GB925388A - Improvements relating to turbine nozzle vane mounting means - Google Patents

Improvements relating to turbine nozzle vane mounting means

Info

Publication number
GB925388A
GB925388A GB28394/61A GB2839461A GB925388A GB 925388 A GB925388 A GB 925388A GB 28394/61 A GB28394/61 A GB 28394/61A GB 2839461 A GB2839461 A GB 2839461A GB 925388 A GB925388 A GB 925388A
Authority
GB
United Kingdom
Prior art keywords
vanes
cooling air
vane
spigot
ball
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
GB28394/61A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft 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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB925388A publication Critical patent/GB925388A/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
    • F01D5/12—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
    • F01D5/182—Transpiration cooling
    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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)
  • Control Of Turbines (AREA)

Abstract

925,388. Turbine blades. UNITED AIRCRAFT CORPORATION. Aug. 4, 1961 [Aug. 16, 1960], No. 28394/61. Class 110 (3). In a nozzle ring for a gas turbine having hollow vanes to which cooling air is supplied, each vane is mounted rigidly at one end and at the other end so that it may slide radially or pivot relative to the supporting means. The inner shrouds 34 of the guide vanes 12 are held rigidly by a number of co-operating splines and grooves and a retaining member 28. The outer shroud 54 has a cylindrical spigot 56 which carries slidably the ball member 76 of a ball-and-socket joint. The socket member 74 is mounted rigidly in the turbine structure. Cooling air supplied to the chamber 102 passes through the spigot 56 and opening 93 to passages 86 in the vanes 12 formed between ribs 88 and the baffle 90. The cooling air passes out of the inner end of the vane through openings 94, 98 and 100. The vanes may be removed by unbolting the retaining member 28, pivoting the inner end of the vane forward and then sliding the spigot 56 out of the ball member 74.
GB28394/61A 1960-08-16 1961-08-04 Improvements relating to turbine nozzle vane mounting means Expired GB925388A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US49979A US3075744A (en) 1960-08-16 1960-08-16 Turbine nozzle vane mounting means

Publications (1)

Publication Number Publication Date
GB925388A true GB925388A (en) 1963-05-08

Family

ID=21962759

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28394/61A Expired GB925388A (en) 1960-08-16 1961-08-04 Improvements relating to turbine nozzle vane mounting means

Country Status (3)

Country Link
US (1) US3075744A (en)
DE (1) DE1221849B (en)
GB (1) GB925388A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2374508A1 (en) * 1976-12-16 1978-07-13 Gen Electric IMPROVED TURBINE DISTRIBUTOR SEGMENT

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3240468A (en) * 1964-12-28 1966-03-15 Curtiss Wright Corp Transpiration cooled blades for turbines, compressors, and the like
US3423071A (en) * 1967-07-17 1969-01-21 United Aircraft Corp Turbine vane retention
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
US3619076A (en) * 1970-02-02 1971-11-09 Gen Electric Liquid-cooled turbine bucket
US3635587A (en) * 1970-06-02 1972-01-18 Gen Motors Corp Blade cooling liner
US4011718A (en) * 1975-08-01 1977-03-15 United Technologies Corporation Gas turbine construction
US4163629A (en) * 1977-12-23 1979-08-07 The United States Of America As Represented By The Secretary Of The Air Force Turbine vane construction
US4218178A (en) * 1978-03-31 1980-08-19 General Motors Corporation Turbine vane structure
US4314793A (en) * 1978-12-20 1982-02-09 United Technologies Corporation Temperature actuated turbine seal
DE3003469C2 (en) * 1980-01-31 1987-03-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for connecting rotationally symmetrically arranged components for turbomachines, in particular gas turbine engines, which are exposed to different thermal influences
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
US4728258A (en) * 1985-04-25 1988-03-01 Trw Inc. Turbine engine component and method of making the same
FR2583820B1 (en) * 1985-06-20 1989-04-28 Snecma DEVICE FOR VARIATION OF THE PASSAGE SECTION OF A TURBINE DISTRIBUTOR
US4990056A (en) * 1989-11-16 1991-02-05 General Motors Corporation Stator vane stage in axial flow compressor
US6517313B2 (en) 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US9279335B2 (en) 2011-08-03 2016-03-08 United Technologies Corporation Vane assembly for a gas turbine engine
US9273565B2 (en) * 2012-02-22 2016-03-01 United Technologies Corporation Vane assembly for a gas turbine engine
US10662792B2 (en) * 2014-02-03 2020-05-26 Raytheon Technologies Corporation Gas turbine engine cooling fluid composite tube
DE102014223975A1 (en) * 2014-11-25 2016-05-25 MTU Aero Engines AG Guide vane ring and turbomachine
US10655482B2 (en) * 2015-02-05 2020-05-19 Rolls-Royce Corporation Vane assemblies for gas turbine engines
JP6546481B2 (en) * 2015-08-31 2019-07-17 川崎重工業株式会社 Exhaust diffuser
FR3044038B1 (en) * 2015-11-19 2019-08-30 Safran Helicopter Engines DAWN EQUIPPED WITH AN ASSOCIATED COOLING SYSTEM, DISTRIBUTOR AND TURBOMACHINE
JP6651378B2 (en) * 2016-02-22 2020-02-19 三菱日立パワーシステムズ株式会社 Insert assembly, blade, gas turbine, and method of manufacturing blade
DE102016217320A1 (en) * 2016-09-12 2018-03-15 Siemens Aktiengesellschaft Gas turbine with separate cooling for turbine and exhaust housing
GB201616197D0 (en) * 2016-09-23 2016-11-09 Rolls Royce Plc Gas turbine engine
US11002147B2 (en) 2018-08-28 2021-05-11 Raytheon Technologies Corporation Fixed vane pack retaining ring
US11149567B2 (en) * 2018-09-17 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite load transfer roller joint
FR3097264B1 (en) * 2019-06-12 2021-05-28 Safran Aircraft Engines Turbomachine turbine with CMC distributor with load recovery
US11428113B2 (en) * 2020-12-08 2022-08-30 General Electric Company Variable stator vanes with anti-lock trunnions
US11719130B2 (en) * 2021-05-06 2023-08-08 Raytheon Technologies Corporation Vane system with continuous support ring
US11970946B2 (en) 2021-07-29 2024-04-30 General Electric Company Clearance control assembly

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE487115A (en) * 1946-04-05
FR965713A (en) * 1947-05-07 1950-09-20
BE492385A (en) * 1948-11-27
GB666537A (en) * 1949-08-27 1952-02-13 Armstrong Siddeley Motors Ltd Mounting of the stator blades of a gaseous fluid turbine
US2741455A (en) * 1950-06-29 1956-04-10 Rolls Royce Gas-turbine engines and nozzle-guidevane assemblies therefor
GB701101A (en) * 1950-06-29 1953-12-16 Rolls Royce Improvements in or relating to gas-turbine engines
US2793832A (en) * 1952-04-30 1957-05-28 Gen Motors Corp Means for cooling stator vane assemblies
US2859934A (en) * 1953-07-29 1958-11-11 Havilland Engine Co Ltd Gas turbines
US2862654A (en) * 1954-12-16 1958-12-02 Gen Motors Corp Variable pitch guide vanes
GB804922A (en) * 1956-01-13 1958-11-26 Rolls Royce Improvements in or relating to axial-flow fluid machines for example compressors andturbines
DE1049393B (en) * 1956-03-20
US2851246A (en) * 1956-10-24 1958-09-09 United Aircraft Corp Turbine or compressor construction and method of assembly
US2972441A (en) * 1957-05-14 1961-02-21 Gen Motors Corp Variable blade system
NL104794C (en) * 1957-08-16
BE570533A (en) * 1957-08-22

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2374508A1 (en) * 1976-12-16 1978-07-13 Gen Electric IMPROVED TURBINE DISTRIBUTOR SEGMENT

Also Published As

Publication number Publication date
US3075744A (en) 1963-01-29
DE1221849B (en) 1966-07-28

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