SE8800465L - GAS TURBINE ENGINE WITH AMPLIFIER AND PREVIOUS SURFACE INJECTOR - Google Patents

GAS TURBINE ENGINE WITH AMPLIFIER AND PREVIOUS SURFACE INJECTOR

Info

Publication number
SE8800465L
SE8800465L SE8800465A SE8800465A SE8800465L SE 8800465 L SE8800465 L SE 8800465L SE 8800465 A SE8800465 A SE 8800465A SE 8800465 A SE8800465 A SE 8800465A SE 8800465 L SE8800465 L SE 8800465L
Authority
SE
Sweden
Prior art keywords
hollow member
hollow
gas
bypass
spraybars
Prior art date
Application number
SE8800465A
Other languages
Unknown language ( )
Swedish (sv)
Other versions
SE8800465D0 (en
SE466559B (en
Inventor
Iii R G Giffin
I E Woltmann
D P Mchugh
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of SE8800465D0 publication Critical patent/SE8800465D0/en
Publication of SE8800465L publication Critical patent/SE8800465L/en
Publication of SE466559B publication Critical patent/SE466559B/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

A plurality of circumferentially displaced hollow members (28) are positioned between an outer bypass duct and the center body of the core engine of a gas turbine. Each of the hollow members is open at the radially outward end thereof for receiving relatively cool gas from the bypass duct. Each hollow member is formed with an opening (48) in the side thereof extending substantially the full length of the hollow member near the trailing edge thereof for discharging bypass gas (49) from the bypass duct in a direction facilitating thorough mixing of the bypass gas and core gases (38). A pivoted vane (50) may be provided in this opening of each of the hollow members and these vanes are controlled to vary the airflow through the aforementioned openings. Radially extending spraybars (44) or fuel rods are provided within each hollow member adjacent opposite sides thereof so as to be cooled by the bypass air flowing through the hollow member. The spraybars are provided with a plurality of openings adjacent the sidewalls of the hollow members and corresponding openings (46) are provided in these walls so that fuel, during augmentor operation, is directed into the area between adjacent hollow members. The aft end of each hollow member is formed as a relatively wide flat surface (36) which acts as a flameholder for the fuel supplied from the spraybars and burned in the augmentor. The forward end (40) of each hollow member is curved to an angle corresponding generally to the swirl angle of core gases exhausted from the core engine so as to effect a deswirling of this gas. <IMAGE>
SE8800465A 1987-02-13 1988-02-11 GAS TURBINE ENGINE WITH AMPLIFIER AND VARIABLE SURFACE INJECTOR SE466559B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US1456287A 1987-02-13 1987-02-13

Publications (3)

Publication Number Publication Date
SE8800465D0 SE8800465D0 (en) 1988-02-11
SE8800465L true SE8800465L (en) 1988-08-14
SE466559B SE466559B (en) 1992-03-02

Family

ID=21766218

Family Applications (1)

Application Number Title Priority Date Filing Date
SE8800465A SE466559B (en) 1987-02-13 1988-02-11 GAS TURBINE ENGINE WITH AMPLIFIER AND VARIABLE SURFACE INJECTOR

Country Status (5)

Country Link
JP (1) JPS63227930A (en)
DE (1) DE3803992A1 (en)
FR (1) FR2610994B1 (en)
GB (1) GB2202589B (en)
SE (1) SE466559B (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE8915860U1 (en) * 1989-02-08 1991-12-05 Mtu Muenchen Gmbh
US5261229A (en) * 1992-08-03 1993-11-16 General Electric Company Noise-suppressed exhaust nozzles for jet engines
FR2712962B1 (en) * 1993-11-24 1995-12-29 Snecma Post-combustion device comprising an improved flame catching device.
FR2763648B1 (en) * 1997-05-22 1999-07-02 Snecma DICHOTOMIC HEATING SYSTEM REDUCING DRY LOSSES
US7596950B2 (en) * 2005-09-16 2009-10-06 General Electric Company Augmentor radial fuel spray bar with counterswirling heat shield
US7603863B2 (en) * 2006-06-05 2009-10-20 General Electric Company Secondary fuel injection from stage one nozzle
JP5625585B2 (en) * 2010-07-27 2014-11-19 株式会社Ihi Afterburner and aircraft engine
JP6229590B2 (en) * 2014-04-30 2017-11-15 株式会社Ihi Afterburner and aircraft engine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3060680A (en) * 1957-12-30 1962-10-30 Rolls Royce By-pass gas-turbine engine and control therefor
GB928475A (en) * 1961-12-27 1963-06-12 Rolls Royce Improvements in or relating to by-pass gas turbine engines
GB1029900A (en) * 1964-11-27 1966-05-18 Rolls Royce By-pass gas turbine jet engine
DE1923150A1 (en) * 1968-05-08 1970-01-15 Man Turbo Gmbh Turbine jet engine
US4335573A (en) * 1970-09-02 1982-06-22 General Electric Company Gas turbine engine mixer
US3698186A (en) * 1970-12-24 1972-10-17 United Aircraft Corp Afterburner combustion apparatus
BE795529A (en) * 1972-02-17 1973-06-18 Gen Electric IGNITER MOUNTED ON A TURBOREACTOR THRUST INCREASING DEVICE AND AIR COOLED
US4072008A (en) * 1976-05-04 1978-02-07 General Electric Company Variable area bypass injector system
JPS5641815A (en) * 1979-09-12 1981-04-18 Mitsui Toatsu Chem Inc Purifying method for wet process phosphoric acid solution
US4461146A (en) * 1982-10-22 1984-07-24 The United States Of America As Represented By The Secretary Of The Navy Mixed flow swirl augmentor for turbofan engine

Also Published As

Publication number Publication date
SE8800465D0 (en) 1988-02-11
GB8803121D0 (en) 1988-03-09
DE3803992A1 (en) 1988-08-25
GB2202589A (en) 1988-09-28
JPH0587652B2 (en) 1993-12-17
GB2202589B (en) 1991-10-02
FR2610994B1 (en) 1993-06-11
FR2610994A1 (en) 1988-08-19
SE466559B (en) 1992-03-02
JPS63227930A (en) 1988-09-22

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