EP0501877A1 - Chambre de combustion à prémélange pauvre munie d'une enceinte à contre-courant destinée à stabiliser la flamme du prémélange - Google Patents

Chambre de combustion à prémélange pauvre munie d'une enceinte à contre-courant destinée à stabiliser la flamme du prémélange Download PDF

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Publication number
EP0501877A1
EP0501877A1 EP92400489A EP92400489A EP0501877A1 EP 0501877 A1 EP0501877 A1 EP 0501877A1 EP 92400489 A EP92400489 A EP 92400489A EP 92400489 A EP92400489 A EP 92400489A EP 0501877 A1 EP0501877 A1 EP 0501877A1
Authority
EP
European Patent Office
Prior art keywords
enclosure
orifices
combustion chamber
wall
fuel
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Withdrawn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
EP92400489A
Other languages
German (de)
English (en)
French (fr)
Inventor
Gérard Yves Georges Barbier
Xavier Marie Henri Bardey
Michel André Albert Desaulty
Serge Marcel Meunier
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0501877A1 publication Critical patent/EP0501877A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • 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
    • 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

Definitions

  • combustion chamber in particular for turbo-machines, comprising a first enclosure, provided with a first fuel injection device for low power operation and primary oxidant intake orifices; a second enclosure, separate from the first enclosure, provided with a second fuel injection device for operation at full power and with primary oxidizer intake orifices; and, an evacuation chamber for the burnt gases, distinct from said first and second enclosures, into which these first and second enclosures open in parallel.
  • the first enclosure provided with the injection device for idling, does not have dilution orifices, while the second enclosure is provided with it.
  • the second enclosure fitted with the injection device for operation at full load, is arranged in series, following the first enclosure, without its own admission of primary oxidizer.
  • the invention intends to remedy these various drawbacks noted, therefore having as its object a combustion chamber, as defined above, in which the wall delimiting the first enclosure is crossed by inlet ports for dilution oxidant, the wall delimiting the second enclosure being, on the contrary, free of orifices other than said primary oxidizer inlet orifices producing a lean premix inside this enclosure.
  • the main advantage of the invention lies in the possibility of obtaining good combustion stability and reduced pollution at the various desired operations, in particular at idle speed and at full load.
  • the space 21 between the outer wall 16 of the casing and the corresponding parts of the wall 6, of the support 2 and of the bottom 5 may contain, as in the example shown, an additional compressor 22; for this purpose, an intermediate wall 23, inside the casing, separates the interior of the latter into two distinct volumes: the space 21, and a space 24, delimited by this intermediate wall 23, the wall 8 and the remaining parts from the bottom 5 and from the wall 6.
  • the space 24 is in direct communication with the orifice 18 of the upstream general intake of compressed oxidizer.
  • the two extreme operating speeds are that of idling, with only the first fuel injection device 3 in service, and that of full load where the second fuel injection device 10 is also in service.
  • the arrangements of the invention shown allow violent combustion of the rich mixture in the first enclosure 1, which is low in pollution and stable due to the configuration against the current of the injection (F3) in this enclosure relative to the direction F14 d evacuation of the burnt gases outside the enclosure 14.
  • combustion in the second enclosure 7 takes place in a premix enclosure, and relates to a very lean mixture. This combustion can be initiated by a catalyst and / or by the supply of hot gases from the first enclosure 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
  • Fuel-Injection Apparatus (AREA)
EP92400489A 1991-02-28 1992-02-26 Chambre de combustion à prémélange pauvre munie d'une enceinte à contre-courant destinée à stabiliser la flamme du prémélange Withdrawn EP0501877A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9102389A FR2673455A1 (fr) 1991-02-28 1991-02-28 Chambre de combustion a premelange pauvre munie d'une enceinte a contre-courant destinee a stabiliser la flamme du premelange.
FR9102389 1991-02-28

Publications (1)

Publication Number Publication Date
EP0501877A1 true EP0501877A1 (fr) 1992-09-02

Family

ID=9410188

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92400489A Withdrawn EP0501877A1 (fr) 1991-02-28 1992-02-26 Chambre de combustion à prémélange pauvre munie d'une enceinte à contre-courant destinée à stabiliser la flamme du prémélange

Country Status (4)

Country Link
US (1) US5261239A (id)
EP (1) EP0501877A1 (id)
JP (1) JPH04316922A (id)
FR (1) FR2673455A1 (id)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2532857A1 (en) * 2011-06-06 2012-12-12 United Technologies Corporation Turbomachine assembly with combustors having different flow directions and corresponding operating method

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5813232A (en) * 1995-06-05 1998-09-29 Allison Engine Company, Inc. Dry low emission combustor for gas turbine engines
DE69625744T2 (de) * 1995-06-05 2003-10-16 Rolls Royce Corp Magervormischbrenner mit niedrigem NOx-Ausstoss für industrielle Gasturbinen
DE19728375A1 (de) * 1997-07-03 1999-01-07 Bmw Rolls Royce Gmbh Betriebsverfahren für eine axial gestufte Brennkammer einer Fluggasturbine
US20110219779A1 (en) * 2010-03-11 2011-09-15 Honeywell International Inc. Low emission combustion systems and methods for gas turbine engines
US9194586B2 (en) * 2011-12-07 2015-11-24 Pratt & Whitney Canada Corp. Two-stage combustor for gas turbine engine
US10976052B2 (en) * 2017-10-25 2021-04-13 General Electric Company Volute trapped vortex combustor assembly
US11828469B2 (en) * 2022-03-03 2023-11-28 General Electric Company Adaptive trapped vortex combustor

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2116363A1 (id) * 1970-12-02 1972-07-13 Gen Electric
DE2412120A1 (de) * 1973-03-13 1974-09-19 Snecma Umweltfreundliche brennkammer fuer gasturbinen
GB2010407A (en) * 1977-12-01 1979-06-27 United Technologies Corp Burner for gas turbine engine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5847928A (ja) * 1981-09-18 1983-03-19 Hitachi Ltd ガスタ−ビン燃焼器
JPS60240833A (ja) * 1984-05-15 1985-11-29 Hitachi Ltd ガスタ−ビン燃焼方法及びガスタ−ビン燃焼器

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2116363A1 (id) * 1970-12-02 1972-07-13 Gen Electric
DE2412120A1 (de) * 1973-03-13 1974-09-19 Snecma Umweltfreundliche brennkammer fuer gasturbinen
GB2010407A (en) * 1977-12-01 1979-06-27 United Technologies Corp Burner for gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2532857A1 (en) * 2011-06-06 2012-12-12 United Technologies Corporation Turbomachine assembly with combustors having different flow directions and corresponding operating method

Also Published As

Publication number Publication date
JPH04316922A (ja) 1992-11-09
US5261239A (en) 1993-11-16
FR2673455A1 (fr) 1992-09-04
FR2673455B1 (id) 1994-12-16

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