GB1283827A - Improvements in or relating to combustion apparatus - Google Patents

Improvements in or relating to combustion apparatus

Info

Publication number
GB1283827A
GB1283827A GB4597770A GB4597770A GB1283827A GB 1283827 A GB1283827 A GB 1283827A GB 4597770 A GB4597770 A GB 4597770A GB 4597770 A GB4597770 A GB 4597770A GB 1283827 A GB1283827 A GB 1283827A
Authority
GB
United Kingdom
Prior art keywords
annular
vanes
combustion chamber
flow
passage
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
GB4597770A
Inventor
Allan Knight Chesters
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB4597770A priority Critical patent/GB1283827A/en
Publication of GB1283827A publication Critical patent/GB1283827A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air

Abstract

1283827 Combustion apparatus such as for gas turbine engines ROLLS-ROYCE Ltd 26 Sept 1970 45977/70 Heading F1L A combustion chamber comprises an annular intake for flow of primary air into the combustion chamber, the annular intake being divided by a deflecting member into at least two annular ducts, one duct being for the main flow of primary air into the combustion chamber whilst the other duct is for flow of air which is attached to the inner surface of the deflecting plate by the coanda effect when the combustion chamber is in operation. The flame tube shown in Fig. 1 comprises a cylindical portion 12 and a flared portion 10, also a fuel injector 20 which is mounted within ring member 18, an annular intake 22 being defined between the parts 12 and 18. A deflector member 14 is disposed between the parts to define two annular intake passages 24, 26, vanes 16 being disposed in the passage 24 and vanes 21 in the passage 26, the vanes 16 not producing swirl in the air-flow but the vanes 21 may produce swirl. The deflector member 14 comprises an upstream cylindical portion 14a and a downstream bellmouth portion 14b, the radius of curvature of which is R 1 . The width of the annular passage 26 is t and it is stated that the ratio t/R 1 must be between 1/5 and 1/13. Also that diameter A must be greater than diameter B and that angle # must be equal to or greater than angle #, the diameters and angles being as shown. The invention may be applied in the case of an annular flame tube.
GB4597770A 1970-09-26 1970-09-26 Improvements in or relating to combustion apparatus Expired GB1283827A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4597770A GB1283827A (en) 1970-09-26 1970-09-26 Improvements in or relating to combustion apparatus

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
GB4597770A GB1283827A (en) 1970-09-26 1970-09-26 Improvements in or relating to combustion apparatus
DE19712147113 DE2147113C3 (en) 1970-09-26 1971-09-21 Flame tube for gas turbine jet engines
JP7495871A JPS5310208B1 (en) 1970-09-26 1971-09-25
FR7134690A FR2108013B1 (en) 1970-09-26 1971-09-27
US3793828D US3793828A (en) 1970-09-26 1971-09-27 Combustion system deflector plate

Publications (1)

Publication Number Publication Date
GB1283827A true GB1283827A (en) 1972-08-02

Family

ID=10439331

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4597770A Expired GB1283827A (en) 1970-09-26 1970-09-26 Improvements in or relating to combustion apparatus

Country Status (5)

Country Link
US (1) US3793828A (en)
JP (1) JPS5310208B1 (en)
DE (1) DE2147113C3 (en)
FR (1) FR2108013B1 (en)
GB (1) GB1283827A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5737921A (en) * 1994-04-20 1998-04-14 Rolls-Royce Plc Gas turbine engine fuel injector

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4173118A (en) * 1974-08-27 1979-11-06 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus employing staged combustion
DE3564024D1 (en) * 1984-02-29 1988-09-01 Lucas Ind Plc Combustion equipment
CZ217496A3 (en) * 1994-01-24 1997-02-12 Siemens Ag Process of combustion fuel in compressed air
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
RU2406034C2 (en) * 2006-02-28 2010-12-10 Сименс Акциенгезелльшафт Gas turbine burner and operating method of gas turbine burner

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA593892A (en) * 1960-03-08 Joseph Lucas (Industries) Limited Liquid fuel combustion chambers
CA607893A (en) * 1960-11-01 S. Massey Bernard Flame tubes for use in combustion systems of gas turbine engines
GB694448A (en) * 1950-10-09 1953-07-22 Rolls Royce Improvements in or relating to gas-turbine engines
US2602292A (en) * 1951-03-31 1952-07-08 Gen Electric Fuel-air mixing device
US2958194A (en) * 1951-09-24 1960-11-01 Power Jets Res & Dev Ltd Cooled flame tube
GB723830A (en) * 1952-09-13 1955-02-09 Armstrong Siddeley Motors Ltd Flame stabilising device
GB741836A (en) * 1953-03-05 1955-12-14 Lucas Industries Ltd Combustion chambers for jet-propulsion engines, gas turbines or other prime movers
US2807933A (en) * 1954-04-01 1957-10-01 Martin Peter Combustion chambers
US2965303A (en) * 1959-03-30 1960-12-20 United Aircraft Corp Coolant injection in a fuel nozzle
GB1031184A (en) * 1964-02-26 1966-06-02 Arthur Henry Lefebvre An improved fuel injection system for gas turbine engines
US3703259A (en) * 1971-05-03 1972-11-21 Gen Electric Air blast fuel atomizer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5737921A (en) * 1994-04-20 1998-04-14 Rolls-Royce Plc Gas turbine engine fuel injector

Also Published As

Publication number Publication date
US3793828A (en) 1974-02-26
DE2147113A1 (en) 1972-03-30
JPS5310208B1 (en) 1978-04-12
DE2147113B2 (en) 1979-09-06
FR2108013A1 (en) 1972-05-12
FR2108013B1 (en) 1977-08-05
DE2147113C3 (en) 1980-04-30

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Legal Events

Date Code Title Description
PS Patent sealed
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee