûleurs à prémélange (10) et les brûleurs catalytiques (20) sont configurés de façon interchangeable.
  3. Chambre de combustion suivant la revendication 1, caractérisée en ce que les brûleurs catalytiques (20) sont pourvus d'un recyclage des gaz d'échappement (24, 26), les gaz d'échappement étant de préférence prélevés dans le volume de combustion (25).
  4. Chambre de combustion suivant la revendication 3, caractérisée en ce que l'entrée de l'air de combustion pour les brûleurs catalytiques est constituée comme une pompe à jet (24), les gaz d'échappement étant aspirés par cette pompe à jet hors du volume de combustion (25).
  5. Chambre de combustion suivant la revendication 1, caractérisée en ce que les brûleurs catalytiques (20) sont disposés dans la zone primaire de la chambre de combustion dans les parties de paroi fortement sollicitées.
EP92110969A 1992-06-29 1992-06-29 Chambre de combustion pour turbine à gaz Expired - Lifetime EP0576697B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE59208831T DE59208831D1 (de) 1992-06-29 1992-06-29 Brennkammer einer Gasturbine
EP92110969A EP0576697B1 (fr) 1992-06-29 1992-06-29 Chambre de combustion pour turbine à gaz
JP5156829A JPH06207717A (ja) 1992-06-29 1993-06-28 ガスタービンの燃焼器
US08/083,898 US5412938A (en) 1992-06-29 1993-06-29 Combustion chamber of a gas turbine having premixing and catalytic burners

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92110969A EP0576697B1 (fr) 1992-06-29 1992-06-29 Chambre de combustion pour turbine à gaz

Publications (2)

Publication Number Publication Date
EP0576697A1 EP0576697A1 (fr) 1994-01-05
EP0576697B1 true EP0576697B1 (fr) 1997-08-27

Family

ID=8209757

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92110969A Expired - Lifetime EP0576697B1 (fr) 1992-06-29 1992-06-29 Chambre de combustion pour turbine à gaz

Country Status (4)

Country Link
US (1) US5412938A (fr)
EP (1) EP0576697B1 (fr)
JP (1) JPH06207717A (fr)
DE (1) DE59208831D1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5569020A (en) * 1994-11-05 1996-10-29 Abb Research Ltd. Method and device for operating a premixing burner
US5687571A (en) * 1995-02-20 1997-11-18 Asea Brown Boveri Ag Combustion chamber with two-stage combustion
US5829967A (en) * 1995-03-24 1998-11-03 Asea Brown Boveri Ag Combustion chamber with two-stage combustion
WO1999046540A1 (fr) 1998-03-10 1999-09-16 Siemens Aktiengesellschaft Chambre de combustion et mode de fonctionnement d'une chambre de combustion
US7029272B2 (en) 2001-08-09 2006-04-18 Siemens Aktiengesellschaft Premix burner and method for operation thereof

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5720163A (en) * 1992-02-14 1998-02-24 Precision Combustion, Inc. Torch assembly
DE4411624A1 (de) * 1994-04-02 1995-10-05 Abb Management Ag Brennkammer mit Vormischbrennern
DE4424597B4 (de) * 1994-07-13 2006-03-23 Alstom Verbrennungsvorrichtung
DE19510743A1 (de) * 1995-02-20 1996-09-26 Abb Management Ag Brennkammer mit Zweistufenverbrennung
EP0747635B1 (fr) * 1995-06-05 2003-01-15 Rolls-Royce Corporation Brûleur à prémélange pauvre avec faible production de NOx pour turbines à gaz industrielles
DE19615910B4 (de) * 1996-04-22 2006-09-14 Alstom Brenneranordnung
US5685156A (en) * 1996-05-20 1997-11-11 Capstone Turbine Corporation Catalytic combustion system
DE19637727A1 (de) 1996-09-16 1998-03-19 Siemens Ag Verfahren zur katalytischen Verbrennung eines fossilen Brennstoffs in einer Verbrennungsanlage und Anordnung zur Durchführung dieses Verfahrens
US6453658B1 (en) 2000-02-24 2002-09-24 Capstone Turbine Corporation Multi-stage multi-plane combustion system for a gas turbine engine
US6532743B1 (en) 2001-04-30 2003-03-18 Pratt & Whitney Canada Corp. Ultra low NOx emissions combustion system for gas turbine engines
DE50212720D1 (de) 2001-04-30 2008-10-16 Alstom Technology Ltd Katalytischer Brenner
US6508056B1 (en) 2001-07-16 2003-01-21 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of Natural Resources Duct burner with conical wire mesh and vanes
US6658856B2 (en) 2002-01-17 2003-12-09 Vericor Power Systems Llc Hybrid lean premixing catalytic combustion system for gas turbines
DE10257704A1 (de) * 2002-12-11 2004-07-15 Alstom Technology Ltd Verfahren zur Verbrennung eines Brennstoffs
US6993912B2 (en) * 2003-01-23 2006-02-07 Pratt & Whitney Canada Corp. Ultra low Nox emissions combustion system for gas turbine engines
AT10353U3 (de) * 2008-07-24 2009-08-15 Avl List Gmbh Prüfanordnung und prüfsystem für turbolader
CN101737802B (zh) * 2009-11-27 2012-12-26 北京航空航天大学 中心空腔稳火切向燃烧室
US9347375B2 (en) * 2012-06-22 2016-05-24 General Electronic Company Hot EGR driven by turbomachinery
RU2561956C2 (ru) * 2012-07-09 2015-09-10 Альстом Текнолоджи Лтд Газотурбинная система сгорания
US10473029B2 (en) 2013-12-30 2019-11-12 William M. Conlon Liquid air power and storage
WO2016195968A1 (fr) 2015-06-01 2016-12-08 Conlon William M Fonctionnement à charge partielle d'énergie à air liquide, et système de stockage
WO2016195999A1 (fr) 2015-06-03 2016-12-08 Conlon William M Énergie d'air liquide et stockage à capture de carbone
WO2016204893A1 (fr) 2015-06-16 2016-12-22 Conlon William M Stockage d'énergie par liquide cryogénique
WO2017069922A1 (fr) 2015-10-21 2017-04-27 Conlon William M Énergie air-liquide haute-pression et stockage

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2986882A (en) * 1955-06-27 1961-06-06 Vladimir H Pavlecka Sub-atmospheric gas turbine circuits
US3323304A (en) * 1965-03-01 1967-06-06 Ljobet Andres Fraucisco Apparatus for producing high temperature gaseous stream
GB1335134A (en) * 1970-12-05 1973-10-24 Nissan Motor Combustion apparatus of a gas turbine engine
US3969892A (en) * 1971-11-26 1976-07-20 General Motors Corporation Combustion system
US3851467A (en) * 1973-07-02 1974-12-03 Gen Motors Corp Recirculating combustion apparatus jet pump
US3826083A (en) * 1973-07-16 1974-07-30 Gen Motors Corp Recirculating combustion apparatus jet pump
US3927958A (en) * 1974-10-29 1975-12-23 Gen Motors Corp Recirculating combustion apparatus
US3943705A (en) * 1974-11-15 1976-03-16 Westinghouse Electric Corporation Wide range catalytic combustor
US4040252A (en) * 1976-01-30 1977-08-09 United Technologies Corporation Catalytic premixing combustor
DE2950535A1 (de) * 1979-11-23 1981-06-11 BBC AG Brown, Boveri & Cie., Baden, Aargau Brennkammer einer gasturbine mit vormisch/vorverdampf-elementen
US4356698A (en) * 1980-10-02 1982-11-02 United Technologies Corporation Staged combustor having aerodynamically separated combustion zones
US4433540A (en) * 1982-06-07 1984-02-28 General Motors Corporation Low emission combustor
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
JP2574171B2 (ja) * 1988-08-25 1997-01-22 東燃化学株式会社 防水性及び通気性を有する複合フィルムの製造方法
CH678757A5 (fr) * 1989-03-15 1991-10-31 Asea Brown Boveri
US5247993A (en) * 1992-06-16 1993-09-28 Union Oil Company Of California Enhanced imbibition oil recovery process

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5569020A (en) * 1994-11-05 1996-10-29 Abb Research Ltd. Method and device for operating a premixing burner
US5687571A (en) * 1995-02-20 1997-11-18 Asea Brown Boveri Ag Combustion chamber with two-stage combustion
US5829967A (en) * 1995-03-24 1998-11-03 Asea Brown Boveri Ag Combustion chamber with two-stage combustion
WO1999046540A1 (fr) 1998-03-10 1999-09-16 Siemens Aktiengesellschaft Chambre de combustion et mode de fonctionnement d'une chambre de combustion
US7029272B2 (en) 2001-08-09 2006-04-18 Siemens Aktiengesellschaft Premix burner and method for operation thereof

Also Published As

Publication number Publication date
US5412938A (en) 1995-05-09
JPH06207717A (ja) 1994-07-26
DE59208831D1 (de) 1997-10-02
EP0576697A1 (fr) 1994-01-05

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