GB1357533A - Combustion equipment for gas turbine engines - Google Patents

Combustion equipment for gas turbine engines

Info

Publication number
GB1357533A
GB1357533A GB4351070A GB4351070A GB1357533A GB 1357533 A GB1357533 A GB 1357533A GB 4351070 A GB4351070 A GB 4351070A GB 4351070 A GB4351070 A GB 4351070A GB 1357533 A GB1357533 A GB 1357533A
Authority
GB
United Kingdom
Prior art keywords
air
fuel
upstream
directed
toroidal
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
GB4351070A
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
Joseph 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, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to GB4351070A priority Critical patent/GB1357533A/en
Priority to US00196160A priority patent/US3820324A/en
Priority to FR7141098A priority patent/FR2160272B1/fr
Priority to DE2157181A priority patent/DE2157181C3/en
Publication of GB1357533A publication Critical patent/GB1357533A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • 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
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

Abstract

1357533 Combustion equipment for gas turbine engines JOSEPH LUCAS (INDUSTRIES) Ltd 18 Oct 1971 [11 Sept 1970] 43510/70 Headings F4T TH5A2 and TH5C The invention relates to combustion equipment for a gas turbine engine of the kind comprising an annular outer casing 10 having an annular flame tube 12 disposed therein, the flame tube having radially directed air inlet openings 21 through which air flows to form upstream and downstream toroidal vortex zones 22, 23, there being means 24 to supply fuel to the vortex zones. The flame tube shown is formed with air inlet openings 18, 19, 20 which have baffles such as 18a, 19a associated therewith so that air-flow therethrough acts to enhance the vortical flows 22, 23. Further air inlet openings 27 are provided downstream of the openings 21, air being guided into the openings by means of baffles 28 projecting into the air-flow passages 14. The fuel injection means 24 comprises pairs of fuel nozzles which discharge as indicated at 25, 26, the injector 25 being a pilot fuel injector which discharges into the upstream toroidal region 22. In Fig. 2 a fuel vaporizing system is utilized comprising an air inlet duct 34 formed with a radially projecting outlet 37 through which air and vaporized fuel are discharged into the downstream toroidal region 33, and an air inlet duct 35 formed adjacent the duct 34 and terminating in upstreamdirected outlets (39), 40 through which air and vaporized fuel are directed into the upstream toroidal region 32. In a further embodiment, Fig. 5 (not shown), a vaporizing type fuel injector is again utilized being disposed centrally of the flame tube, one outlet discharging radially into the downstream toroidal region and the other discharging in an upstream direction into the upstream toroidal region. In a further embodiment Fig. 8, the fuel vaporizer 50 projects radially into the flame tube and terminates in two outlets 55, 56 directed radially outwards, a baffle 57 being disposed within the vaporizer whereby two streams of air and vaporized fuel discharge from the vaporizer, one stream being directed into the downstream toroidal vortex and the other stream being directed into the upstream toroidal vortex.
GB4351070A 1970-09-11 1970-09-11 Combustion equipment for gas turbine engines Expired GB1357533A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB4351070A GB1357533A (en) 1970-09-11 1970-09-11 Combustion equipment for gas turbine engines
US00196160A US3820324A (en) 1970-09-11 1971-11-05 Flame tubes for gas turbine engines
FR7141098A FR2160272B1 (en) 1970-09-11 1971-11-17
DE2157181A DE2157181C3 (en) 1970-09-11 1971-11-18 Combustion chamber for a gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4351070A GB1357533A (en) 1970-09-11 1970-09-11 Combustion equipment for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1357533A true GB1357533A (en) 1974-06-26

Family

ID=10429063

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4351070A Expired GB1357533A (en) 1970-09-11 1970-09-11 Combustion equipment for gas turbine engines

Country Status (4)

Country Link
US (1) US3820324A (en)
DE (1) DE2157181C3 (en)
FR (1) FR2160272B1 (en)
GB (1) GB1357533A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE30925E (en) 1977-12-14 1982-05-11 Caterpillar Tractor Co. Fuel vaporizing combustor tube
FR2510665A1 (en) * 1981-07-28 1983-02-04 Rolls Royce MIXED FUEL INJECTOR FOR A GAS TURBINE ENGINE

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4179881A (en) * 1973-02-28 1979-12-25 United Technologies Corporation Premix combustor assembly
US4271674A (en) * 1974-10-17 1981-06-09 United Technologies Corporation Premix combustor assembly
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
DE2460740C3 (en) * 1974-12-21 1980-09-18 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Combustion chamber for gas turbine engines
GB1539136A (en) * 1976-07-07 1979-01-24 Snecma Gas turbine combustion chambers
GB1575410A (en) * 1976-09-04 1980-09-24 Rolls Royce Combustion apparatus for use in gas turbine engines
GB1571213A (en) * 1977-01-28 1980-07-09 Kainov G Combustion chamber for gas turbine engine
US4903492A (en) * 1988-09-07 1990-02-27 The United States Of America As Represented By The Secretary Of The Air Force Dilution air dispensing apparatus
US5265425A (en) * 1991-09-23 1993-11-30 General Electric Company Aero-slinger combustor
EP1524473A1 (en) * 2003-10-13 2005-04-20 Siemens Aktiengesellschaft Process and device to burn fuel
WO2010096817A2 (en) 2009-02-23 2010-08-26 Williams International Co., L.L.C. Combustion system
US8776525B2 (en) * 2009-12-29 2014-07-15 Rolls-Royce North American Technologies, Inc. Gas turbine engine and combustor
WO2014149081A1 (en) * 2013-03-15 2014-09-25 Rolls-Royce Corporation Counter swirl doublet combustor
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
CN105737204B (en) * 2016-03-04 2018-01-26 武汉英康汇通电气有限公司 A kind of whirlwind burner inner liner and its turbogenerator
FR3066009B1 (en) * 2017-05-02 2020-03-06 Safran Helicopter Engines PREVAPORIZATION ROD FOR A TURBOMACHINE
FR3096761B1 (en) * 2019-05-28 2022-10-14 Safran Helicopter Engines Pre-vaporization rod, combustion assembly fitted therewith and turbomachine fitted therewith
CN116265810A (en) * 2021-12-16 2023-06-20 通用电气公司 Swirler counter dilution with shaped cooling fence
KR20230101582A (en) * 2021-12-29 2023-07-06 한화에어로스페이스 주식회사 Combustor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1130091A (en) * 1954-05-06 1957-01-30 Nat Res Dev Improvements to combustion devices
GB824306A (en) * 1956-04-25 1959-11-25 Rolls Royce Improvements in or relating to combustion equipment of gas-turbine engines
DE1097213B (en) * 1958-05-22 1961-01-12 Rolls Royce Incinerator for gas turbine engines
US3064424A (en) * 1959-09-30 1962-11-20 Gen Motors Corp Flame tube
FR1261034A (en) * 1960-06-24 1961-05-12 Method and apparatus for mixing fluids
GB1136543A (en) * 1966-02-21 1968-12-11 Rolls Royce Liquid fuel combustion apparatus for gas turbine engines
FR1470246A (en) * 1966-03-01 1967-02-17 Lucas Industries Ltd Gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE30925E (en) 1977-12-14 1982-05-11 Caterpillar Tractor Co. Fuel vaporizing combustor tube
FR2510665A1 (en) * 1981-07-28 1983-02-04 Rolls Royce MIXED FUEL INJECTOR FOR A GAS TURBINE ENGINE

Also Published As

Publication number Publication date
FR2160272B1 (en) 1975-02-21
DE2157181A1 (en) 1973-05-24
FR2160272A1 (en) 1973-06-29
US3820324A (en) 1974-06-28
DE2157181B2 (en) 1980-09-18
DE2157181C3 (en) 1981-05-07

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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