GB1043927A - Combustion apparatus for gas turbine engines - Google Patents

Combustion apparatus for gas turbine engines

Info

Publication number
GB1043927A
GB1043927A GB2647664A GB2647664A GB1043927A GB 1043927 A GB1043927 A GB 1043927A GB 2647664 A GB2647664 A GB 2647664A GB 2647664 A GB2647664 A GB 2647664A GB 1043927 A GB1043927 A GB 1043927A
Authority
GB
United Kingdom
Prior art keywords
flame tube
discharge duct
upstream end
gas turbine
support structure
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
GB2647664A
Inventor
Alan Ormerod
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 GB2647664A priority Critical patent/GB1043927A/en
Publication of GB1043927A publication Critical patent/GB1043927A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

1,043,927. Gas turbine engine combustion equipment. JOSEPH LUCAS (INDUSTRIES) Ltd. Sept. 2, 1965 [June 26, 1964], No. 26476/64. Heading F1L. The invention relates to combustion equipment of gas turbine engines of the kind comprising a series of flame tubes disposed angularly about the centre line of the engine. Each flame tube is mounted at its upstream end on supporting structure of the engine with provision for sliding movement longitudinally of the flame tube and for limited pivotal movement of the flame tube about its upstream end. The downstream end of the flame tube is connected to a discharge duct by interengageable partspherical portions on each, which permit of limited movement therebetween. The discharge duct is mounted on support structure so as to prevent any substantial relative movement longitudinally of the flame tube. The flame tube 10 is mounted at its upstream end on the fuel burner nozzle 12 by means of a part-spherical bearing 13. The downstream end of the flame tube is secured to the upstream end of the discharge duct 11 by means of the flanges 16, 17 which have interengaging part-spherical surfaces, the flanges being held in engagement by means of the clamping ring 18 which also has a partspherical surface. The inner periphery of the downstream end of the discharge duct is secured to support structure 15 by means of bolts 14, the outer periphery 19 thereof being arranged for relative movement with respect to the part 20 of the support structure.
GB2647664A 1964-06-26 1964-06-26 Combustion apparatus for gas turbine engines Expired GB1043927A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2647664A GB1043927A (en) 1964-06-26 1964-06-26 Combustion apparatus for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2647664A GB1043927A (en) 1964-06-26 1964-06-26 Combustion apparatus for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1043927A true GB1043927A (en) 1966-09-28

Family

ID=10244253

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2647664A Expired GB1043927A (en) 1964-06-26 1964-06-26 Combustion apparatus for gas turbine engines

Country Status (1)

Country Link
GB (1) GB1043927A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2633387A1 (en) * 1975-08-05 1977-02-24 Stal Laval Turbin Ab COMBUSTION CHAMBER FOR A GAS TURBINE
CN114543120A (en) * 2021-11-30 2022-05-27 中国航发湖南动力机械研究所 Flame tube fixing structure based on ceramic matrix composite

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2633387A1 (en) * 1975-08-05 1977-02-24 Stal Laval Turbin Ab COMBUSTION CHAMBER FOR A GAS TURBINE
CN114543120A (en) * 2021-11-30 2022-05-27 中国航发湖南动力机械研究所 Flame tube fixing structure based on ceramic matrix composite

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