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GB943250A - Improvements in or relating to gas turbine combustion chambers - Google Patents

Improvements in or relating to gas turbine combustion chambers

Info

Publication number
GB943250A
GB943250A GB397362A GB397362A GB943250A GB 943250 A GB943250 A GB 943250A GB 397362 A GB397362 A GB 397362A GB 397362 A GB397362 A GB 397362A GB 943250 A GB943250 A GB 943250A
Authority
GB
United Kingdom
Prior art keywords
ring
flame tube
holes
turbine combustion
parts
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
GB397362A
Inventor
Francis Murray Johnson
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 GB397362A priority Critical patent/GB943250A/en
Priority to DER34346A priority patent/DE1211863B/en
Priority to FR923517A priority patent/FR1346205A/en
Publication of GB943250A publication Critical patent/GB943250A/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
    • F23R3/06—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
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)

Abstract

943,250. Gas-turbine combustion chambers. ROLLS-ROYCE Ltd. Feb. 1, 1962, No. 3973/62. Heading F1L. A gas turbine combustion chamber comprising a flame tube, fuel supply means and one or more primary and secondary air inlets in the flame tube has an inward annular projection from the flame tube adjacent the downstream edge of at least one secondary air inlet comprising a segmental part projecting from an annular ring, the annular ring being set in the wall of the flame tube and itself projecting into the flame tube. The upstream part of the flame tube is formed from portions 17, 18, 19, 20 having cooling air inlet holes 21, 22, 23. A ring member 24 locates the portion 20 which has a series of angularlyspaced air holes 25. A ring 26 has inwardly projecting segmental parts 27 axially aligned with the holes 25 which encroach on the parts 26, 27 to the extent of half the width of the ring 26 to form channels 28. The ring 26 may be of radial width of between 1/10 and 1/30 and the parts 27 project radially inwards from the ring to a distance of between 1/10 and 1/30 of the external radius of the ring 26. Axial holes 29 and radial holes 31 allow the entry of additional cooling air.
GB397362A 1962-02-01 1962-02-01 Improvements in or relating to gas turbine combustion chambers Expired GB943250A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB397362A GB943250A (en) 1962-02-01 1962-02-01 Improvements in or relating to gas turbine combustion chambers
DER34346A DE1211863B (en) 1962-02-01 1963-01-31 Combustion chamber for gas turbine engines
FR923517A FR1346205A (en) 1962-02-01 1963-02-01 Improvements relating to combustion chambers of gas turbo-engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB397362A GB943250A (en) 1962-02-01 1962-02-01 Improvements in or relating to gas turbine combustion chambers

Publications (1)

Publication Number Publication Date
GB943250A true GB943250A (en) 1963-12-04

Family

ID=9768400

Family Applications (1)

Application Number Title Priority Date Filing Date
GB397362A Expired GB943250A (en) 1962-02-01 1962-02-01 Improvements in or relating to gas turbine combustion chambers

Country Status (2)

Country Link
DE (1) DE1211863B (en)
GB (1) GB943250A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2410138A2 (en) * 1977-11-29 1979-06-22 Snecma COMBUSTION CHAMBERS FOR GAS TURBINE ENGINES
EP0348097A1 (en) * 1988-06-22 1989-12-27 Secretary Of State For Defence In Her Britannic Majesty's Gov. Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
EP0509176A1 (en) * 1991-04-16 1992-10-21 General Electric Company Method and apparatus for injecting dilution air

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE501690A (en) * 1950-03-07
BE502037A (en) * 1950-03-21
GB798474A (en) * 1955-03-16 1958-07-23 Bristol Aero Engines Ltd Improvements in or relating to combustion chambers
GB845971A (en) * 1958-07-21 1960-08-24 Gen Electric Improvements relating to combustion chambers for gas turbine engines
NL127178C (en) * 1959-11-20

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2410138A2 (en) * 1977-11-29 1979-06-22 Snecma COMBUSTION CHAMBERS FOR GAS TURBINE ENGINES
EP0348097A1 (en) * 1988-06-22 1989-12-27 Secretary Of State For Defence In Her Britannic Majesty's Gov. Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
WO1989012788A1 (en) * 1988-06-22 1989-12-28 The Secretary Of State For Defence In Her Britanni Gas turbine engine combustors
GB2238864A (en) * 1988-06-22 1991-06-12 Secr Defence Gas turbine engine combustors
GB2238864B (en) * 1988-06-22 1992-04-22 Secr Defence Gas turbine engine combustors
US5187937A (en) * 1988-06-22 1993-02-23 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
EP0509176A1 (en) * 1991-04-16 1992-10-21 General Electric Company Method and apparatus for injecting dilution air
US5220795A (en) * 1991-04-16 1993-06-22 General Electric Company Method and apparatus for injecting dilution air

Also Published As

Publication number Publication date
DE1211863B (en) 1966-03-03

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