GB1119439A - Adjustable nozzle guide vane assembly for an axial flow turbine - Google Patents

Adjustable nozzle guide vane assembly for an axial flow turbine

Info

Publication number
GB1119439A
GB1119439A GB24823/66A GB2482366A GB1119439A GB 1119439 A GB1119439 A GB 1119439A GB 24823/66 A GB24823/66 A GB 24823/66A GB 2482366 A GB2482366 A GB 2482366A GB 1119439 A GB1119439 A GB 1119439A
Authority
GB
United Kingdom
Prior art keywords
vane
axial flow
nozzle guide
adjustable nozzle
flow turbine
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
GB24823/66A
Inventor
Robert Noel Penny
Joseph John Poole
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.)
Rover Co Ltd
Original Assignee
Rover Co Ltd
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 Rover Co Ltd filed Critical Rover Co Ltd
Priority to GB24823/66A priority Critical patent/GB1119439A/en
Priority to CH776767A priority patent/CH464607A/en
Priority to FR108845A priority patent/FR1528203A/en
Priority to DE19671601636 priority patent/DE1601636B2/en
Priority to US643454A priority patent/US3392958A/en
Publication of GB1119439A publication Critical patent/GB1119439A/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,119,439. Turbines. ROVER CO. Ltd. June 2, 1967 [June 3, 1966], No.24823/66. Heading F1T. An axial flow turbine has an assembly of adjustable nozzle guide vanes 1 wherein each vane carries a pinion 3 which is rotated by engagement with an axially extending toothed rack portion 11 on an axially movable operating member 5 coaxial with the assembly. The member 5 is formed by a piston movable in a cylinder 6 having a space 8 supplied with operating air from a compressor of the engine of which the turbines 2, 9 form a part. The supply of air may be controlled manually or automatically to maintain the gas inlet temperature of turbine 2 constant. The axis of turning of each vane 1 is either coincident with the longitudinal axis through the centre of pressure of the vane or offset chordwise therefrom. The vanes, pinions, racks etc. are all made from high temperature resistant ceramic material.
GB24823/66A 1966-06-03 1966-06-03 Adjustable nozzle guide vane assembly for an axial flow turbine Expired GB1119439A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
GB24823/66A GB1119439A (en) 1966-06-03 1966-06-03 Adjustable nozzle guide vane assembly for an axial flow turbine
CH776767A CH464607A (en) 1966-06-03 1967-06-01 Axial flow gas turbine
FR108845A FR1528203A (en) 1966-06-03 1967-06-02 Axial turbine nozzle guide vane system
DE19671601636 DE1601636B2 (en) 1966-06-03 1967-06-02 Guide vane arrangement for turbines with guide vanes that can be adjusted during operation
US643454A US3392958A (en) 1966-06-03 1967-06-05 Adjustable nozzle guide vane assembly for an axial flow turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB24823/66A GB1119439A (en) 1966-06-03 1966-06-03 Adjustable nozzle guide vane assembly for an axial flow turbine

Publications (1)

Publication Number Publication Date
GB1119439A true GB1119439A (en) 1968-07-10

Family

ID=10217784

Family Applications (1)

Application Number Title Priority Date Filing Date
GB24823/66A Expired GB1119439A (en) 1966-06-03 1966-06-03 Adjustable nozzle guide vane assembly for an axial flow turbine

Country Status (4)

Country Link
US (1) US3392958A (en)
CH (1) CH464607A (en)
DE (1) DE1601636B2 (en)
GB (1) GB1119439A (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4278398A (en) * 1978-12-04 1981-07-14 General Electric Company Apparatus for maintaining variable vane clearance
US4239450A (en) * 1979-05-17 1980-12-16 Buffalo Forge Company Adjusting mechanism for variable inlet vane
US4302149A (en) * 1980-02-19 1981-11-24 General Motors Corporation Ceramic vane drive joint
DE3427528C1 (en) * 1984-07-26 1985-08-22 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8500 Nürnberg Device for regulating the extraction pressure of a extraction condensation turbine
DE4237031C1 (en) * 1992-11-03 1994-02-10 Mtu Muenchen Gmbh Adjustable guide vane
US5704762A (en) * 1993-11-08 1998-01-06 Alliedsignal Inc. Ceramic-to-metal stator vane assembly
DE102010021145A1 (en) * 2010-05-21 2011-11-24 Mtu Aero Engines Gmbh Adjustable guide vane and turbomachine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2364672A (en) * 1939-03-06 1944-12-12 Stevenson Engineering Corp Aerial propulsion
US2412365A (en) * 1943-10-26 1946-12-10 Wright Aeronautical Corp Variable turbine nozzle
US2486643A (en) * 1946-02-06 1949-11-01 Richard S Graham Reversible propeller
US2643852A (en) * 1950-01-09 1953-06-30 Us Air Force High-speed turbine
CA561070A (en) * 1952-10-03 1958-07-29 H. A. Magin Sidney Turbo machines having adjustable guide blades

Also Published As

Publication number Publication date
CH464607A (en) 1968-10-31
DE1601636B2 (en) 1970-11-05
US3392958A (en) 1968-07-16
DE1601636A1 (en) 1970-06-18

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