GB905573A - Improvements in flame tube construction for a gas turbine engine - Google Patents

Improvements in flame tube construction for a gas turbine engine

Info

Publication number
GB905573A
GB905573A GB17398/61A GB1739861A GB905573A GB 905573 A GB905573 A GB 905573A GB 17398/61 A GB17398/61 A GB 17398/61A GB 1739861 A GB1739861 A GB 1739861A GB 905573 A GB905573 A GB 905573A
Authority
GB
United Kingdom
Prior art keywords
flame tube
notch
passage
walls
vane
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
GB17398/61A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB905573A publication Critical patent/GB905573A/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
    • F23R3/42—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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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

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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

905,573. Generating combustion products under pressure. GENERAL ELECTRIC CO. May 12, 1961 [May 16, 1960], No. 17398/61. Class 51 (1). Combustion equipment for a gas turbine engine comprises inner and outer casings which form an annular air passage therebetween, at least one vane extending radially across the passage, a flame tube being mounted within the passage and extending downstream from the vane, the upstream end of the flame tube being formed with a notch or recess comprising a pair of walls spaced apart circumferentially and extending radially to the annular passage, and provided with a baffle portion extending transversely to the air flow through the passage and joining the walls, the baffle portion being formed with an apex extending generally circumferentially of the annular passage and transversely to the vane, and the vane being located in axiallyspaced relation to the notch or recess. The equipment shown comprises inner and outer casings 9, 8 forming an annular air passage within which is disposed an annular flame tube comprising inner and outer walls 3, 4 and an upstream portion 15. A strut 1 extends radially across the diffuser portion 7 formed between the walls 8, 9 and the upstream portion 15 of the flame tube is formed with a notch or recess 17 in which the trailing edge 1a of the strut is received. The notch 17 is formed by circumferentiallyspaced side walls 18, 19 and a transverse wall 20, the wall 20 being formed of V-shape with an apex 21 and acting as a baffle to deflect the air stream entering the notch into the inner and outer passages 7a, 7b. The flame tube also comprises an inner ring member 14 and fuel is supplied to the flame tube through injectors 12. The trailing edge of the strut need not necessarily be located within the notch 17.
GB17398/61A 1960-05-16 1961-05-12 Improvements in flame tube construction for a gas turbine engine Expired GB905573A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US29358A US3049882A (en) 1960-05-16 1960-05-16 Combustor construction with means for prevention of hot streaks

Publications (1)

Publication Number Publication Date
GB905573A true GB905573A (en) 1962-09-12

Family

ID=21848628

Family Applications (1)

Application Number Title Priority Date Filing Date
GB17398/61A Expired GB905573A (en) 1960-05-16 1961-05-12 Improvements in flame tube construction for a gas turbine engine

Country Status (3)

Country Link
US (1) US3049882A (en)
DE (1) DE1177415B (en)
GB (1) GB905573A (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE795867A (en) * 1972-03-01 1973-06-18 Gen Electric DEVICE FOR UNIFORMISING THE FLOW OF AIR IN A GAS TURBINE
US7222488B2 (en) * 2002-09-10 2007-05-29 General Electric Company Fabricated cowl for double annular combustor of a gas turbine engine
US9046272B2 (en) * 2008-12-31 2015-06-02 Rolls-Royce Corporation Combustion liner assembly having a mount stake coupled to an upstream support
US11732892B2 (en) * 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB657789A (en) * 1949-01-13 1951-09-26 Rolls Royce Improvements relating to liquid fuel combustion equipment for gas-turbine engines
BE496626A (en) * 1949-06-27
US2676460A (en) * 1950-03-23 1954-04-27 United Aircraft Corp Burner construction of the can-an-nular type having means for distributing airflow to each can
GB713422A (en) * 1950-03-28 1954-08-11 Rolls Royce Improvements relating to combustion equipment for gas turbine engines
GB715909A (en) * 1952-02-01 1954-09-22 Rolls Royce Improvements in or relating to combustion equipment of gas-turbine engines

Also Published As

Publication number Publication date
US3049882A (en) 1962-08-21
DE1177415B (en) 1964-09-03

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