GB1270959A - Means for cooling or regulating the temperature of a gas turbine engine - Google Patents
Means for cooling or regulating the temperature of a gas turbine engineInfo
- Publication number
- GB1270959A GB1270959A GB38483/69A GB3848369A GB1270959A GB 1270959 A GB1270959 A GB 1270959A GB 38483/69 A GB38483/69 A GB 38483/69A GB 3848369 A GB3848369 A GB 3848369A GB 1270959 A GB1270959 A GB 1270959A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- chamber
- turbine
- indicated
- seal
- 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
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- 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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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)
Abstract
1,270,959. Gas turbine engines - cooling. BENNES MARREL. July 31, 1969 [Sept. 27, 1968], No. 38483/69. Heading F1G. The invention relates to a gas turbine engine of the kind having compressor, combustion equipment, a first turbine driving the compressor, and a second turbine which drives a power output shaft, there being means to cool parts of the engine comprising three systems, firstly one utilizing air taken from the compressor, secondly one utilizing air taken from the chamber into which the compressor discharges high-pressure air, and thirdly one utilizing air drawn in from atmosphere. The engine shown comprises a centrifugal compressor 2 mounted on shaft 1 and driven by HP turbine 3, and a separate LP turbine 5 mounted on a shaft 6. The compressor discharges air to annular chamber 9 from which the air passes to two combustion chambers (not shown), the gases passing to an annular chamber 10 from which they are directed by inlet guide vane assembly 38 on to the HP turbine. Gases from the HP turbine are re-directed by interstage guide vane assembly 11 on to the LP turbine 5, the gases finally discharging through exhaust duct 12. The shaft 1 is supported in a bearing 4 and the shaft 6 in a bearing 7. Air is taken from the discharge of the compressor 2 as indicated by arrow 15 and passes through seal 17, then in part through seal 19 to chamber 13 then through seal 22 to chamber 24 of bearing 4. A second part of air from seal 17 passes through duct 20 arrow (41), Fig. 5 (not shown), to the seal 21, one part flowing through seal 21 to chamber 14 as indicated by arrow (42), the air then passing through seal 23 to chamber 34 of bearing 4. The chambers 24, 34 communicate through ducts (35), 36, 37 with atmosphere so as to permit a through-flow of cooling air. The chambers 13, 14 are interconnected by duct 26 through which a portion of air flows from the chambers 13, 14 through duct 27 to chamber 29 as indicated by arrow 28 on Fig. 1. From chamber 29 the air flows within the wall of the exhaust duct 12 as indicated by arrows 30, some finally discharging through orifices 76, some discharging through openings 75 into the exhaust gas stream and some passing through openings 31, 32, see Figs. 1 and 7, to cool the downstream face of the LP turbine rotor disc 5. A portion of air from the duct 20 flows through the seal 21, Fig. 5 (not shown) to cool the upstream face (40) of the HP turbine rotor disc 3 as indicated by arrows (43), (45). A portion of hot gases is taken from the chamber 10 upstream of the inlet guide vane assembly 38 through ducts (39) to control the temperature of the cooling air (43) flowing past the upstream face (40) of the HP turbine rotor disc. Air from the chamber 9 is also passed through ducts (77) for the same purpose. The above comprises the first cooling system. In the second cooling system, HP air is taken from the annular chamber 9 through ducts 46, 47, Figs. 1 and 2 to the annular manifold 48 of the interstage guide vane assembly 11, the air then passing through hollow struts 49 to the inner annular space 50. An interstage diaphragm 52 is secured to the inner wall of the space 50 and openings 53, 54 are formed in the inner wall at each side of the diaphragm whereby cooling air flows into the spaces 55, 56 adjacent the downstream face of the HP turbine rotor disc 3 and the upstream face of the LP turbine rotor disc 5 respectively. The air flows from the spaces 55, 56 into the turbine working fluid stream as indicated by the flow arrows 57, 58 and 59, 60 respectively. In the third cooling system air is drawn into chamber 65 through openings 66 as indicated by arrows 74, passing to a chamber 67, see Fig. 7. One portion of air from chamber 67 is drawn by a screw pump device 70 on the shaft 6 and flows as indicated by arrow 71 to cool the shaft bearing indicated at 7. A second portion of air from the chamber 67 is drawn by a centrifugal pump device comprising a series of radial grooves (78) and flows as indicated by arrow 72 through seal 73 to flow together with air-flow 30 across the downstream face of the LP turbine rotor disc 5.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR69050435 | 1968-09-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1270959A true GB1270959A (en) | 1972-04-19 |
Family
ID=9695624
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB38483/69A Expired GB1270959A (en) | 1968-09-27 | 1969-07-31 | Means for cooling or regulating the temperature of a gas turbine engine |
Country Status (7)
Country | Link |
---|---|
AT (1) | AT304956B (en) |
CA (1) | CA922115A (en) |
CH (1) | CH516081A (en) |
DE (1) | DE1940905B2 (en) |
FR (1) | FR1593039A (en) |
GB (1) | GB1270959A (en) |
NL (1) | NL6914432A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2520441A1 (en) * | 1980-10-10 | 1983-07-29 | Rolls Royce | TURBOMACHINE PROVIDED WITH AIR COOLING MEANS |
CN1297735C (en) * | 2004-11-15 | 2007-01-31 | 西安交通大学 | High temperature gas seal structure with heat insulating and cooling action |
EP3018299A1 (en) * | 2014-11-06 | 2016-05-11 | Rolls-Royce plc | A sealing arrangement for a gas turbine engine |
EP3023583A1 (en) * | 2014-11-20 | 2016-05-25 | Siemens Aktiengesellschaft | Gas turbine with the cooling of the last turbine stage |
CN107269396A (en) * | 2017-08-17 | 2017-10-20 | 中国科学院工程热物理研究所 | A kind of achievable bearing seal structure that chamber and bearing exocoel are pressed altogether |
CN114635796A (en) * | 2020-12-16 | 2022-06-17 | 中国航发商用航空发动机有限责任公司 | Aircraft engine bleed air cooling system and aircraft engine |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE395747B (en) * | 1975-12-10 | 1977-08-22 | Stal Laval Turbin Ab | TVASTEGSGASTURBIN |
FR2514408B1 (en) * | 1981-10-14 | 1985-11-08 | Snecma | DEVICE FOR CONTROLLING EXPANSIONS AND THERMAL CONSTRAINTS IN A GAS TURBINE DISC |
GB2121885B (en) * | 1982-06-10 | 1985-07-31 | Rolls Royce | Load distribution member for a gas turbine engine |
GB2561837A (en) | 2017-04-24 | 2018-10-31 | Hieta Tech Limited | Turbine rotor, turbine, apparatus and method |
CN117532864B (en) * | 2024-01-09 | 2024-04-09 | 漳州安越新材料科技有限公司 | Thermoplastic vehicular gas mixing box |
-
1968
- 1968-09-27 FR FR69050435A patent/FR1593039A/fr not_active Expired
-
1969
- 1969-07-31 GB GB38483/69A patent/GB1270959A/en not_active Expired
- 1969-08-12 DE DE19691940905 patent/DE1940905B2/en not_active Withdrawn
- 1969-08-19 AT AT7920/69A patent/AT304956B/en not_active IP Right Cessation
- 1969-08-28 CH CH1313869A patent/CH516081A/en not_active IP Right Cessation
- 1969-09-23 NL NL6914432A patent/NL6914432A/xx not_active Application Discontinuation
- 1969-09-26 CA CA063268A patent/CA922115A/en not_active Expired
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2520441A1 (en) * | 1980-10-10 | 1983-07-29 | Rolls Royce | TURBOMACHINE PROVIDED WITH AIR COOLING MEANS |
US4657482A (en) * | 1980-10-10 | 1987-04-14 | Rolls-Royce Plc | Air cooling systems for gas turbine engines |
CN1297735C (en) * | 2004-11-15 | 2007-01-31 | 西安交通大学 | High temperature gas seal structure with heat insulating and cooling action |
EP3018299A1 (en) * | 2014-11-06 | 2016-05-11 | Rolls-Royce plc | A sealing arrangement for a gas turbine engine |
US9638052B2 (en) | 2014-11-06 | 2017-05-02 | Rolls-Royce Plc | Sealing arrangement for a gas turbine engine |
EP3023583A1 (en) * | 2014-11-20 | 2016-05-25 | Siemens Aktiengesellschaft | Gas turbine with the cooling of the last turbine stage |
WO2016078980A1 (en) * | 2014-11-20 | 2016-05-26 | Siemens Aktiengesellschaft | Gas turbine having cooling of the last turbine stage |
US10125624B2 (en) | 2014-11-20 | 2018-11-13 | Siemens Aktiengesellschaft | Gas turbine with cooling of the last turbine stage |
CN107269396A (en) * | 2017-08-17 | 2017-10-20 | 中国科学院工程热物理研究所 | A kind of achievable bearing seal structure that chamber and bearing exocoel are pressed altogether |
CN107269396B (en) * | 2017-08-17 | 2019-02-15 | 中国科学院工程热物理研究所 | A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed |
CN114635796A (en) * | 2020-12-16 | 2022-06-17 | 中国航发商用航空发动机有限责任公司 | Aircraft engine bleed air cooling system and aircraft engine |
CN114635796B (en) * | 2020-12-16 | 2024-05-17 | 中国航发商用航空发动机有限责任公司 | Aeroengine bleed air cooling system and aeroengine |
Also Published As
Publication number | Publication date |
---|---|
CA922115A (en) | 1973-03-06 |
DE1940905A1 (en) | 1970-04-09 |
FR1593039A (en) | 1970-05-25 |
AT304956B (en) | 1972-12-15 |
DE1940905B2 (en) | 1971-08-05 |
CH516081A (en) | 1971-11-30 |
NL6914432A (en) | 1970-04-01 |
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