CA995472A - Gas turbine engine augmenter liner coolant flow control system - Google Patents

Gas turbine engine augmenter liner coolant flow control system

Info

Publication number
CA995472A
CA995472A CA191,342A CA191342A CA995472A CA 995472 A CA995472 A CA 995472A CA 191342 A CA191342 A CA 191342A CA 995472 A CA995472 A CA 995472A
Authority
CA
Canada
Prior art keywords
control system
flow control
gas turbine
turbine engine
coolant flow
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
CA191,342A
Inventor
David A. Velegol
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
Application granted granted Critical
Publication of CA995472A publication Critical patent/CA995472A/en
Expired legal-status Critical Current

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
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners

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)
  • Exhaust Silencers (AREA)
CA191,342A 1973-02-09 1974-01-30 Gas turbine engine augmenter liner coolant flow control system Expired CA995472A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US331078A US3866417A (en) 1973-02-09 1973-02-09 Gas turbine engine augmenter liner coolant flow control system

Publications (1)

Publication Number Publication Date
CA995472A true CA995472A (en) 1976-08-24

Family

ID=23292537

Family Applications (1)

Application Number Title Priority Date Filing Date
CA191,342A Expired CA995472A (en) 1973-02-09 1974-01-30 Gas turbine engine augmenter liner coolant flow control system

Country Status (8)

Country Link
US (1) US3866417A (en)
JP (1) JPS49112017A (en)
BE (1) BE810794A (en)
CA (1) CA995472A (en)
DE (1) DE2405840A1 (en)
FR (1) FR2217547A1 (en)
GB (1) GB1458054A (en)
IT (1) IT1006315B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114341479A (en) * 2019-08-30 2022-04-12 赛峰航空器发动机 Convergent-divergent flap pair for a variable-geometry turbojet nozzle, the flaps of which each comprise a cooling air circulation duct

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4072008A (en) * 1976-05-04 1978-02-07 General Electric Company Variable area bypass injector system
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
US4833881A (en) * 1984-12-17 1989-05-30 General Electric Company Gas turbine engine augmentor
US4813229A (en) * 1985-03-04 1989-03-21 General Electric Company Method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas
DE3606286A1 (en) * 1985-03-04 1986-09-04 General Electric Co., Schenectady, N.Y. METHOD AND DEVICE FOR CONTROLLING THE COOLANT FLOW FLOW IN AN AFTERBURN LINING
US4961312A (en) * 1985-03-04 1990-10-09 General Electric Company Method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas turbine engine
US4958489A (en) * 1985-03-04 1990-09-25 General Electric Company Means for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas turbine engine
US4718230A (en) * 1986-11-10 1988-01-12 United Technologies Corporation Augmentor liner construction
US4706453A (en) * 1986-11-12 1987-11-17 General Motors Corporation Support and seal assembly
US4773593A (en) * 1987-05-04 1988-09-27 United Technologies Corporation Coolable thin metal sheet
US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
GB9127505D0 (en) * 1991-03-11 2013-12-25 Gen Electric Multi-hole film cooled afterburner combustor liner
US5157917A (en) * 1991-05-20 1992-10-27 United Technologies Corporation Gas turbine engine cooling air flow
US5720434A (en) * 1991-11-05 1998-02-24 General Electric Company Cooling apparatus for aircraft gas turbine engine exhaust nozzles
US5201887A (en) * 1991-11-26 1993-04-13 United Technologies Corporation Damper for augmentor liners
DE4338745B4 (en) * 1993-11-12 2005-05-19 Alstom Device for heat shielding the rotor in gas turbines
US5704208A (en) * 1995-12-05 1998-01-06 Brewer; Keith S. Serviceable liner for gas turbine engine
US7966823B2 (en) * 2006-01-06 2011-06-28 General Electric Company Exhaust dust flow splitter system
FR2900444B1 (en) * 2006-04-28 2008-06-13 Snecma Sa TURBOREACTOR COMPRISING A POST COMBUSTION CHANNEL COOLED BY A VARIABLE FLOW VENTILATION FLOW
GB2449477B (en) * 2007-05-24 2009-05-13 Rolls Royce Plc A duct installation
GB0904973D0 (en) * 2009-03-24 2009-05-06 Rolls Royce Plc A casing arrangement
US10253651B2 (en) * 2012-06-14 2019-04-09 United Technologies Corporation Turbomachine flow control device
US10054080B2 (en) * 2012-10-22 2018-08-21 United Technologies Corporation Coil spring hanger for exhaust duct liner
FR3004494B1 (en) * 2013-04-15 2018-01-19 Safran Nacelles TUYERE FOR AIRCRAFT TURBOPROPULSER WITH NON-CARBONATED BLOWER
US10385868B2 (en) * 2016-07-05 2019-08-20 General Electric Company Strut assembly for an aircraft engine
US11905843B2 (en) * 2020-04-01 2024-02-20 General Electric Company Liner support system

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR962862A (en) * 1946-10-26 1950-06-22
US2974486A (en) * 1958-03-27 1961-03-14 United Aircraft Corp Afterburner mixture and flame control baffle
US3031844A (en) * 1960-08-12 1962-05-01 William A Tomolonius Split combustion liner
FR1525092A (en) * 1967-01-23 1968-05-17 Snecma Hot gas flow and cold air flow turbo-reactor
US3712062A (en) * 1968-04-17 1973-01-23 Gen Electric Cooled augmentor liner
GB1180706A (en) * 1968-08-02 1970-02-11 Rolls Royce Flame Tube

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114341479A (en) * 2019-08-30 2022-04-12 赛峰航空器发动机 Convergent-divergent flap pair for a variable-geometry turbojet nozzle, the flaps of which each comprise a cooling air circulation duct
CN114341479B (en) * 2019-08-30 2023-06-16 赛峰航空器发动机 Convergence-divergence flap pairs for variable geometry turbojet nozzles, the flaps each comprising a cooling air circulation duct

Also Published As

Publication number Publication date
DE2405840A1 (en) 1974-08-15
IT1006315B (en) 1976-09-30
FR2217547A1 (en) 1974-09-06
US3866417A (en) 1975-02-18
BE810794A (en) 1974-05-29
GB1458054A (en) 1976-12-08
JPS49112017A (en) 1974-10-25

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