GB1062170A - Turbomachine cooling system - Google Patents
Turbomachine cooling systemInfo
- Publication number
- GB1062170A GB1062170A GB35920/65A GB3592065A GB1062170A GB 1062170 A GB1062170 A GB 1062170A GB 35920/65 A GB35920/65 A GB 35920/65A GB 3592065 A GB3592065 A GB 3592065A GB 1062170 A GB1062170 A GB 1062170A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- disc
- turbine
- air
- shank portions
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/181—Blades having a closed internal cavity containing a cooling medium, e.g. sodium
-
- 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)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1,062,170. Turbine and compressor blades. GENERAL ELECTRIC CO. Aug. 20, 1965, No. 35920/65. Headings F1G and F1T. The rotor disc 10 of a gas turbine has airfoil blades 11 (which may be compressor blades or turbine buckets) disposed in a duct 12 through which hot gas flows to drive the disc. In order to cool the blades 11 each blade contains a multiplicity of internal sealed thermosiphons 16 receiving a liquid metal that bolls to conduct heat to the shank portion 15 of the blade. In order to cool the shank portions 15, these have, on one or both sides of the disc 10, turbine blades 17 comprising spiral path buckets 18, Figs.2, 3 (not shown). A casing 19 adjacent the shank portions has a nozzle 20 for admitting hot gaseous fluid, e.g. ram air, to the blades 17 which air gives up energy by driving the disc. The work done on the disc cools the air which is then recycled through the turbine blades 17 by another expanding nozzle 21 to perform further work on the disc. The air may be exhausted through conduit 23 into the engine exhaust nozzle. In a modified construction, Figs.4-6 (not shown) the turbine blades 17 for cooling the shank portions are formed by extensions of the airfoil blades 11 and the air coolant may be exhausted to the main gas flow in the duct 12 through apertures 25.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB35920/65A GB1062170A (en) | 1965-08-20 | 1965-08-20 | Turbomachine cooling system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB35920/65A GB1062170A (en) | 1965-08-20 | 1965-08-20 | Turbomachine cooling system |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1062170A true GB1062170A (en) | 1967-03-15 |
Family
ID=10383020
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB35920/65A Expired GB1062170A (en) | 1965-08-20 | 1965-08-20 | Turbomachine cooling system |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1062170A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140140805A1 (en) * | 2012-11-05 | 2014-05-22 | General Electric Company | Inducer Guide Vanes |
EP2818639A1 (en) * | 2013-06-27 | 2014-12-31 | MTU Aero Engines GmbH | Turbomachine rotor blade and corresponding turbomachine |
CN113027538A (en) * | 2021-03-24 | 2021-06-25 | 北京航空航天大学 | High-efficiency cooling device for blades of turbine guider of aircraft engine |
-
1965
- 1965-08-20 GB GB35920/65A patent/GB1062170A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140140805A1 (en) * | 2012-11-05 | 2014-05-22 | General Electric Company | Inducer Guide Vanes |
US9441540B2 (en) * | 2012-11-05 | 2016-09-13 | General Electric Company | Inducer guide vanes |
EP2818639A1 (en) * | 2013-06-27 | 2014-12-31 | MTU Aero Engines GmbH | Turbomachine rotor blade and corresponding turbomachine |
US9951631B2 (en) | 2013-06-27 | 2018-04-24 | MTU Aero Engines AG | Turbomachine rotor blade |
CN113027538A (en) * | 2021-03-24 | 2021-06-25 | 北京航空航天大学 | High-efficiency cooling device for blades of turbine guider of aircraft engine |
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