GB1062170A - Turbomachine cooling system - Google Patents

Turbomachine cooling system

Info

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
Application number
GB35920/65A
Inventor
John Richard Erwin
Archie Harold Perugi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to GB35920/65A priority Critical patent/GB1062170A/en
Publication of GB1062170A publication Critical patent/GB1062170A/en
Expired legal-status Critical Current

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.
GB35920/65A 1965-08-20 1965-08-20 Turbomachine cooling system Expired GB1062170A (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (5)

* Cited by examiner, † Cited by third party
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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