GB1335746A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1335746A
GB1335746A GB2400071*A GB2400071A GB1335746A GB 1335746 A GB1335746 A GB 1335746A GB 2400071 A GB2400071 A GB 2400071A GB 1335746 A GB1335746 A GB 1335746A
Authority
GB
United Kingdom
Prior art keywords
links
gutter
gutters
engine
pivotally connected
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
GB2400071*A
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 GB1335746A publication Critical patent/GB1335746A/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
    • F23R3/16—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
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Control Of Turbines (AREA)

Abstract

1335746 Gas turbine combustion equipment GENERAL ELECTRIC CO 19 April 1971 [25 May 1970] 22400/71 Heading F1L Gas turbine engine after-burner flameholder consists of an annular V-shaped gutter 32 having its apex in an upstream direction, links 42 connected at their downstream ends to the apex of the gutter and spaced circumferentially therearound and mounting means 48 pivotally connected to the upstream ends of the links and aligning the pivot axes of the links and the bisector "x" of the gutter in the direction of the hot gas flow theretoward in the "hot" condition of the afterburner, thereby reducing any tendency to twist the gutter when its material strength is weakest. Exhaust gases from a compressor/combustion chamber/ turbine unit flow along an annular duct formed by an engine casing 24 and central plug 26. Fuel is injected into the gas stream from bundles of tubes 30, and the flame is stabilized by a number of annular sheet metal gutters 32. Mounting lugs 38 extend through openings 36 in the gutters and have curved wings 40 which are brazed to the gutter. The upstream end of each lug is pivotally connected by a pair of links 42 to a beam 48. The radially outer end of the beam is pivotally attached to a lug 52 attached to the outer casing 24 of the engine. The beam is also supported by a link 54, one end of which is pivotally connected to the beam and the other end of which is pivotally connected into a bracket 60 mounted on a central plug 26 of the engine. When the afterburner is in operation, expansion of the casing 24, plug 26 and gutters 32 is accommodated by the links so that the gutters take up a position in which the bi-sector is aligned with the pivots 44 and 46. and with the direction of the hot gas stream.
GB2400071*A 1970-05-25 1971-04-19 Gas turbine engines Expired GB1335746A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US4029870A 1970-05-25 1970-05-25

Publications (1)

Publication Number Publication Date
GB1335746A true GB1335746A (en) 1973-10-31

Family

ID=21910234

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2400071*A Expired GB1335746A (en) 1970-05-25 1971-04-19 Gas turbine engines

Country Status (6)

Country Link
US (1) US3646763A (en)
BE (1) BE763178A (en)
CA (1) CA927616A (en)
DE (1) DE2108690A1 (en)
FR (1) FR2090250B1 (en)
GB (1) GB1335746A (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2122308B1 (en) * 1971-01-19 1976-03-05 Snecma Fr
FR2551500B1 (en) * 1983-09-07 1985-11-08 Snecma BURNER RING FOR POSTCOMBUSTION OF A REACTION ENGINE
FR2586792B1 (en) * 1985-09-03 1989-06-16 Snecma CONNECTION DEVICE BETWEEN A BURNER RING OR FLAME HANGER OF COMPOSITE MATERIAL AND A POST-COMBUSTION CHAMBER CHANNEL OF A TURBOREACTOR
US4815283A (en) * 1987-06-25 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Afterburner flameholder construction
US5103638A (en) * 1990-01-29 1992-04-14 Rolls-Royce Inc. Mounting arrangement
EP0550126A1 (en) * 1992-01-02 1993-07-07 General Electric Company Thrust augmentor heat shield
US6351941B1 (en) * 2000-02-29 2002-03-05 General Electric Company Methods and apparatus for reducing thermal stresses in an augmentor
US7712315B2 (en) * 2006-04-20 2010-05-11 United Technologies Corporation Augmentor variable vane flame stabilization

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2714287A (en) * 1950-01-03 1955-08-02 Westinghouse Electric Corp Flameholder device for turbojet afterburner
GB821286A (en) * 1956-06-05 1959-10-07 Rolls Royce Improvements in or relating to reheat combustion equipment of jet-propulsion engines
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
US3056261A (en) * 1959-09-01 1962-10-02 Gen Electric Flameholder configuration
FR1245920A (en) * 1960-01-19 1960-11-10 Le Ministre De La Defense Nati Insulated fuel distribution manifold
FR1265727A (en) * 1960-08-23 1961-06-30 Gen Electric Structure of flame tubes for afterburner burners of turbo-reactors
GB944202A (en) * 1961-07-11 1963-12-11 Rolls Royce Improvements in or relating to combustion equipment and ignition devices therefor
FR1406603A (en) * 1964-06-09 1965-07-23 Snecma Burner device and its installation in a combustion chamber

Also Published As

Publication number Publication date
DE2108690A1 (en) 1972-08-10
FR2090250B1 (en) 1975-01-17
FR2090250A1 (en) 1972-01-14
US3646763A (en) 1972-03-07
CA927616A (en) 1973-06-05
BE763178A (en) 1971-07-16

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees