GB1132940A - Annular combustion equipment for a gas turbine engine - Google Patents

Annular combustion equipment for a gas turbine engine

Info

Publication number
GB1132940A
GB1132940A GB47705/67A GB4770567A GB1132940A GB 1132940 A GB1132940 A GB 1132940A GB 47705/67 A GB47705/67 A GB 47705/67A GB 4770567 A GB4770567 A GB 4770567A GB 1132940 A GB1132940 A GB 1132940A
Authority
GB
United Kingdom
Prior art keywords
wall
flame tube
sleeve
upstream end
annular
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
GB47705/67A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1132940A publication Critical patent/GB1132940A/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
    • 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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Gas Burners (AREA)

Abstract

1,132,940. Gas turbine engine combustion equipment. UNITED AIRCRAFT CORP. Oct. 19, 1967 [Nov.25, 1966], No.47705/67. Heading F1L. The invention relates to gas turbine engine combustion equipment of the kind comprising an annular flame tube disposed between inner and outer annular air casing walls, a series of combustion cups each receiving a fuel nozzle, being mounted on one of the flame tube walls adjacent the upstream end thereof, the combustion cups being disposed to form an annular assembly each having axial slidable engagement with the other flame tube wall. The combustion equipment shown comprises an inner air casing wall 6, 10, 16 and an outer air casing wall 8, 12, 23 which define an annular air space including an annular diffuser portion 4, a series of hollow struts 14 extending between the wall portions 6, 8. A pair of spaced-apart nose pieces 40, 46 and a pair of sleeves 36, 56 are located within the diffuser portion 4, the sleeve 36 being formed with notches 38 Fig. 2. to accommodate the strut members 14. The flame tube inner wall 30 is mounted at its upstream end on the downstream end of the sleeve 36 and the downstream end of the flame tube wall is secured be means of a bracket 34 to turbine stator structure including the inner air casing wall 16 and the turbine inlet nozzle guide vane assembly 20, the parts being secured together by means of bolts 22. The outer wall 32 of the flame tube is mounted at its upstream end on the sleeve member 56 and at its downstream end by means of a bracket 62 to the inlet nozzle guide vane structure 28. A series of combustion cups 64 each receiving a fuel nozzle 68 are secured to the flame tube outer wall 32, the cups being in slidable engagement with the flame tube inner wall 30. Each cup 64 is of circular form at its upstream end and diverges at its downstream end to a segment of an annulus. Each cup carries at its upstream end a ring of swirl vanes 66 which engage the fuel nozzle 68. The fuel burner 50 extends through openings in the outer casing 8 and the nose piece 46 and sleeve 56. The inner and outer sleeves 36, 56 are secured together by radial wall members 76, Fig. 2. The flame tube outer wall is located by means of pins 70 which extend into openings in the sleeve 56 and combustion cup 64. The nose pieces 40, 46 are formed with lugs 44, 52 by means of which the pieces are secured to the struts 14.
GB47705/67A 1966-11-25 1967-10-19 Annular combustion equipment for a gas turbine engine Expired GB1132940A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US596978A US3372542A (en) 1966-11-25 1966-11-25 Annular burner for a gas turbine

Publications (1)

Publication Number Publication Date
GB1132940A true GB1132940A (en) 1968-11-06

Family

ID=24389533

Family Applications (1)

Application Number Title Priority Date Filing Date
GB47705/67A Expired GB1132940A (en) 1966-11-25 1967-10-19 Annular combustion equipment for a gas turbine engine

Country Status (4)

Country Link
US (1) US3372542A (en)
DE (1) DE1601677B2 (en)
FR (1) FR1547846A (en)
GB (1) GB1132940A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2686683A1 (en) * 1992-01-28 1993-07-30 Snecma TURBOMACHINE WITH REMOVABLE COMBUSTION CHAMBER.

Families Citing this family (15)

* 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
GB1581050A (en) * 1976-12-23 1980-12-10 Rolls Royce Combustion equipment for gas turbine engines
US4365470A (en) * 1980-04-02 1982-12-28 United Technologies Corporation Fuel nozzle guide and seal for a gas turbine engine
US4458479A (en) * 1981-10-13 1984-07-10 General Motors Corporation Diffuser for gas turbine engine
US4483149A (en) * 1982-05-20 1984-11-20 United Technologies Corporation Diffuser case for a gas turbine engine
US4965994A (en) * 1988-12-16 1990-10-30 General Electric Company Jet engine turbine support
GB9108235D0 (en) * 1991-04-17 1991-06-05 Rolls Royce Plc A combustion chamber assembly
DE4242650A1 (en) * 1992-12-17 1994-06-23 Asea Brown Boveri Gas turbine combustion chamber
FR2857409B1 (en) * 2003-07-11 2006-07-28 Snecma Moteurs DEVICE FOR PASSIVELY PILOTING THE THERMAL EXPANSION OF THE EXPANSION BOX OF A TURBOREACTOR
FR2913050B1 (en) * 2007-02-28 2011-06-17 Snecma HIGH-PRESSURE TURBINE OF A TURBOMACHINE
US9046272B2 (en) * 2008-12-31 2015-06-02 Rolls-Royce Corporation Combustion liner assembly having a mount stake coupled to an upstream support
US9435535B2 (en) * 2012-02-20 2016-09-06 General Electric Company Combustion liner guide stop and method for assembling a combustor
US20150068212A1 (en) * 2012-04-19 2015-03-12 General Electric Company Combustor liner stop
US10247019B2 (en) * 2017-02-23 2019-04-02 General Electric Company Methods and features for positioning a flow path inner boundary within a flow path assembly
CN115142906B (en) * 2022-09-02 2022-11-22 中国航发沈阳发动机研究所 Connecting structure for rear end of inner wall of combustor flame tube and root of blade of turbine guider

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2686683A1 (en) * 1992-01-28 1993-07-30 Snecma TURBOMACHINE WITH REMOVABLE COMBUSTION CHAMBER.
US5524430A (en) * 1992-01-28 1996-06-11 Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Gas-turbine engine with detachable combustion chamber

Also Published As

Publication number Publication date
FR1547846A (en) 1968-11-29
US3372542A (en) 1968-03-12
DE1601677B2 (en) 1971-08-19
DE1601677A1 (en) 1970-08-27

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