GB948128A - Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers - Google Patents

Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers

Info

Publication number
GB948128A
GB948128A GB1050859A GB1050859A GB948128A GB 948128 A GB948128 A GB 948128A GB 1050859 A GB1050859 A GB 1050859A GB 1050859 A GB1050859 A GB 1050859A GB 948128 A GB948128 A GB 948128A
Authority
GB
United Kingdom
Prior art keywords
air
annular
nose piece
combustion chambers
vanes
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
GB1050859A
Inventor
Squire Ronald Jackson
Ronald Douglas Haig Saunders
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
Joseph Lucas Industries 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 Lucas Industries Ltd, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to GB1050859A priority Critical patent/GB948128A/en
Publication of GB948128A publication Critical patent/GB948128A/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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means

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)

Abstract

948,128. Gas turbine combustion chambers. JOSEPH LUCAS (INDUSTRIES) Ltd. March 24, 1960 [March 26, 1959], No. 10508/59. Heading F1L. Combustion apparatus for jet propulsion engines and other prime movers comprises two concentrically arranged annular combustion chambers having a common annular outlet, an air jacket arranged surrounding both chambers and providing a common annular air inlet thereto, and vanes fixed within the inlet for directing air to the combustion chambers, the vanes being arranged to support two concentric annular fuel supply manifolds each carrying a number of angularly spaced burners and a nose piece itself serving to support the combustion chambers within the air jacket. As shown two concentric combustion chambers 23, 24, surrounded by an air jacket 10, are supported at the common outlet 26 by a pair of sheet metal rings 39 which are supported in complementary annular grooves 40 in the air jacket 10. In the inlet end of the air jacket are vanes 11 formed from a continuous strip of metal 12. The strip 12 is supported by axially extending vanes 15, 16. Secured to the vanes are annularly disposed bosses 17 to which are attached either bridge pieces 18 supporting fuel manifolds 19, 20, or the nose piece 30, which has air inlet openings 33 shaped to direct primary air to the swirlers 34 surrounding burners 22 arranged round the manifolds 15, 20. The nose piece 30 forms with the adjacent walls of the combustion chamber an annular air duct 25 through which secondary air passes via apertures 31 into the combustion chamber. Secondary air also passes from two other annular air passages, defined by the air jacket and combustion chamber walls, via apertures 32 into the combustion chambers. Secured within the nose piece are radial tubes 37 which are aligned with radial tubes 36 secured to combustion chamber extensions 35. A pin 38 passing through the tubes 36, 37 secures the combustion chamber to the nose piece. The air jacket 10 is formed in two parts, so that when the inlet end is disconnected the combustion chambers 23, 24, complete with fuel manifolds 19, 20 and the nose piece 30 are removed.
GB1050859A 1959-03-26 1959-03-26 Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers Expired GB948128A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1050859A GB948128A (en) 1959-03-26 1959-03-26 Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1050859A GB948128A (en) 1959-03-26 1959-03-26 Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers

Publications (1)

Publication Number Publication Date
GB948128A true GB948128A (en) 1964-01-29

Family

ID=9969136

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1050859A Expired GB948128A (en) 1959-03-26 1959-03-26 Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers

Country Status (1)

Country Link
GB (1) GB948128A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4151713A (en) * 1977-03-15 1979-05-01 United Technologies Corporation Burner for gas turbine engine
EP0488557A1 (en) * 1990-11-26 1992-06-03 General Electric Company Double dome combustor
FR2691235A1 (en) * 1992-05-13 1993-11-19 Snecma Combustion chamber comprising a gas separator assembly.

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4151713A (en) * 1977-03-15 1979-05-01 United Technologies Corporation Burner for gas turbine engine
EP0488557A1 (en) * 1990-11-26 1992-06-03 General Electric Company Double dome combustor
FR2691235A1 (en) * 1992-05-13 1993-11-19 Snecma Combustion chamber comprising a gas separator assembly.
US5311743A (en) * 1992-05-13 1994-05-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas separator for a combustion chamber

Similar Documents

Publication Publication Date Title
US2856755A (en) Combustion chamber with diverse combustion and diluent air paths
GB1427146A (en) Combustion apparatus for gas turbine engines
GB1478395A (en) Apparatus for supplying a mixture of fuel and air to a combustion chamber
GB836088A (en) Improvements in turbojet engine afterburners
GB1495672A (en) Combustion systems for gas turbine engines
GB1180524A (en) Gas Turbine Jet Engine of the By-Pass Type
GB1138547A (en) Improvements in cooling structure
GB943839A (en) Jet propulsion engines
GB884756A (en) Primary air intake device for the combustion chamber of a gas-turbine unit
GB1127651A (en) Flameholder assembly for a jet propulsion engine afterburner
GB1344359A (en) Combustion equipment for gas turbine engines
GB904142A (en) Improvements in or relating to gas-turbine engines
GB1019050A (en) Aircraft-propulsive combustion ducts,such as ramjet engines and turbojet afterburners
GB948128A (en) Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers
GB802370A (en) Improvements relating to exhaust reheaters for gas turbine jet engines
GB638109A (en) Improvements in combustion chambers for aero-thermodynamic ducts and gas turbine engines
GB710353A (en) Improvements in or relating to combustion equipment for gas-turbine engines
GB788557A (en) Main combustion chambers for gas turbine engines
GB987564A (en) Aircraft jet propulsion power plant fuel burning equipment
GB1516177A (en) Fuel combustion apparatus
GB1150344A (en) Combustion Apparatus for Gas Turbine Engines
GB791752A (en) Improvements in or relating to flame tubes for use in combustion systems of gas turbine engines
GB741489A (en) Liquid fuel combustion chambers for jet-propulsion engines, gas turbines or other purposes
GB915233A (en) Fuel injection arrangement for gas turbine engines
GB746462A (en) Improved combustion apparatus for gas turbines and the like