DE69207360D1 - Einrichtung um bei einer Gasturbinenbrennkammer eine geregelte Luftmenge an den Überschneidungsstellen von Kraftstoffsprühkegeln einzublasen - Google Patents

Einrichtung um bei einer Gasturbinenbrennkammer eine geregelte Luftmenge an den Überschneidungsstellen von Kraftstoffsprühkegeln einzublasen

Info

Publication number
DE69207360D1
DE69207360D1 DE69207360T DE69207360T DE69207360D1 DE 69207360 D1 DE69207360 D1 DE 69207360D1 DE 69207360 T DE69207360 T DE 69207360T DE 69207360 T DE69207360 T DE 69207360T DE 69207360 D1 DE69207360 D1 DE 69207360D1
Authority
DE
Germany
Prior art keywords
blowing
intersection
air
combustion chamber
gas turbine
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
DE69207360T
Other languages
English (en)
Other versions
DE69207360T2 (de
Inventor
Denis Roger Henri Ansart
Gerard Joseph Pa Bayle-Laboure
Jacques Louis Michel Maunand
Denis Jean Maurice Sandelis
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 DE69207360D1 publication Critical patent/DE69207360D1/de
Application granted granted Critical
Publication of DE69207360T2 publication Critical patent/DE69207360T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
DE69207360T 1991-11-20 1992-11-18 Einrichtung um bei einer Gasturbinenbrennkammer eine geregelte Luftmenge an den Überschneidungsstellen von Kraftstoffsprühkegeln einzublasen Expired - Lifetime DE69207360T2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9114291A FR2683891B1 (fr) 1991-11-20 1991-11-20 Turbomachine comportant un dispositif pour diminuer l'emission d'oxydes d'azote.

Publications (2)

Publication Number Publication Date
DE69207360D1 true DE69207360D1 (de) 1996-02-15
DE69207360T2 DE69207360T2 (de) 1996-08-01

Family

ID=9419137

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69207360T Expired - Lifetime DE69207360T2 (de) 1991-11-20 1992-11-18 Einrichtung um bei einer Gasturbinenbrennkammer eine geregelte Luftmenge an den Überschneidungsstellen von Kraftstoffsprühkegeln einzublasen

Country Status (4)

Country Link
US (1) US5285630A (de)
EP (1) EP0543720B1 (de)
DE (1) DE69207360T2 (de)
FR (1) FR2683891B1 (de)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4851674B2 (ja) 2000-05-01 2012-01-11 キャプストーン タービン コーポレーション エネルギーシステムと併用する環状燃焼器
JP2002317650A (ja) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
GB2396687A (en) * 2002-12-23 2004-06-30 Rolls Royce Plc Helmholtz resonator for combustion chamber use
US20090260340A1 (en) * 2008-04-17 2009-10-22 General Electric Company Combustor of a Turbine, a Method of Retro-Fitting a Combustor of a Turbine and a Method of Building a Combustor of a Turbine
US8713945B2 (en) * 2010-06-29 2014-05-06 Nuovo Pignone S.P.A. Liner aft end support mechanisms and spring loaded liner stop mechanisms
DE102011007059A1 (de) * 2011-04-08 2012-10-11 Siemens Aktiengesellschaft Brennkammeranordnung mit Verdichterendluft-Bypass für den Teillastbetrieb
US9869279B2 (en) * 2012-11-02 2018-01-16 General Electric Company System and method for a multi-wall turbine combustor
CN104566463B (zh) * 2014-11-29 2016-12-07 哈尔滨广瀚燃气轮机有限公司 燃气轮机低排放燃烧室空气调节装置
US10288289B2 (en) * 2014-12-12 2019-05-14 United Technologies Corporation Gas turbine engine diffuser-combustor assembly inner casing
US10619856B2 (en) * 2017-03-13 2020-04-14 Rolls-Royce Corporation Notched gas turbine combustor cowl
US10982852B2 (en) 2018-11-05 2021-04-20 Rolls-Royce Corporation Cowl integration to combustor wall

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB662764A (en) * 1949-01-12 1951-12-12 Lucas Ltd Joseph Improvements relating to combustion chambers for jet-engines or gas turbines
US2770096A (en) * 1952-09-15 1956-11-13 Phillips Petroleum Co Continuous combustion chamber with air flow and turbulence controlled by flame frontposition
US3705492A (en) * 1971-01-11 1972-12-12 Gen Motors Corp Regenerative gas turbine system
US3952501A (en) * 1971-04-15 1976-04-27 United Aircraft Of Canada Limited Gas turbine control
FR2133832B1 (de) * 1971-04-15 1975-10-24 United Aircraft Canada
US3842597A (en) * 1973-03-16 1974-10-22 Gen Electric Gas turbine engine with means for reducing the formation and emission of nitrogen oxides
US4138842A (en) * 1975-11-05 1979-02-13 Zwick Eugene B Low emission combustion apparatus
US4255927A (en) * 1978-06-29 1981-03-17 General Electric Company Combustion control system
GB2039359A (en) * 1979-01-15 1980-08-06 United Technologies Corp Gas turbine combustion chamber
CH680084A5 (de) * 1989-06-06 1992-06-15 Asea Brown Boveri

Also Published As

Publication number Publication date
EP0543720B1 (de) 1996-01-03
DE69207360T2 (de) 1996-08-01
US5285630A (en) 1994-02-15
FR2683891B1 (fr) 1995-03-24
FR2683891A1 (fr) 1993-05-21
EP0543720A1 (de) 1993-05-26

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: SNECMA MOTEURS, PARIS, FR

8327 Change in the person/name/address of the patent owner

Owner name: SNECMA, PARIS, FR