IL161423A0 - Turbine engine augmentors - Google Patents

Turbine engine augmentors

Info

Publication number
IL161423A0
IL161423A0 IL16142304A IL16142304A IL161423A0 IL 161423 A0 IL161423 A0 IL 161423A0 IL 16142304 A IL16142304 A IL 16142304A IL 16142304 A IL16142304 A IL 16142304A IL 161423 A0 IL161423 A0 IL 161423A0
Authority
IL
Israel
Prior art keywords
turbine engine
augmentors
engine augmentors
turbine
engine
Prior art date
Application number
IL16142304A
Other languages
English (en)
Original Assignee
United Technologies 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 Technologies Corp filed Critical United Technologies Corp
Publication of IL161423A0 publication Critical patent/IL161423A0/xx

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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
    • 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
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion

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)
  • Air Supply (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Exhaust Gas After Treatment (AREA)
IL16142304A 2003-04-30 2004-04-15 Turbine engine augmentors IL161423A0 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/426,671 US7093442B2 (en) 2003-04-30 2003-04-30 Augmentor

Publications (1)

Publication Number Publication Date
IL161423A0 true IL161423A0 (en) 2004-09-27

Family

ID=32990420

Family Applications (1)

Application Number Title Priority Date Filing Date
IL16142304A IL161423A0 (en) 2003-04-30 2004-04-15 Turbine engine augmentors

Country Status (13)

Country Link
US (1) US7093442B2 (fr)
EP (1) EP1473519A3 (fr)
JP (1) JP3974595B2 (fr)
KR (1) KR100610732B1 (fr)
AU (1) AU2004201209B2 (fr)
CA (1) CA2460659A1 (fr)
DE (1) DE04252295T1 (fr)
IL (1) IL161423A0 (fr)
NO (1) NO20041762L (fr)
PL (1) PL366887A1 (fr)
SG (1) SG144713A1 (fr)
TR (1) TR200500469T3 (fr)
TW (1) TWI238871B (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2866675B1 (fr) * 2004-02-24 2008-05-16 Snecma Moteurs Procede d'amelioration des performances d'allumage de dispositif de post-combustion pour turboreacteur double flux et dispositif de post-combustion a performance d'allumage amelioree
US6983601B2 (en) * 2004-05-28 2006-01-10 General Electric Company Method and apparatus for gas turbine engines
US7174704B2 (en) * 2004-07-23 2007-02-13 General Electric Company Split shroud exhaust nozzle
US7437876B2 (en) * 2005-03-25 2008-10-21 General Electric Company Augmenter swirler pilot
US7467518B1 (en) 2006-01-12 2008-12-23 General Electric Company Externally fueled trapped vortex cavity augmentor
US8286416B2 (en) * 2008-04-02 2012-10-16 Pratt & Whitney Rocketdyne, Inc. Valve system for a gas turbine engine
US8578716B2 (en) * 2008-03-22 2013-11-12 United Technologies Corporation Valve system for a gas turbine engine
US8402744B2 (en) * 2008-03-22 2013-03-26 Pratt & Whitney Rocketdyne, Inc. Valve system for a gas turbine engine
US8240126B2 (en) * 2008-03-22 2012-08-14 Pratt & Whitney Rocketdyne, Inc. Valve system for a gas turbine engine
US8209987B2 (en) * 2008-11-26 2012-07-03 United Technologies Corporation Augmentor pilot
US8534071B1 (en) 2012-04-06 2013-09-17 United Technologies Corporation Engine hot section vane with tapered flame holder surface
US9879862B2 (en) 2013-03-08 2018-01-30 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
CN113280366B (zh) 2021-05-13 2022-09-27 中国航空发动机研究院 一种基于自激扫掠振荡燃油喷嘴的加力燃烧室结构

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2693083A (en) * 1951-03-26 1954-11-02 Roy W Abbott Combination flame-holder and fuel nozzle
US2780915A (en) * 1951-12-05 1957-02-12 Solar Aircraft Co Fuel distribution system for jet engine and afterburner
US2880573A (en) * 1952-08-27 1959-04-07 Gen Motors Corp Afterburner fuel injection system
US2979899A (en) * 1953-06-27 1961-04-18 Snecma Flame spreading device for combustion equipments
US2978865A (en) * 1956-02-06 1961-04-11 Curtiss Wright Corp Turbo fan exhaust mixing device
US2880574A (en) * 1956-05-18 1959-04-07 Curtiss Wright Corp By-pass turbo jet engine construction
US2847821A (en) * 1956-06-21 1958-08-19 Westinghouse Electric Corp Fuel ignition apparatus for an afterburner in the bypass duct of a turbojet engine
US2910828A (en) * 1956-08-24 1959-11-03 United Aircraft Company Convergent-divergent variable area propulsion nozzle
US2929203A (en) * 1956-08-31 1960-03-22 Westinghouse Electric Corp Afterburning bypass aviation turbojet engine
US3075353A (en) * 1959-08-19 1963-01-29 Gen Electric Supersonic combustion
US3712062A (en) * 1968-04-17 1973-01-23 Gen Electric Cooled augmentor liner
GB1305887A (fr) * 1971-07-01 1973-02-07
US3938328A (en) * 1971-11-08 1976-02-17 The Boeing Company Multicycle engine
US4069661A (en) * 1975-06-02 1978-01-24 The United States Of America As Represented By The United States National Aeronautics And Space Administration Variable mixer propulsion cycle
US4185461A (en) * 1978-01-10 1980-01-29 The United States Of America As Represented By The Secretary Of The Air Force Turbojet engine with combustor bypass
US5136840A (en) * 1982-09-30 1992-08-11 General Electric Company Gas turbine engine actuation system
US4798048A (en) * 1987-12-21 1989-01-17 United Technologies Corporation Augmentor pilot
US5099644A (en) * 1990-04-04 1992-03-31 General Electric Company Lean staged combustion assembly
US5385015A (en) * 1993-07-02 1995-01-31 United Technologies Corporation Augmentor burner
US5396761A (en) * 1994-04-25 1995-03-14 General Electric Company Gas turbine engine ignition flameholder with internal impingement cooling
US5685140A (en) * 1995-06-21 1997-11-11 United Technologies Corporation Method for distributing fuel within an augmentor
US5867980A (en) * 1996-12-17 1999-02-09 General Electric Company Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner
US6125627A (en) * 1998-08-11 2000-10-03 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
US6463739B1 (en) * 2001-02-05 2002-10-15 General Electric Company Afterburner heat shield

Also Published As

Publication number Publication date
EP1473519A3 (fr) 2007-04-11
NO20041762L (no) 2004-11-01
TWI238871B (en) 2005-09-01
DE04252295T1 (de) 2005-06-23
CA2460659A1 (fr) 2004-10-30
EP1473519A2 (fr) 2004-11-03
KR20040094313A (ko) 2004-11-09
KR100610732B1 (ko) 2006-08-09
PL366887A1 (en) 2004-11-02
US7093442B2 (en) 2006-08-22
JP2004332729A (ja) 2004-11-25
JP3974595B2 (ja) 2007-09-12
TW200424435A (en) 2004-11-16
AU2004201209B2 (en) 2005-10-27
US20040216444A1 (en) 2004-11-04
TR200500469T3 (tr) 2005-04-21
SG144713A1 (en) 2008-08-28
AU2004201209A1 (en) 2004-11-18

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