GB932513A - Gas turbine engine combustion chamber - Google Patents

Gas turbine engine combustion chamber

Info

Publication number
GB932513A
GB932513A GB1262/61A GB126261A GB932513A GB 932513 A GB932513 A GB 932513A GB 1262/61 A GB1262/61 A GB 1262/61A GB 126261 A GB126261 A GB 126261A GB 932513 A GB932513 A GB 932513A
Authority
GB
United Kingdom
Prior art keywords
flame tube
combustion
air
combustion chamber
supplied
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
GB1262/61A
Inventor
Kenneth Miller
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 GB1262/61A priority Critical patent/GB932513A/en
Publication of GB932513A publication Critical patent/GB932513A/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
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • 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

932,513. Generating combustion products under pressure. ROLLS-ROYCE Ltd. Jan. 4, 1962 [Jan. 11, 1961], No. 1262/61. Class 51 (1). A gas turbine engine combustion chamber comprises a flame tube, combustion air and fuel supply means, and means for supplying the internal wall of the flame tube at its upstream end with a flow of cooling air which enters the flame tube tangentially and in a direction such that any unburnt or incompletely burnt fuel particles which have moved upstream of the combustion zone and into the path of the flow of cooling air tend to be returned to the combustion zone. Each flame tube 14 comprises axially consecutive sheet metal tubular portions 20, 21, 22, 23 separated by corrugated annular members 24, 25, 26 through which cooling air from the space 17 may pass to flow axially along the internal surfaces of the tubular portions. Mounted within the tubular portion 20 is a sheetmetal member 27 having a frusto-conical portion 32 formed with axially-extending slots 33 provided with cowlings 34. Fuel is supplied to an injector 36 through a pipe 37. Of the air supplied to the upstream end of the combustion chamber, one portion passes through the tube 35 and a swirl device 38, one portion is supplied to the space 17, and the remainder passes via apertures 40 in a curved baffle member 41 to the slots 33. The air passing through the slots 33 flows tangentially of the frusto-conical portion 32 inwards towards the longitudinal axis thereof and causes unburnt fuel particles to be returned to the combustion zone.
GB1262/61A 1961-01-11 1961-01-11 Gas turbine engine combustion chamber Expired GB932513A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1262/61A GB932513A (en) 1961-01-11 1961-01-11 Gas turbine engine combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1262/61A GB932513A (en) 1961-01-11 1961-01-11 Gas turbine engine combustion chamber

Publications (1)

Publication Number Publication Date
GB932513A true GB932513A (en) 1963-07-31

Family

ID=9718916

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1262/61A Expired GB932513A (en) 1961-01-11 1961-01-11 Gas turbine engine combustion chamber

Country Status (1)

Country Link
GB (1) GB932513A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2194881A1 (en) * 1972-08-02 1974-03-01 Gen Electric
JPS4995305U (en) * 1972-12-11 1974-08-16
DE2845619A1 (en) * 1977-10-21 1979-04-26 Rolls Royce COMBUSTION DEVICE FOR A GAS TURBINE ENGINE
CN113217949A (en) * 2021-05-20 2021-08-06 西安航天动力研究所 Combustion chamber diverging and cooling structure and ramjet combustion chamber

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2194881A1 (en) * 1972-08-02 1974-03-01 Gen Electric
JPS4995305U (en) * 1972-12-11 1974-08-16
JPS5329842Y2 (en) * 1972-12-11 1978-07-26
DE2845619A1 (en) * 1977-10-21 1979-04-26 Rolls Royce COMBUSTION DEVICE FOR A GAS TURBINE ENGINE
CN113217949A (en) * 2021-05-20 2021-08-06 西安航天动力研究所 Combustion chamber diverging and cooling structure and ramjet combustion chamber

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