GB2017827A - Combustor liner cooling - Google Patents

Combustor liner cooling

Info

Publication number
GB2017827A
GB2017827A GB7910910A GB7910910A GB2017827A GB 2017827 A GB2017827 A GB 2017827A GB 7910910 A GB7910910 A GB 7910910A GB 7910910 A GB7910910 A GB 7910910A GB 2017827 A GB2017827 A GB 2017827A
Authority
GB
United Kingdom
Prior art keywords
combustor liner
air
liner
liner cooling
downstream side
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
GB7910910A
Other versions
GB2017827B (en
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 GB2017827A publication Critical patent/GB2017827A/en
Application granted granted Critical
Publication of GB2017827B publication Critical patent/GB2017827B/en
Expired 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Spray-Type Burners (AREA)
  • Gas Burners (AREA)
  • Separation Using Semi-Permeable Membranes (AREA)

Abstract

The flow of film cooling air on the inner surface of a combustor liner is re-established on the downstream side of air dilution holes by the introduction of cooling air, e.g. through apertures 51, to a gap provided between the liner wall 40 and the downstream side of the dilution hole thimble 48. The air is diverted and directed along the liner inner surface by a lip 36 protruding downstream from the thimble and across the gap. <IMAGE>
GB7910910A 1978-04-04 1979-03-29 Combustor liner cooling Expired GB2017827B (en)

Applications Claiming Priority (1)

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

Publications (2)

Publication Number Publication Date
GB2017827A true GB2017827A (en) 1979-10-10
GB2017827B GB2017827B (en) 1983-02-02

Family

ID=25401226

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7910910A Expired GB2017827B (en) 1978-04-04 1979-03-29 Combustor liner cooling

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 (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2479901A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERNAL COMBUSTION CHAMBER LINING FOR A GAS TURBINE
EP0348097A1 (en) * 1988-06-22 1989-12-27 Secretary Of State For Defence In Her Britannic Majesty's Gov. Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
FR2714152A1 (en) * 1993-12-22 1995-06-23 Snecma Device for fixing a thermal protection tile in a combustion chamber.
EP0780638A3 (en) * 1995-12-20 1998-06-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Combustion chamber for gasturbine
GB2353589A (en) * 1999-08-24 2001-02-28 Rolls Royce Plc Combustor wall arrangement with air intake port
GB2377487A (en) * 2001-06-19 2003-01-15 Snecma Moteurs Air inlet bushes used in a combustion chamber of a gas turbine
CN101220965B (en) * 2007-01-09 2012-05-02 通用电气公司 Airfoil, sleeve, and method for assembling a combustor assembly
CN103075744A (en) * 2011-09-22 2013-05-01 通用电气公司 Turbine combustor and method for temperature control and damping a portion of a combustor
WO2015085069A1 (en) 2013-12-06 2015-06-11 United Technologies Corporation Combustor quench aperture cooling
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
US20160178199A1 (en) * 2014-12-17 2016-06-23 United Technologies Corporation Combustor dilution hole active heat transfer control apparatus and system
EP3037725A1 (en) * 2014-12-22 2016-06-29 Alstom Technology Ltd 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
EP3077641A1 (en) * 2013-12-06 2016-10-12 United Technologies Corporation Cooling an igniter aperture body of a combustor wall
US20160305663A1 (en) * 2015-04-17 2016-10-20 Pratt & Whitney Canada Corp. Gas turbine engine combustor
EP3066387A4 (en) * 2013-11-04 2016-11-30 United Technologies Corp Quench aperture body for a turbine engine combustor
EP2574846A3 (en) * 2011-09-27 2017-10-18 Rolls-Royce plc A method of operating a combustion chamber
FR3055950A1 (en) * 2016-09-14 2018-03-16 Safran Helicopter Engines COMBUSTION CHAMBER FOR TURBOMACHINE COMPRISING MEANS FOR IMPROVING THE COOLING OF AN ANNULAR WALL IN THE WAKE OF AN OBSTACLE
EP3282190A3 (en) * 2014-07-03 2018-04-18 United Technologies Corporation Dilution hole assembly
US10443848B2 (en) * 2014-04-02 2019-10-15 United Technologies Corporation Grommet assembly and method of design
EP3569929A1 (en) * 2018-05-16 2019-11-20 Safran Aircraft Engines Assembly for a turbine engine combustion chamber
EP3575686A1 (en) * 2018-05-31 2019-12-04 Honeywell International Inc. Double wall combustors with strain isolated inserts
US11015529B2 (en) 2016-12-23 2021-05-25 General Electric Company Feature based cooling using in wall contoured cooling passage
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
CN114857618A (en) * 2021-02-03 2022-08-05 通用电气公司 Combustor for a gas turbine engine
CN115507387A (en) * 2021-06-07 2022-12-23 通用电气公司 Combustor for a gas turbine engine
CN115507384A (en) * 2021-06-07 2022-12-23 通用电气公司 Combustor for a gas turbine engine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
JPS5932862U (en) * 1982-08-27 1984-02-29 三菱重工業株式会社 gas turbine combustor
US4622821A (en) * 1985-01-07 1986-11-18 United Technologies Corporation Combustion liner for a gas turbine engine
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
FR2599821B1 (en) * 1986-06-04 1988-09-02 Snecma COMBUSTION CHAMBER FOR TURBOMACHINES WITH MIXING HOLES PROVIDING THE POSITIONING OF THE HOT WALL ON THE COLD WALL
DE19508110A1 (en) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Combustion chamber of gas turbine
US20130283806A1 (en) * 2012-04-26 2013-10-31 General Electric Company Combustor and a method for repairing the combustor
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

Family Cites Families (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
NL257968A (en) * 1959-11-20
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
GB1240009A (en) * 1968-07-27 1971-07-21 Leyland Gas Turbines Ltd Flame tube
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
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
DE2606704A1 (en) * 1976-02-19 1977-09-01 Motoren Turbinen Union COMBUSTION CHAMBER FOR GAS TURBINE ENGINES

Cited By (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2479901A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERNAL COMBUSTION CHAMBER LINING FOR A GAS TURBINE
EP0348097A1 (en) * 1988-06-22 1989-12-27 Secretary Of State For Defence In Her Britannic Majesty's Gov. Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
WO1989012788A1 (en) * 1988-06-22 1989-12-28 The Secretary Of State For Defence In Her Britanni Gas turbine engine combustors
GB2238864A (en) * 1988-06-22 1991-06-12 Secr Defence Gas turbine engine combustors
GB2238864B (en) * 1988-06-22 1992-04-22 Secr Defence Gas turbine engine combustors
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
FR2714152A1 (en) * 1993-12-22 1995-06-23 Snecma Device for fixing a thermal protection tile in a combustion chamber.
US5501071A (en) * 1993-12-22 1996-03-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fixing arrangement for a thermal protection tile in a combustion chamber
EP0780638A3 (en) * 1995-12-20 1998-06-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Combustion chamber for gasturbine
GB2353589A (en) * 1999-08-24 2001-02-28 Rolls Royce Plc Combustor wall arrangement with air intake port
GB2377487A (en) * 2001-06-19 2003-01-15 Snecma Moteurs Air inlet bushes used in a combustion chamber of a gas turbine
GB2377487B (en) * 2001-06-19 2005-03-16 Snecma Moteurs Improvements to gas turbine combustion chambers
CN101220965B (en) * 2007-01-09 2012-05-02 通用电气公司 Airfoil, sleeve, and method for assembling a combustor assembly
CN103075744A (en) * 2011-09-22 2013-05-01 通用电气公司 Turbine combustor and method for temperature control and damping a portion of a combustor
EP2574846A3 (en) * 2011-09-27 2017-10-18 Rolls-Royce plc A method of operating a combustion chamber
EP3066387A4 (en) * 2013-11-04 2016-11-30 United Technologies Corp Quench aperture body for a turbine engine combustor
US10571125B2 (en) 2013-11-04 2020-02-25 United Technologies Corporation Quench aperture body for a turbine engine combustor
EP3591292A1 (en) * 2013-11-04 2020-01-08 United Technologies Corporation Quench aperture body for a turbine engine combustor
US10378768B2 (en) 2013-12-06 2019-08-13 United Technologies Corporation Combustor quench aperture cooling
EP3077641A1 (en) * 2013-12-06 2016-10-12 United Technologies Corporation Cooling an igniter aperture body of a combustor wall
US10968829B2 (en) 2013-12-06 2021-04-06 Raytheon Technologies Corporation Cooling an igniter body of a combustor wall
EP3077640A4 (en) * 2013-12-06 2016-12-07 United Technologies Corp Combustor quench aperture cooling
EP3077641A4 (en) * 2013-12-06 2017-04-05 United Technologies Corporation Cooling an igniter aperture body of a combustor wall
WO2015085069A1 (en) 2013-12-06 2015-06-11 United Technologies Corporation Combustor quench aperture cooling
US11193672B2 (en) 2013-12-06 2021-12-07 Raytheon Technologies Corporation Combustor quench aperture cooling
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
EP3282190A3 (en) * 2014-07-03 2018-04-18 United Technologies Corporation Dilution hole assembly
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
US10323574B2 (en) 2014-12-22 2019-06-18 Ansaldo Energia Switzerland AG Mixer for admixing a dilution air to the hot gas flow
EP3037725A1 (en) * 2014-12-22 2016-06-29 Alstom Technology Ltd 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
US20160305663A1 (en) * 2015-04-17 2016-10-20 Pratt & Whitney Canada Corp. Gas turbine engine combustor
WO2018050999A1 (en) * 2016-09-14 2018-03-22 Safran Helicopter Engines Combustion chamber for turbine engine comprising means for improving the cooling of an annular wall in the wake of an obstacle
FR3055950A1 (en) * 2016-09-14 2018-03-16 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
FR3081211A1 (en) * 2018-05-16 2019-11-22 Safran Aircraft Engines ASSEMBLY FOR A TURBOMACHINE COMBUSTION CHAMBER
US11280494B2 (en) 2018-05-16 2022-03-22 Safran Aircraft Engines Assembly for a turbomachine combustion chamber
EP3569929A1 (en) * 2018-05-16 2019-11-20 Safran Aircraft Engines Assembly for a turbine engine combustion chamber
EP3575686A1 (en) * 2018-05-31 2019-12-04 Honeywell International Inc. Double wall combustors with strain isolated inserts
US11022308B2 (en) 2018-05-31 2021-06-01 Honeywell International Inc. Double wall combustors with strain isolated inserts
US11326781B2 (en) 2018-05-31 2022-05-10 Honeywell International Inc. Liner for a combustor with strain isolated inserts
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
CN114857618A (en) * 2021-02-03 2022-08-05 通用电气公司 Combustor for a gas turbine engine
CN115507384A (en) * 2021-06-07 2022-12-23 通用电气公司 Combustor for a gas turbine engine
CN115507387A (en) * 2021-06-07 2022-12-23 通用电气公司 Combustor for a gas turbine engine

Also Published As

Publication number Publication date
DE2913223A1 (en) 1979-10-11
JPS54158729A (en) 1979-12-14
FR2422035A1 (en) 1979-11-02
GB2017827B (en) 1983-02-02
IT7921515A0 (en) 1979-04-03
IT1163665B (en) 1987-04-08

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee