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GB1270905A - Cooling system for an axial flow elastic fluid utilizing machine - Google Patents

Cooling system for an axial flow elastic fluid utilizing machine

Info

Publication number
GB1270905A
GB1270905A GB40125/70A GB4012570A GB1270905A GB 1270905 A GB1270905 A GB 1270905A GB 40125/70 A GB40125/70 A GB 40125/70A GB 4012570 A GB4012570 A GB 4012570A GB 1270905 A GB1270905 A GB 1270905A
Authority
GB
United Kingdom
Prior art keywords
rotor
passageway
annular
blades
air
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
GB40125/70A
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.)
Westinghouse Electric Corp
Original Assignee
Westinghouse Electric Corp
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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of GB1270905A publication Critical patent/GB1270905A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,270,905. Elastic-fluid turbines - cooling. WESTINGHOUSE ELECTRIC CORP. Aug. 20, 1970 [Sept. 29, 1969], No.40125/70. Headings F1G and F1T. The invention relates to an axial-flow elasticfluid machine such as a turbine having a bladed rotor assembly, the rotor shaft comprising an annular passageway for supply of cooling fluid to the blades, also an annular cavity formed around part of the rotor and in communication with the annular passageway; flow-directing means are disposed upsteam of the annular passageway to impart an angular velocity to the cooling fluid as it enters the passageway. A gas turbine engine is shown in Fig. 1 and comprises a turbine rotor comprising discs 16, 18 also a torque tube 42 secured together by through-bolts 19. The torque tube is connected to a shaft member 43 by bolts 44. The rotor discs carry blades 20, 22 which co-operate with blades 23, 25 carried by the stator casing 11, 12. The engine comprises also combustion chambers 36. An inner stator casing member 45 carries labyrinth seal members 46 which co-operate with a member 49 which forms part of the rotor assembly, an annular passageway 60 being defined between the member 49 and the torque tube 42, the passageway extending to an annular chamber 70 defined between a flange 50 of the member and the rotor disc 16. Cooling fluid such as air from the compressor is supplied to manifold 47 and then flows through pipe 48 to an annular cavity 56 defined between the stator member 45, the rotor member 49 and the seal members 46. The cooling air then flows through devices 62 carried by the rotor member 49 into the annular passageway 60, the devices 62 acting to impart angular velocity to the cooling fluid as it enters the passageway. The flange portion 50 of the rotor member 49 carries vanes 71 which assist the circumferential flow of the air in chamber 70. From chamber 70 the air passes to cool the roots of the rotor blades. The device 62 is a tubular-shaped member as shown in Fig. 3, part of the radially inner portion 63 being cut away to provide an outlet 64. In place of the member 62 shown in Fig. 3, a straight vane may be utilized. In a further embodiment the cooling air passes through a series of tangentially directed nozzles (90) formed in a ring member (82) supported by the stator member (83), the air passing through openings (88) formed in the rotor member (86) and so into the annular passageway (89).
GB40125/70A 1969-09-29 1970-08-20 Cooling system for an axial flow elastic fluid utilizing machine Expired GB1270905A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US86197769A 1969-09-29 1969-09-29

Publications (1)

Publication Number Publication Date
GB1270905A true GB1270905A (en) 1972-04-19

Family

ID=25337275

Family Applications (1)

Application Number Title Priority Date Filing Date
GB40125/70A Expired GB1270905A (en) 1969-09-29 1970-08-20 Cooling system for an axial flow elastic fluid utilizing machine

Country Status (7)

Country Link
US (1) US3602605A (en)
AT (1) AT301273B (en)
CA (1) CA919091A (en)
CH (1) CH519096A (en)
DE (2) DE2043480A1 (en)
FR (1) FR2062769A5 (en)
GB (1) GB1270905A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4674955A (en) * 1984-12-21 1987-06-23 The Garrett Corporation Radial inboard preswirl system

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3750398A (en) * 1971-05-17 1973-08-07 Westinghouse Electric Corp Static seal structure
US3842595A (en) * 1972-12-26 1974-10-22 Gen Electric Modular gas turbine engine
US3945758A (en) * 1974-02-28 1976-03-23 Westinghouse Electric Corporation Cooling system for a gas turbine
US3904307A (en) * 1974-04-10 1975-09-09 United Technologies Corp Gas generator turbine cooling scheme
US3990812A (en) * 1975-03-03 1976-11-09 United Technologies Corporation Radial inflow blade cooling system
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
US4113406A (en) * 1976-11-17 1978-09-12 Westinghouse Electric Corp. Cooling system for a gas turbine engine
US4184797A (en) * 1977-10-17 1980-01-22 General Electric Company Liquid-cooled turbine rotor
US4306834A (en) * 1979-06-25 1981-12-22 Westinghouse Electric Corp. Balance piston and seal for gas turbine engine
DE3014279A1 (en) * 1980-04-15 1981-10-22 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 4200 Oberhausen DEVICE FOR COOLING THE INSIDE OF A GAS TURBINE
FR2484574A1 (en) * 1980-06-13 1981-12-18 Snecma MULTI-BODY TURBOMACHINE INTER-SHAFT BEARING WITH OIL-DAMPING DAMPING
DE3310396A1 (en) * 1983-03-18 1984-09-20 Kraftwerk Union AG, 4330 Mülheim MD STEAM TURBINE IN SINGLE-FLOW CONSTRUCTION FOR A HIGH-TEMPERATURE STEAM TURBINE SYSTEM WITH INTERMEDIATE HEATING
EP0144842B1 (en) * 1983-12-05 1988-07-27 Westinghouse Electric Corporation Cascaded air supply for gas turbine cooling
DE3424139C2 (en) * 1984-06-30 1996-02-22 Bbc Brown Boveri & Cie Gas turbine rotor
US4759688A (en) * 1986-12-16 1988-07-26 Allied-Signal Inc. Cooling flow side entry for cooled turbine blading
US5340271A (en) * 1990-08-18 1994-08-23 Rolls-Royce Plc Flow control method and means
DE4337281A1 (en) * 1993-11-02 1995-05-04 Abb Management Ag compressor
DE4433289A1 (en) * 1994-09-19 1996-03-21 Abb Management Ag Axial gas turbine
DE4435322B4 (en) * 1994-10-01 2005-05-04 Alstom Method and device for shaft seal and for cooling on the exhaust side of an axial flowed gas turbine
JP3652780B2 (en) * 1996-04-08 2005-05-25 三菱重工業株式会社 Turbine cooling system
SE508085C2 (en) * 1996-12-12 1998-08-24 Abb Carbon Ab Method for air flow control of combustion air and barrier air device
DE69819290T2 (en) * 1997-06-20 2004-07-29 Mitsubishi Heavy Industries, Ltd. AIR SEPARATOR FOR GAS TURBINES
US6234746B1 (en) * 1999-08-04 2001-05-22 General Electric Co. Apparatus and methods for cooling rotary components in a turbine
JP4067709B2 (en) * 1999-08-23 2008-03-26 三菱重工業株式会社 Rotor cooling air supply device
DE102004016244B4 (en) * 2004-04-02 2007-08-23 Mtu Aero Engines Gmbh Rotor for a turbomachine
GB2424927A (en) * 2005-04-06 2006-10-11 Rolls Royce Plc A pre-swirl nozzle ring and a method of manufacturing a pre-swirl nozzle ring
US7244104B2 (en) * 2005-05-31 2007-07-17 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
US7189055B2 (en) * 2005-05-31 2007-03-13 Pratt & Whitney Canada Corp. Coverplate deflectors for redirecting a fluid flow
US7189056B2 (en) * 2005-05-31 2007-03-13 Pratt & Whitney Canada Corp. Blade and disk radial pre-swirlers
US8192151B2 (en) 2009-04-29 2012-06-05 General Electric Company Turbine engine having cooling gland
US8529195B2 (en) 2010-10-12 2013-09-10 General Electric Company Inducer for gas turbine system
US9435206B2 (en) * 2012-09-11 2016-09-06 General Electric Company Flow inducer for a gas turbine system
US9441540B2 (en) * 2012-11-05 2016-09-13 General Electric Company Inducer guide vanes
US9039357B2 (en) * 2013-01-23 2015-05-26 Siemens Aktiengesellschaft Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine
US9556737B2 (en) 2013-11-18 2017-01-31 Siemens Energy, Inc. Air separator for gas turbine engine
CA2964126C (en) * 2016-04-12 2019-01-08 Airtek Systems Inc. System and method for generating rotational power
US11242804B2 (en) * 2017-06-14 2022-02-08 General Electric Company Inleakage management apparatus

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4674955A (en) * 1984-12-21 1987-06-23 The Garrett Corporation Radial inboard preswirl system

Also Published As

Publication number Publication date
FR2062769A5 (en) 1971-06-25
CA919091A (en) 1973-01-16
DE2047648A1 (en) 1971-05-19
DE2043480A1 (en) 1971-04-01
AT301273B (en) 1972-08-25
CH519096A (en) 1972-02-15
US3602605A (en) 1971-08-31

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