GB1524956A - Gas tubine engine - Google Patents
Gas tubine engineInfo
- Publication number
- GB1524956A GB1524956A GB4866074A GB4866074A GB1524956A GB 1524956 A GB1524956 A GB 1524956A GB 4866074 A GB4866074 A GB 4866074A GB 4866074 A GB4866074 A GB 4866074A GB 1524956 A GB1524956 A GB 1524956A
- Authority
- GB
- United Kingdom
- Prior art keywords
- cooling air
- orifices
- chamber
- shroud
- guide vanes
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1524956 Gas turbine engines; cooling turbine structure ROLLS-ROYCE (1971) Ltd 30 Oct 1975 [11 Nov 1974] 48660/74 Heading F1G The invention relates to a gas turbine engine comprising stator structure defining the radially outer wall of the gas flow duct through the turbine, the stator structure including a shroud surrounding the rotor blades, there being air supply passages for cooling the shroud, the air passages having outlets for discharging the cooling air into the gas flow duct upstream of the rotor blades. In Fig. 2 the turbine comprises a rotor having blades 18 and inlet guide vanes 15 disposed in gas flow duct 21. The stator casing is shaped to provide two annular chambers 24, 25 separated by a wall 23A, also a shroud ring 22 disposed around the rotor blades. A series of tube members 27 extend across the chamber 25 each tube having discharge orifices 29 directed towards the outer surface of the shroud ring 22, so that cooling air supplied through chamber 24 and tubes 27 discharges through orifices 29 to impinge against the shroud ring. The cooling air then discharges from the chamber 25 through a series of orifices 32 disposed upstream of the rotor blades 18. The orifices 32 are so inclined as to direct the cooling air in the same direction as the gas discharge from the guide vanes 15. In Fig. 5 the inlet guide vanes are formed with longitudinal chambers adjacent the leading and trailing edges, a duct 43 being disposed within the leading edge chamber, cooling air supplied into the duct impinging against the inward surface of the leading edge before discharging from the vane. Cooling air discharging from tubes 47 against the outer surface of the shroud 22 discharges from the chamber 42 into the trailing edge chambers 45 of the guide vanes discharging therefrom through orifices 48 formed in the trailing edge 46.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4866074A GB1524956A (en) | 1975-10-30 | 1975-10-30 | Gas tubine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4866074A GB1524956A (en) | 1975-10-30 | 1975-10-30 | Gas tubine engine |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1524956A true GB1524956A (en) | 1978-09-13 |
Family
ID=10449445
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4866074A Expired GB1524956A (en) | 1975-10-30 | 1975-10-30 | Gas tubine engine |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1524956A (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2428141A1 (en) * | 1978-06-05 | 1980-01-04 | Gen Electric | IMPROVED TURBINE RUBBER SUPPORT DEVICE |
FR2467292A1 (en) * | 1979-10-09 | 1981-04-17 | Snecma | DEVICE FOR ADJUSTING THE GAME BETWEEN THE MOBILE AUBES AND THE TURBINE RING |
FR2519374A1 (en) * | 1982-01-07 | 1983-07-08 | Snecma | DEVICE FOR COOLING THE HEELS OF MOBILE BLADES OF A TURBINE |
FR2526083A1 (en) * | 1982-05-03 | 1983-11-04 | Gen Electric | AUTHOR MOTOR WITH TURBINE AUBES |
DE3736836A1 (en) * | 1987-10-30 | 1989-05-11 | Bbc Brown Boveri & Cie | AXIAL FLOWED GAS TURBINE |
EP0709550A1 (en) * | 1994-10-31 | 1996-05-01 | General Electric Company | Cooled shroud |
US6179557B1 (en) | 1998-07-18 | 2001-01-30 | Rolls-Royce Plc | Turbine cooling |
EP1657407A1 (en) * | 2004-11-15 | 2006-05-17 | Rolls-Royce Deutschland Ltd & Co KG | Method and apparatus for the cooling of the outer shrouds of the rotor blades of a gas turbine |
EP2180148A1 (en) * | 2008-10-27 | 2010-04-28 | Siemens Aktiengesellschaft | Gas turbine with cooling insert |
EP3023600A1 (en) * | 2014-11-24 | 2016-05-25 | Alstom Technology Ltd | Engine casing element |
CN106437861A (en) * | 2015-08-11 | 2017-02-22 | 熵零股份有限公司 | Region cooling impeller mechanism |
GB2603884A (en) * | 2004-09-07 | 2022-08-24 | Rolls Royce Plc | A cooling arrangement |
-
1975
- 1975-10-30 GB GB4866074A patent/GB1524956A/en not_active Expired
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2428141A1 (en) * | 1978-06-05 | 1980-01-04 | Gen Electric | IMPROVED TURBINE RUBBER SUPPORT DEVICE |
FR2467292A1 (en) * | 1979-10-09 | 1981-04-17 | Snecma | DEVICE FOR ADJUSTING THE GAME BETWEEN THE MOBILE AUBES AND THE TURBINE RING |
FR2519374A1 (en) * | 1982-01-07 | 1983-07-08 | Snecma | DEVICE FOR COOLING THE HEELS OF MOBILE BLADES OF A TURBINE |
EP0083896A1 (en) * | 1982-01-07 | 1983-07-20 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Cooling device for the shroud of the rotor blades of a turbine |
FR2526083A1 (en) * | 1982-05-03 | 1983-11-04 | Gen Electric | AUTHOR MOTOR WITH TURBINE AUBES |
DE3736836A1 (en) * | 1987-10-30 | 1989-05-11 | Bbc Brown Boveri & Cie | AXIAL FLOWED GAS TURBINE |
US4910958A (en) * | 1987-10-30 | 1990-03-27 | Bbc Brown Boveri Ag | Axial flow gas turbine |
EP0709550A1 (en) * | 1994-10-31 | 1996-05-01 | General Electric Company | Cooled shroud |
US5584651A (en) * | 1994-10-31 | 1996-12-17 | General Electric Company | Cooled shroud |
US6179557B1 (en) | 1998-07-18 | 2001-01-30 | Rolls-Royce Plc | Turbine cooling |
GB2603884A (en) * | 2004-09-07 | 2022-08-24 | Rolls Royce Plc | A cooling arrangement |
GB2603884B (en) * | 2004-09-07 | 2023-03-15 | Rolls Royce Plc | A cooling arrangement |
EP1657407A1 (en) * | 2004-11-15 | 2006-05-17 | Rolls-Royce Deutschland Ltd & Co KG | Method and apparatus for the cooling of the outer shrouds of the rotor blades of a gas turbine |
US7520719B2 (en) | 2004-11-15 | 2009-04-21 | Rolls-Royce Deutschland Ltd & Co Kg | Method and apparatus for the cooling of the outer shrouds of the rotor blades of a gas turbine |
WO2010049195A1 (en) * | 2008-10-27 | 2010-05-06 | Siemens Aktiengesellschaft | Gas turbine having cooling insert |
EP2180148A1 (en) * | 2008-10-27 | 2010-04-28 | Siemens Aktiengesellschaft | Gas turbine with cooling insert |
EP3023600A1 (en) * | 2014-11-24 | 2016-05-25 | Alstom Technology Ltd | Engine casing element |
CN106065789A (en) * | 2014-11-24 | 2016-11-02 | 通用电器技术有限公司 | Engine housing element |
CN106065789B (en) * | 2014-11-24 | 2020-08-07 | 安萨尔多能源英国知识产权有限公司 | Engine casing element |
CN106437861A (en) * | 2015-08-11 | 2017-02-22 | 熵零股份有限公司 | Region cooling impeller mechanism |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
CSNS | Application of which complete specification have been accepted and published, but patent is not sealed |