GB1424197A - Combustion chambers for gas turbine engines - Google Patents

Combustion chambers for gas turbine engines

Info

Publication number
GB1424197A
GB1424197A GB2715472A GB2715472A GB1424197A GB 1424197 A GB1424197 A GB 1424197A GB 2715472 A GB2715472 A GB 2715472A GB 2715472 A GB2715472 A GB 2715472A GB 1424197 A GB1424197 A GB 1424197A
Authority
GB
United Kingdom
Prior art keywords
air
flame tube
air inlet
towards
disposed
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
Application number
GB2715472A
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
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 Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to GB2715472A priority Critical patent/GB1424197A/en
Priority to IT50516/73A priority patent/IT989653B/en
Priority to DE2329367A priority patent/DE2329367C2/en
Priority to JP6529173A priority patent/JPS5411844B2/ja
Priority to US368576A priority patent/US3869864A/en
Priority to FR7321313A priority patent/FR2188055B1/fr
Publication of GB1424197A publication Critical patent/GB1424197A/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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow

Abstract

1424197 Gas turbine engine combustion equipment LUCAS INDUSTRIES Ltd 31 May 1973 [9 June 1972] 27154/72 Heading F1L The invention relates to combustion chambers for gas turbine engines of the kind comprising a flame tube disposed within an outer casing and to means for establishing and maintaining a desired air-flow pattern. The combustion equipment shown comprises an annular flame tube 3 of toroidal form disposed within an outer annular air casing 2, the equipment being of the reverse flow type with the air inlet at 4 and the combustion gas outlet at 6. The flame tube outer wall is formed in two parts with a corrugated member 12 disposed therebetween to define a series of air inlet openings 9 through which air flows towards the fuel injection device 5 towards an annular baffle member 13 disposed transversely within the flame tube. The baffle 13 is of castellated form having a series of recesses 14 and a deflector 15 is disposed at the base of each recess and projects normal to the baffle towards the air inlet openings 9. The inner wall of the flame tube is similarly formed in two parts with a corrugated member 12 disposed therebetween to define a series of air inlet openings 9 through which air flows away from the fuel injection device 5 towards an annular baffle member 13 which is similar to the baffle member 13 associated with the outer wall. The flame tube walls are also formed with air inlet openings 7 and 8 which are associated with baffles 10 and 11 so that air flowing through the openings 7 and 8 is deflected by the baffles to flow in directions away from and towards the fuel injector, respectively. A further air inlet opening 16 is provided in the outer wall adjacent the baffle member 13 through which air is directed radially inwardly.
GB2715472A 1972-06-09 1972-06-09 Combustion chambers for gas turbine engines Expired GB1424197A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
GB2715472A GB1424197A (en) 1972-06-09 1972-06-09 Combustion chambers for gas turbine engines
IT50516/73A IT989653B (en) 1972-06-09 1973-06-07 COMBUSTION CHAMBER FOR GAS TURBINE ENGINES
DE2329367A DE2329367C2 (en) 1972-06-09 1973-06-08 Combustion chamber for gas turbine
JP6529173A JPS5411844B2 (en) 1972-06-09 1973-06-09
US368576A US3869864A (en) 1972-06-09 1973-06-11 Combustion chambers for gas turbine engines
FR7321313A FR2188055B1 (en) 1972-06-09 1973-06-12

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2715472A GB1424197A (en) 1972-06-09 1972-06-09 Combustion chambers for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1424197A true GB1424197A (en) 1976-02-11

Family

ID=10255088

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2715472A Expired GB1424197A (en) 1972-06-09 1972-06-09 Combustion chambers for gas turbine engines

Country Status (6)

Country Link
US (1) US3869864A (en)
JP (1) JPS5411844B2 (en)
DE (1) DE2329367C2 (en)
FR (1) FR2188055B1 (en)
GB (1) GB1424197A (en)
IT (1) IT989653B (en)

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
JPS5638389Y2 (en) * 1976-12-09 1981-09-08
GB1571213A (en) * 1977-01-28 1980-07-09 Kainov G Combustion chamber for gas turbine engine
DE2723546A1 (en) * 1977-05-25 1978-11-30 Motoren Turbinen Union COMBUSTION CHAMBER, IN PARTICULAR REVERSAL COMBUSTION CHAMBER FOR GAS TURBINE ENGINES
DE2728399C2 (en) * 1977-06-24 1982-04-22 Brown, Boveri & Cie Ag, 6800 Mannheim Combustion chamber for a gas turbine
US4195476A (en) * 1978-04-27 1980-04-01 General Motors Corporation Combustor construction
US4361010A (en) * 1980-04-02 1982-11-30 United Technologies Corporation Combustor liner construction
US4765136A (en) * 1985-11-25 1988-08-23 United Technologies Corporation Gas turbine engine augmentor
US4928479A (en) * 1987-12-28 1990-05-29 Sundstrand Corporation Annular combustor with tangential cooling air injection
US4944152A (en) * 1988-10-11 1990-07-31 Sundstrand Corporation Augmented turbine combustor cooling
US4949545A (en) * 1988-12-12 1990-08-21 Sundstrand Corporation Turbine wheel and nozzle cooling
US5109671A (en) * 1989-12-05 1992-05-05 Allied-Signal Inc. Combustion apparatus and method for a turbine engine
JPH0387059U (en) * 1989-12-11 1991-09-04
US5069033A (en) * 1989-12-21 1991-12-03 Sundstrand Corporation Radial inflow combustor
US5113647A (en) * 1989-12-22 1992-05-19 Sundstrand Corporation Gas turbine annular combustor
US5165226A (en) * 1991-08-09 1992-11-24 Pratt & Whitney Canada, Inc. Single vortex combustor arrangement
US5237813A (en) * 1992-08-21 1993-08-24 Allied-Signal Inc. Annular combustor with outer transition liner cooling
US5271220A (en) * 1992-10-16 1993-12-21 Sundstrand Corporation Combustor heat shield for a turbine containment ring
US5628193A (en) * 1994-09-16 1997-05-13 Alliedsignal Inc. Combustor-to-turbine transition assembly
US5746048A (en) * 1994-09-16 1998-05-05 Sundstrand Corporation Combustor for a gas turbine engine
US6079199A (en) * 1998-06-03 2000-06-27 Pratt & Whitney Canada Inc. Double pass air impingement and air film cooling for gas turbine combustor walls
CA2407717A1 (en) * 2000-05-01 2001-11-08 J. Michael Teets Annular combustor for use with an energy system
US6405703B1 (en) 2001-06-29 2002-06-18 Brian Sowards Internal combustion engine
US6925810B2 (en) * 2002-11-08 2005-08-09 Honeywell International, Inc. Gas turbine engine transition liner assembly and repair
US7308794B2 (en) * 2004-08-27 2007-12-18 Pratt & Whitney Canada Corp. Combustor and method of improving manufacturing accuracy thereof
DE102005008421A1 (en) * 2005-02-24 2006-08-31 Alstom Technology Ltd. Combustion chamber for a gas turbine, at a power station, has an additional air jet to give a counter flow and increase the fuel/air recirculation within the combustion zone
JP2008536333A (en) * 2005-04-13 2008-09-04 コーニング インコーポレイテッド Mode matching system for tunable external cavity lasers
US7954326B2 (en) * 2007-11-28 2011-06-07 Honeywell International Inc. Systems and methods for cooling gas turbine engine transition liners
US8640464B2 (en) * 2009-02-23 2014-02-04 Williams International Co., L.L.C. Combustion system
US8864492B2 (en) * 2011-06-23 2014-10-21 United Technologies Corporation Reverse flow combustor duct attachment
US9879862B2 (en) 2013-03-08 2018-01-30 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
US20150323185A1 (en) 2014-05-07 2015-11-12 General Electric Compamy Turbine engine and method of assembling thereof
US11674445B2 (en) * 2021-08-30 2023-06-13 Collins Engine Nozzles, Inc. Cooling for continuous ignition devices
US11674446B2 (en) * 2021-08-30 2023-06-13 Collins Engine Nozzles, Inc. Cooling for surface ignitors in torch ignition devices
US20230296250A1 (en) * 2022-03-21 2023-09-21 General Electric Company Turbine engine combustor and combustor liner

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2531810A (en) * 1946-06-05 1950-11-28 Kellogg M W Co Air inlet arrangement for combustion chamber flame tubes
BE507258A (en) * 1950-12-02
US3333414A (en) * 1965-10-13 1967-08-01 United Aircraft Canada Aerodynamic-flow reverser and smoother
GB1289523A (en) * 1969-03-17 1972-09-20
US3613360A (en) * 1969-10-30 1971-10-19 Garrett Corp Combustion chamber construction
US3653207A (en) * 1970-07-08 1972-04-04 Gen Electric High fuel injection density combustion chamber for a gas turbine engine
US3671171A (en) * 1970-11-27 1972-06-20 Avco Corp Annular combustors

Also Published As

Publication number Publication date
JPS5411844B2 (en) 1979-05-18
DE2329367C2 (en) 1981-12-24
FR2188055B1 (en) 1976-09-17
IT989653B (en) 1975-06-10
FR2188055A1 (en) 1974-01-18
JPS4949012A (en) 1974-05-13
DE2329367A1 (en) 1973-12-20
US3869864A (en) 1975-03-11

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee