[go: up one dir, main page]

GB899213A - Combustion chambers - Google Patents

Combustion chambers

Info

Publication number
GB899213A
GB899213A GB43865/59A GB4386559A GB899213A GB 899213 A GB899213 A GB 899213A GB 43865/59 A GB43865/59 A GB 43865/59A GB 4386559 A GB4386559 A GB 4386559A GB 899213 A GB899213 A GB 899213A
Authority
GB
United Kingdom
Prior art keywords
annular
air inlet
walls
air
space
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
GB43865/59A
Inventor
Peter Henry Calder
Derek John Stansfiel Lancaster
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.)
Bristol Siddeley Engines Ltd
Original Assignee
De Havilland Engine Co 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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to GB43865/59A priority Critical patent/GB899213A/en
Publication of GB899213A publication Critical patent/GB899213A/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
    • 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
    • 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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

899,213. Generating combustion products under pressure. DE HAVILLAND ENGINE CO. Ltd. Dec. 22, 1960 [Dec. 24, 1959], No. 43865/59. Class 51 (1). An annular combustion chamber for a gas turbine engine comprises radially inner and outer walls defining an annular combustion space, air inlet apertures being provided in the inner or outer walls or both such walls, as distinct from the end walls, and being arranged to impart a velocity to the gases within the combustion space in a direction having a substantial circumferential component around the combustion chamber, fuel nozzles being provided so as to direct fuel directly into the rotating mass of gases in the combustion space. The equipment shown in Figs. 1 and 2 comprises inner and outer air casing walls 12, 11 defining an annular air space within which is disposed an annular flame tube comprising inner and outer walls 14, 13 and an end wall 15 defining an annular combustion space. The walls 14, 13 are built up of sections and air inlet ducts 17a, 17b and 17c are provided therein, the ducts being inclined with respect to the radial direction whereby a circumferential component of velocity is imparted to the inflowing air. The ducts 17a, 17b and 17c are inlets for primary, secondary and dilution air respectively. The air inlet ducts in the outer wall 13 may alternatively be directed purely radially as indicated in chain-dotted lines. Fuel inlet nozzles 19 are disposed in the end wall 15, but no air swirl device is provided there. Fuel injection nozzles may, alternatively, be disposed within some of the primary air inlet ducts 17a. In a second embodiment, air inlet ducts are provided only in the radially outer wall of the flame tube. In a further embodiment, Fig. 4, an annular air inlet duct 25 is disposed centrally within the annular flame tube so as to provide two annular combustion spaces 23, 22, air inlet ducts being provided in the outer wall of the inner annular space and in the inner wall of the outer annular space.
GB43865/59A 1959-12-24 1959-12-24 Combustion chambers Expired GB899213A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB43865/59A GB899213A (en) 1959-12-24 1959-12-24 Combustion chambers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB43865/59A GB899213A (en) 1959-12-24 1959-12-24 Combustion chambers

Publications (1)

Publication Number Publication Date
GB899213A true GB899213A (en) 1962-06-20

Family

ID=10430666

Family Applications (1)

Application Number Title Priority Date Filing Date
GB43865/59A Expired GB899213A (en) 1959-12-24 1959-12-24 Combustion chambers

Country Status (1)

Country Link
GB (1) GB899213A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2203023A1 (en) * 1972-10-13 1974-05-10 Onera (Off Nat Aerospatiale)
FR2222124A1 (en) * 1973-03-23 1974-10-18 Pillard Chauffage Combustion gases homogenizing equipment - ensures uniform temperatures for drying plants, gas turbines and jet engines
GB2301428A (en) * 1994-05-25 1996-12-04 Westinghouse Electric Corp Method and apparatus for reducing noise generated by combustion
JP2014044045A (en) * 2012-08-24 2014-03-13 Alstom Technology Ltd Method for mixing dilution air in sequential combustion system of gas turbine
CN104180398A (en) * 2014-08-24 2014-12-03 武汉英康汇通电气有限公司 Annular combustor
GB2519149A (en) * 2013-10-11 2015-04-15 Reaction Engines Ltd Ducts for engines
CN105716112A (en) * 2014-12-04 2016-06-29 中国航空工业集团公司沈阳发动机设计研究所 Method used for regulating temperature field of combustion chamber
CN115046227A (en) * 2022-06-21 2022-09-13 厦门大学 High-pressure rotary detonation gas turbine taking ammonia as fuel

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2203023A1 (en) * 1972-10-13 1974-05-10 Onera (Off Nat Aerospatiale)
FR2222124A1 (en) * 1973-03-23 1974-10-18 Pillard Chauffage Combustion gases homogenizing equipment - ensures uniform temperatures for drying plants, gas turbines and jet engines
GB2301428A (en) * 1994-05-25 1996-12-04 Westinghouse Electric Corp Method and apparatus for reducing noise generated by combustion
GB2301428B (en) * 1994-05-25 1998-09-30 Westinghouse Electric Corp Method and apparatus for reducing noise generated by combustion
JP2014044045A (en) * 2012-08-24 2014-03-13 Alstom Technology Ltd Method for mixing dilution air in sequential combustion system of gas turbine
GB2519149A (en) * 2013-10-11 2015-04-15 Reaction Engines Ltd Ducts for engines
CN104180398A (en) * 2014-08-24 2014-12-03 武汉英康汇通电气有限公司 Annular combustor
CN105716112A (en) * 2014-12-04 2016-06-29 中国航空工业集团公司沈阳发动机设计研究所 Method used for regulating temperature field of combustion chamber
CN115046227A (en) * 2022-06-21 2022-09-13 厦门大学 High-pressure rotary detonation gas turbine taking ammonia as fuel
CN115046227B (en) * 2022-06-21 2023-09-15 厦门大学 High-pressure rotary detonation gas turbine using ammonia as fuel

Similar Documents

Publication Publication Date Title
GB1427146A (en) Combustion apparatus for gas turbine engines
GB911759A (en) Improvements in fluid fuel combustion apparatus
GB836088A (en) Improvements in turbojet engine afterburners
GB1260557A (en) Improvements in annular combustion chamber liners
GB723015A (en) Improvements in or relating to gas turbine plant
GB765327A (en) Improvements relating to combustion chambers
GB650462A (en) Improvements in or relating to combustion apparatus
GB1094540A (en) Improvements in or relating to annular combustion chambers for gas turbine engines
GB899213A (en) Combustion chambers
GB812201A (en) Improvements in combustion equipment for continuous-flow internal combustion engines
GB736823A (en) Engine combustion chambers
GB627644A (en) Improvements relating to gas-turbine-engines and combustion-equipment therefor
GB922069A (en) Combustion chamber for a gas turbine engine
GB802370A (en) Improvements relating to exhaust reheaters for gas turbine jet engines
GB1524217A (en) Combustion chamber for a gas turbine engine
GB845971A (en) Improvements relating to combustion chambers for gas turbine engines
GB1354333A (en) Regenerative gas turbine engines
GB887829A (en) Improvements relating to flame tubes for combustion systems
GB791617A (en) Improvements in or relating to combustion equipment for gas-turbine engines
GB788557A (en) Main combustion chambers for gas turbine engines
GB620270A (en) Improvements in or relating to turbine apparatus
GB866969A (en) Gas turbine engines
GB1397296A (en) Combustion apparatus especially for gas turbine engines
GB1196168A (en) Combustion Assemblies for Gas-Turbine Engines
GB1150344A (en) Combustion Apparatus for Gas Turbine Engines