GB1458054A - Gas turbine engines including exhaust reheat combustion equipment - Google Patents
Gas turbine engines including exhaust reheat combustion equipmentInfo
- Publication number
- GB1458054A GB1458054A GB448374A GB448374A GB1458054A GB 1458054 A GB1458054 A GB 1458054A GB 448374 A GB448374 A GB 448374A GB 448374 A GB448374 A GB 448374A GB 1458054 A GB1458054 A GB 1458054A
- Authority
- GB
- United Kingdom
- Prior art keywords
- liner
- openings
- jet pipe
- gas turbine
- engine
- 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
Abstract
1458054 Gas turbine jet propulsion engines GENERAL ELECTRIC CO 31 Jan 1974 [9 Feb 1973] 04483/74 Headings F1J and F1L The invention relates to an exhaust re-heat system of a gas turbine engine in which a liner is disposed within the engine jet pipe to define therebetween a plenum space to which cooling air is supplied and from which it discharges through openings in the liner into the re-heat combustion zone. The engine shown is a by-pass type engine, air from the fan or L.P. compressor 15 passing through by-pass duct 22 and mixing with gases discharging from the turbine 14 in a mixing device 32. The re-heat combustion zone 40 is disposed downstream of the mixer and is defined by a liner 46 located within the jet pipe 44 cooling air from the by-pass duct 22 passing into the plenum space 48 defined between the jet pipe and the liner. The cooling air passes through openings 54 formed in the liner into the re-heat combustion zone 40. The object of the invention is to make the pressure drop across the openings 54 move nearly uniform along the length of the liner, and this is achieved by dividing the plenum space 48 into a series of interconnected chambers 78, 80, 82 by means of a series of flanges 76 which provide openings 84 of reduced height into each chamber.. Each flange 76 is associated with a support device 56, each of which comprises a circumferential row of struts 58, a securing member 60 which is secured to the jet pipe 44 by means of bolts 70, a ring member 62 being interposed there-between. The forward edge of the ring member is extended as a radially inwardly directed flange 76 which defines the restricted inlet to a chamber such as 80.
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 |
|---|---|
| GB1458054A true GB1458054A (en) | 1976-12-08 |
Family
ID=23292537
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB448374A Expired GB1458054A (en) | 1973-02-09 | 1974-01-31 | Gas turbine engines including exhaust reheat combustion equipment |
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) |
Families Citing this family (27)
| 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 |
| 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 |
| 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 |
| 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 |
| FR3100284B1 (en) * | 2019-08-30 | 2021-12-03 | Safran Aircraft Engines | COUPLE CONVERGENT-DIVERGENT FLAP FOR VARIABLE GEOMETRY TURBOREACTOR NOZZLE WHOSE SHUTTERS EACH INCLUDE A COOLING AIR CIRCULATION DUCT |
| 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 IT IT20314/74A patent/IT1006315B/en active
- 1974-02-08 JP JP49015533A patent/JPS49112017A/ja active Pending
- 1974-02-08 BE BE140711A patent/BE810794A/en unknown
- 1974-02-08 FR FR7404254A patent/FR2217547A1/fr not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| BE810794A (en) | 1974-05-29 |
| CA995472A (en) | 1976-08-24 |
| FR2217547A1 (en) | 1974-09-06 |
| DE2405840A1 (en) | 1974-08-15 |
| US3866417A (en) | 1975-02-18 |
| IT1006315B (en) | 1976-09-30 |
| JPS49112017A (en) | 1974-10-25 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed [section 19, patents act 1949] | ||
| PCNP | Patent ceased through non-payment of renewal fee |