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FR2422035A1 - AIR FILM COOLED COMBUSTION SYSTEM - Google Patents

AIR FILM COOLED COMBUSTION SYSTEM

Info

Publication number
FR2422035A1
FR2422035A1 FR7908319A FR7908319A FR2422035A1 FR 2422035 A1 FR2422035 A1 FR 2422035A1 FR 7908319 A FR7908319 A FR 7908319A FR 7908319 A FR7908319 A FR 7908319A FR 2422035 A1 FR2422035 A1 FR 2422035A1
Authority
FR
France
Prior art keywords
air film
air
combustion system
cooled combustion
film cooled
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Withdrawn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
FR7908319A
Other languages
French (fr)
Inventor
Milton James Kenworty
Howard Lewis Foltz
Robert Carl King
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 FR2422035A1 publication Critical patent/FR2422035A1/en
Withdrawn legal-status Critical Current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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Separation Using Semi-Permeable Membranes (AREA)
  • Gas Burners (AREA)

Abstract

Dispositif évitant un décollement du film d'air de la paroi à refroidir. Il comprend des tubes courts 26 traversant les parois 13, 14 de la chambre de combustion et destinés à introduire de l'air de dilution dans cette chambre et des moyens pour refroidir les parois en aval de chaque tube court, ces moyens étant formés par un intervalle ménagé entre le côté aval du tube court et la paroi 14 et des éléments de passage d'air 24 pour introduire un écoulement d'air de refroidissement Application aux moteurs à turbine à gaz.Device preventing separation of the air film from the wall to be cooled. It comprises short tubes 26 passing through the walls 13, 14 of the combustion chamber and intended to introduce dilution air into this chamber and means for cooling the walls downstream of each short tube, these means being formed by a gap formed between the downstream side of the short tube and the wall 14 and air passage elements 24 to introduce a flow of cooling air. Application to gas turbine engines.

FR7908319A 1978-04-04 1979-04-03 AIR FILM COOLED COMBUSTION SYSTEM Withdrawn FR2422035A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US89322178A 1978-04-04 1978-04-04

Publications (1)

Publication Number Publication Date
FR2422035A1 true FR2422035A1 (en) 1979-11-02

Family

ID=25401226

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7908319A Withdrawn FR2422035A1 (en) 1978-04-04 1979-04-03 AIR FILM COOLED COMBUSTION SYSTEM

Country Status (5)

Country Link
JP (1) JPS54158729A (en)
DE (1) DE2913223A1 (en)
FR (1) FR2422035A1 (en)
GB (1) GB2017827B (en)
IT (1) IT1163665B (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2404110A1 (en) * 1977-09-23 1979-04-20 United Technologies Corp COOLING JACKET FOR THE COMBUSTION CHAMBER OF A GAS TURBINE ENGINE
EP0187731A1 (en) * 1985-01-07 1986-07-16 United Technologies Corporation Combustion liner for a gas turbine engine
EP0248731A1 (en) * 1986-06-04 1987-12-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall
CN114135901A (en) * 2021-11-08 2022-03-04 中国航发四川燃气涡轮研究院 Ablation-proof flame tube large-hole jet sleeve

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4302941A (en) * 1980-04-02 1981-12-01 United Technologies Corporation Combuster liner construction for gas turbine engine
JPS5932862U (en) * 1982-08-27 1984-02-29 三菱重工業株式会社 gas turbine combustor
DE3535443C1 (en) * 1985-10-04 1986-11-20 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Combustion chamber for a gas turbine engine, especially an annular combustion chamber, with at least one air supply bushing
US5187937A (en) * 1988-06-22 1993-02-23 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
FR2714152B1 (en) * 1993-12-22 1996-01-19 Snecma Device for fixing a thermal protection tile in a combustion chamber.
DE19508110A1 (en) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Combustion chamber of gas turbine
DE19547703C2 (en) * 1995-12-20 1999-02-18 Mtu Muenchen Gmbh Combustion chamber, in particular ring combustion chamber, for gas turbine engines
GB9919981D0 (en) * 1999-08-24 1999-10-27 Rolls Royce Plc Combustion apparatus
FR2826102B1 (en) * 2001-06-19 2004-01-02 Snecma Moteurs IMPROVEMENTS TO GAS TURBINE COMBUSTION CHAMBERS
US8387396B2 (en) * 2007-01-09 2013-03-05 General Electric Company Airfoil, sleeve, and method for assembling a combustor assembly
US20130074471A1 (en) * 2011-09-22 2013-03-28 General Electric Company Turbine combustor and method for temperature control and damping a portion of a combustor
GB201116608D0 (en) * 2011-09-27 2011-11-09 Rolls Royce Plc A method of operating a combustion chamber
US20130283806A1 (en) * 2012-04-26 2013-10-31 General Electric Company Combustor and a method for repairing the combustor
EP3591292B1 (en) * 2013-11-04 2022-01-05 Raytheon Technologies Corporation Quench aperture body for a turbine engine combustor
WO2015085069A1 (en) 2013-12-06 2015-06-11 United Technologies Corporation Combustor quench aperture cooling
EP3077641B1 (en) * 2013-12-06 2020-02-12 United Technologies Corporation Cooling an igniter aperture body of a combustor wall
US10443848B2 (en) * 2014-04-02 2019-10-15 United Technologies Corporation Grommet assembly and method of design
CN105091030A (en) * 2014-05-23 2015-11-25 中航商用航空发动机有限责任公司 Sleeve for flame tube and flame tube
US9976743B2 (en) 2014-07-03 2018-05-22 United Technologies Corporation Dilution hole assembly
US20160178199A1 (en) * 2014-12-17 2016-06-23 United Technologies Corporation Combustor dilution hole active heat transfer control apparatus and system
EP3037725B1 (en) * 2014-12-22 2018-10-31 Ansaldo Energia Switzerland AG Mixer for admixing a dilution air to the hot gas flow
US20160209035A1 (en) * 2015-01-16 2016-07-21 Solar Turbines Incorporated Combustion hole insert with integrated film restarter
US10094564B2 (en) * 2015-04-17 2018-10-09 Pratt & Whitney Canada Corp. Combustor dilution hole cooling system
FR3055950B1 (en) * 2016-09-14 2019-09-27 Safran Helicopter Engines COMBUSTION CHAMBER FOR TURBOMACHINE COMPRISING MEANS FOR IMPROVING THE COOLING OF AN ANNULAR WALL IN THE WAKE OF AN OBSTACLE
US11015529B2 (en) 2016-12-23 2021-05-25 General Electric Company Feature based cooling using in wall contoured cooling passage
FR3081211B1 (en) 2018-05-16 2021-02-26 Safran Aircraft Engines TURBOMACHINE COMBUSTION CHAMBER SET
US11022308B2 (en) 2018-05-31 2021-06-01 Honeywell International Inc. Double wall combustors with strain isolated inserts
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11371701B1 (en) * 2021-02-03 2022-06-28 General Electric Company Combustor for a gas turbine engine
US11774098B2 (en) * 2021-06-07 2023-10-03 General Electric Company Combustor for a gas turbine engine
US12152777B2 (en) * 2021-06-07 2024-11-26 General Electric Company Combustor for a gas turbine engine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB665155A (en) * 1949-03-30 1952-01-16 Lucas Ltd Joseph Improvements relating to combustion chambers for prime movers
FR1273296A (en) * 1960-11-10 1961-10-06 Rolls Royce Combustion equipment for gas turbo-engines
FR1277573A (en) * 1961-01-10 1961-12-01 Lucas Industries Ltd Combustion chamber for internal combustion engine
GB887639A (en) * 1959-11-20 1962-01-24 Rolls Royce Combustion equipment for a gas turbine engine
FR2013864A1 (en) * 1968-07-27 1970-04-10 Leyland Gas Turbines
FR2023415A1 (en) * 1968-11-15 1970-08-21 Rolls Royce
FR2055720A1 (en) * 1969-08-01 1971-04-30 Snecma
US3899882A (en) * 1974-03-27 1975-08-19 Westinghouse Electric Corp Gas turbine combustor basket cooling
FR2341742A1 (en) * 1976-02-19 1977-09-16 Mtu Muenchen Gmbh COMBUSTION CHAMBER FOR GAS TURBINE REACTION ENGINES

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB665155A (en) * 1949-03-30 1952-01-16 Lucas Ltd Joseph Improvements relating to combustion chambers for prime movers
GB887639A (en) * 1959-11-20 1962-01-24 Rolls Royce Combustion equipment for a gas turbine engine
FR1273296A (en) * 1960-11-10 1961-10-06 Rolls Royce Combustion equipment for gas turbo-engines
FR1277573A (en) * 1961-01-10 1961-12-01 Lucas Industries Ltd Combustion chamber for internal combustion engine
FR2013864A1 (en) * 1968-07-27 1970-04-10 Leyland Gas Turbines
FR2023415A1 (en) * 1968-11-15 1970-08-21 Rolls Royce
FR2055720A1 (en) * 1969-08-01 1971-04-30 Snecma
US3899882A (en) * 1974-03-27 1975-08-19 Westinghouse Electric Corp Gas turbine combustor basket cooling
FR2341742A1 (en) * 1976-02-19 1977-09-16 Mtu Muenchen Gmbh COMBUSTION CHAMBER FOR GAS TURBINE REACTION ENGINES

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2404110A1 (en) * 1977-09-23 1979-04-20 United Technologies Corp COOLING JACKET FOR THE COMBUSTION CHAMBER OF A GAS TURBINE ENGINE
EP0187731A1 (en) * 1985-01-07 1986-07-16 United Technologies Corporation Combustion liner for a gas turbine engine
EP0248731A1 (en) * 1986-06-04 1987-12-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall
FR2599821A1 (en) * 1986-06-04 1987-12-11 Snecma COMBUSTION CHAMBER FOR TURBOMACHINES WITH MIXING ORIFICES ENSURING THE POSITIONING OF THE HOT WALL ON THE COLD WALL
US4805397A (en) * 1986-06-04 1989-02-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Combustion chamber structure for a turbojet engine
CN114135901A (en) * 2021-11-08 2022-03-04 中国航发四川燃气涡轮研究院 Ablation-proof flame tube large-hole jet sleeve

Also Published As

Publication number Publication date
IT7921515A0 (en) 1979-04-03
GB2017827A (en) 1979-10-10
IT1163665B (en) 1987-04-08
JPS54158729A (en) 1979-12-14
DE2913223A1 (en) 1979-10-11
GB2017827B (en) 1983-02-02

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