FR2357738A1 - Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds - Google Patents

Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds

Info

Publication number
FR2357738A1
FR2357738A1 FR7620707A FR7620707A FR2357738A1 FR 2357738 A1 FR2357738 A1 FR 2357738A1 FR 7620707 A FR7620707 A FR 7620707A FR 7620707 A FR7620707 A FR 7620707A FR 2357738 A1 FR2357738 A1 FR 2357738A1
Authority
FR
France
Prior art keywords
combustion chamber
air
speeds
gas turbine
air streams
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.)
Granted
Application number
FR7620707A
Other languages
French (fr)
Other versions
FR2357738B1 (en
Inventor
Jacques Emile Jules Caruel
Jean Robert Bedue
Bruno Deroide
Jean-Paul Rene Gaillac
Philippe Gastebois
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
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR7620707A priority Critical patent/FR2357738A1/en
Priority to GB28040/77A priority patent/GB1539136A/en
Priority to US05/812,636 priority patent/US4162611A/en
Priority to DE2730791A priority patent/DE2730791C2/en
Publication of FR2357738A1 publication Critical patent/FR2357738A1/en
Application granted granted Critical
Publication of FR2357738B1 publication Critical patent/FR2357738B1/fr
Granted 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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)

Abstract

The combustion chamber for gas turbine engine has combustion zones with holes for radial entry of air streams. Anther air stream enters a mixing or dilution zone. The fuel is atomised by compressed air or by evaporation and enters while entrained in a third air stream. Combustion is ensured at low turbine speeds. Primary air in the second stream is fed independently of the turbine speed and the combustion chamber is hence suited for all turbine speeds. Between fuel injection nozzles and combustion chamber floor (9, 10) is a contracted section 15) upstream of the primary zone. This contraction expands in flow direction of gases and its wall has performations (16) for inlet of air jets from fourth air stream.
FR7620707A 1976-07-07 1976-07-07 Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds Granted FR2357738A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR7620707A FR2357738A1 (en) 1976-07-07 1976-07-07 Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds
GB28040/77A GB1539136A (en) 1976-07-07 1977-07-05 Gas turbine combustion chambers
US05/812,636 US4162611A (en) 1976-07-07 1977-07-05 Combustion chamber for turbo engines
DE2730791A DE2730791C2 (en) 1976-07-07 1977-07-07 Combustion chamber for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7620707A FR2357738A1 (en) 1976-07-07 1976-07-07 Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds

Publications (2)

Publication Number Publication Date
FR2357738A1 true FR2357738A1 (en) 1978-02-03
FR2357738B1 FR2357738B1 (en) 1983-04-01

Family

ID=9175345

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7620707A Granted FR2357738A1 (en) 1976-07-07 1976-07-07 Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds

Country Status (1)

Country Link
FR (1) FR2357738A1 (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2433710A1 (en) * 1978-08-19 1980-03-14 Rolls Royce IMPROVED COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
FR2446442A1 (en) * 1979-01-15 1980-08-08 United Technologies Corp BURNER SYSTEM AND METHOD OF USING BURNER SYSTEM
FR2451998A1 (en) * 1979-03-22 1980-10-17 Rolls Royce COMBUSTION CHAMBER FOR A SPECIALLY REFRIGERATED GAS TURBINE ENGINE
US4696157A (en) * 1985-10-18 1987-09-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Fuel and air injection system for a turbojet engine
US4754600A (en) * 1986-03-20 1988-07-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Axial-centripetal swirler injection apparatus
EP0182687B1 (en) * 1984-10-30 1988-08-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Injection system with a variable geometry
FR2698157A1 (en) * 1992-11-18 1994-05-20 Snecma Aerodynamic combustion chamber injection system.
FR2829707A1 (en) * 2001-09-19 2003-03-21 Air Liquide Mixing at least two gases which are prone to react in a mixer, comprises setting specific retention time and standard deviation of retention time in mixer
US20230072621A1 (en) * 2021-09-06 2023-03-09 Rolls-Royce Plc Controlling soot

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2433710A1 (en) * 1978-08-19 1980-03-14 Rolls Royce IMPROVED COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
FR2446442A1 (en) * 1979-01-15 1980-08-08 United Technologies Corp BURNER SYSTEM AND METHOD OF USING BURNER SYSTEM
FR2451998A1 (en) * 1979-03-22 1980-10-17 Rolls Royce COMBUSTION CHAMBER FOR A SPECIALLY REFRIGERATED GAS TURBINE ENGINE
EP0182687B1 (en) * 1984-10-30 1988-08-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Injection system with a variable geometry
US4696157A (en) * 1985-10-18 1987-09-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Fuel and air injection system for a turbojet engine
US4754600A (en) * 1986-03-20 1988-07-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Axial-centripetal swirler injection apparatus
FR2698157A1 (en) * 1992-11-18 1994-05-20 Snecma Aerodynamic combustion chamber injection system.
EP0598662A1 (en) * 1992-11-18 1994-05-25 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aerodynamic injection system for a combustion chamber
FR2829707A1 (en) * 2001-09-19 2003-03-21 Air Liquide Mixing at least two gases which are prone to react in a mixer, comprises setting specific retention time and standard deviation of retention time in mixer
WO2003024580A1 (en) * 2001-09-19 2003-03-27 L'air Liquide, Societe Anonyme A Directoire Et Conseil De Surveillance Pour L'etude Et L'exploitation Des Procedes Georges Claude Method and device for mixing two reactant gases
US20230072621A1 (en) * 2021-09-06 2023-03-09 Rolls-Royce Plc Controlling soot

Also Published As

Publication number Publication date
FR2357738B1 (en) 1983-04-01

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Legal Events

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ST Notification of lapse
ST Notification of lapse
ST Notification of lapse