GB757871A - Improvements in and relating to combustion chambers - Google Patents

Improvements in and relating to combustion chambers

Info

Publication number
GB757871A
GB757871A GB35434/54A GB3543454A GB757871A GB 757871 A GB757871 A GB 757871A GB 35434/54 A GB35434/54 A GB 35434/54A GB 3543454 A GB3543454 A GB 3543454A GB 757871 A GB757871 A GB 757871A
Authority
GB
United Kingdom
Prior art keywords
fuel
air
dome
flame tube
flow
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
GB35434/54A
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 GB757871A publication Critical patent/GB757871A/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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

757,871. Generating combustion products under pressure. GENERAL ELECTRIC CO. Dec. 7, 1954 [Dec. 7, 1953], No. 35434/54. Class 51(1). In an air jacketed type of combustion chamber, such as a combustion chamber of a gas turbine engine, the flame tube 11 has a dome-shaped closed end portion 14 and inclined vanes 18 are inserted in an annular passageway 17 formed between the overlapping ends of the dome portion 14 and a cylindrical main portion of the flame tube for directing air from the space 16 between the outer wall and the flame tube into the dome-shaped portion so as to provide a swirling and reversing. vortex flow. Means 15 are provided to inject fuel into or near the flow. In Fig. 1 the air flow produced is indicated by the arrows 20, 21, 22, 23, 24, 28. Secondary and dilution air enters through orifices 19 in the flame tube wall, the air flow being indicated by the arrows, 25, 26, 27. Ignition means are disposed in the zone of the reversed flow of fuel and air mixture indicated at 24. In a second embodiment additional fuel is injected through two fuel injectors which inject through diametrically-opposed air inlet orifices in the flame tube wall, semi-circular air deflectors being disposed on the downstream sides of the orifices around the injectors. In another embodiment, the fuel injector 15 at the centre of the dome-shaped portion is replaced by pilot burner or flame igniter. In Fig. 6 the fuel injector in the end dome is omitted, the whole of the fuel being supplied through the two radially-disposed fuel injectors 15<SP>1</SP>.
GB35434/54A 1953-12-07 1954-12-07 Improvements in and relating to combustion chambers Expired GB757871A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US757871XA 1953-12-07 1953-12-07

Publications (1)

Publication Number Publication Date
GB757871A true GB757871A (en) 1956-09-26

Family

ID=22127984

Family Applications (1)

Application Number Title Priority Date Filing Date
GB35434/54A Expired GB757871A (en) 1953-12-07 1954-12-07 Improvements in and relating to combustion chambers

Country Status (1)

Country Link
GB (1) GB757871A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1097213B (en) * 1958-05-22 1961-01-12 Rolls Royce Incinerator for gas turbine engines
DE1102491B (en) * 1957-10-19 1961-03-16 Bristol Siddeley Engines Ltd Combustion device for a gas turbine engine
US3203168A (en) * 1962-05-21 1965-08-31 Oxy Catalyst Inc Method and apparatus for improving the purification of exhaust gases from an internal combustion engine
DE1601674B1 (en) * 1966-08-31 1971-09-16 United Aircraft Corp COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
US20160223196A1 (en) * 2015-02-02 2016-08-04 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Crude Oil Spray Combustor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1102491B (en) * 1957-10-19 1961-03-16 Bristol Siddeley Engines Ltd Combustion device for a gas turbine engine
DE1097213B (en) * 1958-05-22 1961-01-12 Rolls Royce Incinerator for gas turbine engines
US3203168A (en) * 1962-05-21 1965-08-31 Oxy Catalyst Inc Method and apparatus for improving the purification of exhaust gases from an internal combustion engine
DE1601674B1 (en) * 1966-08-31 1971-09-16 United Aircraft Corp COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
US20160223196A1 (en) * 2015-02-02 2016-08-04 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Crude Oil Spray Combustor

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