CA995472A - Gas turbine engine augmenter liner coolant flow control system - Google Patents
Gas turbine engine augmenter liner coolant flow control systemInfo
- 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
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)
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)
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)
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 |
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 |
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 |
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)
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 |
-
1973
- 1973-02-09 US US331078A patent/US3866417A/en not_active Expired - Lifetime
-
1974
- 1974-01-30 CA CA191,342A patent/CA995472A/en not_active Expired
- 1974-01-31 GB GB448374A patent/GB1458054A/en not_active Expired
- 1974-02-07 DE DE19742405840 patent/DE2405840A1/en active Pending
- 1974-02-08 JP JP49015533A patent/JPS49112017A/ja active Pending
- 1974-02-08 IT IT20314/74A patent/IT1006315B/en active
- 1974-02-08 FR FR7404254A patent/FR2217547A1/fr not_active Withdrawn
- 1974-02-08 BE BE140711A patent/BE810794A/en unknown
Cited By (2)
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 |
---|---|
JPS49112017A (en) | 1974-10-25 |
BE810794A (en) | 1974-05-29 |
FR2217547A1 (en) | 1974-09-06 |
US3866417A (en) | 1975-02-18 |
GB1458054A (en) | 1976-12-08 |
DE2405840A1 (en) | 1974-08-15 |
IT1006315B (en) | 1976-09-30 |
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