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GB938247A - Gas turbine engine having cooled turbine blading - Google Patents

Gas turbine engine having cooled turbine blading

Info

Publication number
GB938247A
GB938247A GB11525/62A GB1152562A GB938247A GB 938247 A GB938247 A GB 938247A GB 11525/62 A GB11525/62 A GB 11525/62A GB 1152562 A GB1152562 A GB 1152562A GB 938247 A GB938247 A GB 938247A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
apertures
passages
pipe
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
Application number
GB11525/62A
Inventor
Harry Hartley Malley
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB11525/62A priority Critical patent/GB938247A/en
Publication of GB938247A publication Critical patent/GB938247A/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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

938,247. Gas turbine plant. ROLLS-ROYCE Ltd. March 26, 1962, No. 11525/62. Class 110(3). A gas turbine engine has at least one fixed hollow aerofoil member spanning a main annular gas duct and means for supplying a cooling fluid radially inwardly across the duct to passages in turbine rotor blades disposed in the duct downstream of the member, which itself is disposed downstream of an additional bladed turbine rotor stage forming part of the same rotor as the first mentioned stage. A fixed hollow aerofoil member is defined as a member which does not rotate about the axis of the engine and may be a pivotable nozzle guide vane. The high pressure turbine 8 of a compound gas turbine comprises stages 14, 15 and nozzle guide vanes 17. A tube 22 extends through each vane 17 having apertures 25 communicating with chamber 23. Cooling air supplied by pipe 34 to annular manifold 31, passes through tubes 32, 22, 39 to annular manifold 38, then through apertures 54 to chamber 44 and into passages 49 in the blades 48. Some air flows through apertures 25, 27 to cool the vanes 17 and thermally insulate them from the tubes 22. In a modification a further annular member 55 having inclined discharge orifices 57 may be mounted on member 36 to direct air into the passages 49 without loss. Vanes 17 may be pivotable about their longitudinal axes. Pipe 34 may contain an automatic shut-off valve and a heat exchanger or cooler may be provided in pipe 34 to cool air tapped from the compressor. Specification 884,409 is referred to.
GB11525/62A 1962-03-26 1962-03-26 Gas turbine engine having cooled turbine blading Expired GB938247A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB11525/62A GB938247A (en) 1962-03-26 1962-03-26 Gas turbine engine having cooled turbine blading

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB11525/62A GB938247A (en) 1962-03-26 1962-03-26 Gas turbine engine having cooled turbine blading

Publications (1)

Publication Number Publication Date
GB938247A true GB938247A (en) 1963-10-02

Family

ID=9987848

Family Applications (1)

Application Number Title Priority Date Filing Date
GB11525/62A Expired GB938247A (en) 1962-03-26 1962-03-26 Gas turbine engine having cooled turbine blading

Country Status (1)

Country Link
GB (1) GB938247A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1280618B (en) * 1964-12-02 1968-10-17 Rolls Royce Double-walled guide vane for gas turbine engines
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
US4930980A (en) * 1989-02-15 1990-06-05 Westinghouse Electric Corp. Cooled turbine vane
WO1994007005A1 (en) * 1992-09-24 1994-03-31 United Technologies Corporation, Pratt & Whitney Turbine vane assembly with integrally cast cooling fluid nozzle
EP0864728A3 (en) * 1997-03-11 2000-05-10 Mitsubishi Heavy Industries, Ltd. Blade cooling air supplying system for gas turbine
JP2000310127A (en) * 1999-04-15 2000-11-07 General Electric Co <Ge> Coolant supply system for third stage bucket for gas turbine
US6217279B1 (en) * 1997-06-19 2001-04-17 Mitsubishi Heavy Industries, Ltd. Device for sealing gas turbine stator blades
EP1380723A1 (en) * 2002-07-09 2004-01-14 Siemens Aktiengesellschaft Cooling method and pre-swirler for gas turbine blades as well as a turbine comprising such a pre-swirler
US7147431B2 (en) * 2002-11-27 2006-12-12 Rolls-Royce Plc Cooled turbine assembly
WO2008092845A3 (en) * 2007-01-31 2008-10-16 Siemens Ag A gas turbine
EP2383435A1 (en) * 2010-04-29 2011-11-02 Siemens Aktiengesellschaft Turbine vane hollow inner rail
EP2508733A1 (en) * 2011-04-07 2012-10-10 Siemens Aktiengesellschaft Gas turbine with a cooled turbine stage and method for cooling the turbine stage
US20160003071A1 (en) * 2014-05-22 2016-01-07 United Technologies Corporation Gas turbine engine stator vane baffle arrangement
CN110268152A (en) * 2017-02-07 2019-09-20 赛峰飞机发动机公司 Turbofan engine comprising an intermediate flow for supplying air through radial arms to an exhaust receptacle of the turbofan engine
EP4283097A1 (en) * 2022-05-27 2023-11-29 RTX Corporation Turbine engine with tangential onboard injector (tobi) supporting vanes

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1280618B (en) * 1964-12-02 1968-10-17 Rolls Royce Double-walled guide vane for gas turbine engines
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
US4930980A (en) * 1989-02-15 1990-06-05 Westinghouse Electric Corp. Cooled turbine vane
EP0383046A1 (en) * 1989-02-15 1990-08-22 Westinghouse Electric Corporation Cooled turbine vane
JP3226543B2 (en) 1992-09-24 2001-11-05 ユナイテッド テクノロジーズ コーポレイション，プラット アンド ホイットニー Turbine vane assembly with integrally cast cooling fluid nozzle
WO1994007005A1 (en) * 1992-09-24 1994-03-31 United Technologies Corporation, Pratt & Whitney Turbine vane assembly with integrally cast cooling fluid nozzle
EP0864728A3 (en) * 1997-03-11 2000-05-10 Mitsubishi Heavy Industries, Ltd. Blade cooling air supplying system for gas turbine
US6077034A (en) * 1997-03-11 2000-06-20 Mitsubishi Heavy Industries, Ltd. Blade cooling air supplying system of gas turbine
JP3416447B2 (en) 1997-03-11 2003-06-16 三菱重工業株式会社 Gas turbine blade cooling air supply system
US6217279B1 (en) * 1997-06-19 2001-04-17 Mitsubishi Heavy Industries, Ltd. Device for sealing gas turbine stator blades
JP2000310127A (en) * 1999-04-15 2000-11-07 General Electric Co <Ge> Coolant supply system for third stage bucket for gas turbine
EP1045114A3 (en) * 1999-04-15 2002-10-30 General Electric Company Cooling supply system for stage 3 bucket of a gas turbine
EP1380723A1 (en) * 2002-07-09 2004-01-14 Siemens Aktiengesellschaft Cooling method and pre-swirler for gas turbine blades as well as a turbine comprising such a pre-swirler
US7147431B2 (en) * 2002-11-27 2006-12-12 Rolls-Royce Plc Cooled turbine assembly
WO2008092845A3 (en) * 2007-01-31 2008-10-16 Siemens Ag A gas turbine
US8267641B2 (en) 2007-01-31 2012-09-18 Siemens Aktiengesellschaft Gas turbine
RU2576600C2 (en) * 2010-04-29 2016-03-10 Сименс Акциенгезелльшафт Guide vanes device for turbine and method of its manufacturing
WO2011134731A1 (en) * 2010-04-29 2011-11-03 Siemens Aktiengesellschaft Turbine vane hollow inner rail
US9869200B2 (en) 2010-04-29 2018-01-16 Siemens Aktiengesellschaft Turbine vane hollow inner rail
EP2383435A1 (en) * 2010-04-29 2011-11-02 Siemens Aktiengesellschaft Turbine vane hollow inner rail
CN102906374A (en) * 2010-04-29 2013-01-30 西门子公司 Turbine vane hollow inner rail
RU2591751C2 (en) * 2011-04-07 2016-07-20 Сименс Акциенгезелльшафт Method of cooling turbine stage and gas turbine comprising cooled turbine stage
WO2012136437A1 (en) 2011-04-07 2012-10-11 Siemens Aktiengesellschaft Process for cooling the turbine stage and gas turbine having a cooled turbine stage
EP2508733A1 (en) * 2011-04-07 2012-10-10 Siemens Aktiengesellschaft Gas turbine with a cooled turbine stage and method for cooling the turbine stage
US10180081B2 (en) 2011-04-07 2019-01-15 Siemens Aktiengesellschaft Process for cooling the turbine stage and gas turbine having a cooled turbine stage
US20160003071A1 (en) * 2014-05-22 2016-01-07 United Technologies Corporation Gas turbine engine stator vane baffle arrangement
CN110268152A (en) * 2017-02-07 2019-09-20 赛峰飞机发动机公司 Turbofan engine comprising an intermediate flow for supplying air through radial arms to an exhaust receptacle of the turbofan engine
US11499439B2 (en) * 2017-02-07 2022-11-15 Safran Aircraft Engines Double flow turbojet including an intermediate flow path dedicated to supplying with air via radial arms an exhaust casing of this turbojet
EP4283097A1 (en) * 2022-05-27 2023-11-29 RTX Corporation Turbine engine with tangential onboard injector (tobi) supporting vanes
US20230383663A1 (en) * 2022-05-27 2023-11-30 Raytheon Technologies Corporation Turbine engine with tobi supporting vanes
US12215606B2 (en) * 2022-05-27 2025-02-04 Rtx Corporation Turbine engine with TOBI supporting vanes

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