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US3392958A - Adjustable nozzle guide vane assembly for an axial flow turbine - Google Patents

Adjustable nozzle guide vane assembly for an axial flow turbine Download PDF

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Publication number
US3392958A
US3392958A US643454A US64345467A US3392958A US 3392958 A US3392958 A US 3392958A US 643454 A US643454 A US 643454A US 64345467 A US64345467 A US 64345467A US 3392958 A US3392958 A US 3392958A
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US
United States
Prior art keywords
nozzle guide
turbine
vane
axial flow
guide vane
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 - Lifetime
Application number
US643454A
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English (en)
Inventor
Penny Robert Noel
Poole Joseph John
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
Application granted granted Critical
Publication of US3392958A publication Critical patent/US3392958A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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]

Definitions

  • vanes are turned by a common operating ring which is moved circumferentially about its axis.
  • a circumferentially-movable operating ring is unsuitable for a turbine subject to a high operating temperature, e.g., of the order of 1100 C., as provision has to be made to allow for radial and circumferential expansion and contraction of the operating ring.
  • an adjustable nozzle guide vane assembly for a turbine of the axial flow type comprises a plurality of nozzle guide vanes spaced apart circumferentially about the axis of the turbine in a circle and each mounted for turning about at an axis extending transversely to the axis of the turbine, a pinion integral with or attached to each vane and an axially movable operating member co-axial with the circle of vanes and carrying a plurality of circumferentially-spaced, axiallyextending toothed rack portions, each engaging a respective pinion, whereby axial movement of the operating member will turn the vanes about their respective axes.
  • the operating member is a piston mounted in a cylinder co-axial with and positioned radially within the circle of vanes, the piston having a skirt portion extending from the cylinder and formed on its outer peripheral surface with the said toothed rack portions, and the cylinder having inlet and outlet means through which operating fluid is arranged to be passed.
  • the operating fluid may be compressed air bled from a compressor of a gas turbine engine of which the turbine is a component.
  • the supply of operating fluid to and from the cylinder and therefore the operation of the piston may be controlled by the operator of the gas turbine engine or it may be operated automatically, for example to maintain the turbine inlet temperature substantially constant.
  • each vane may be coincident with the longitudinal axis through the center of pressure of the vane or it may be offset chordwise of the vane from said longitudinal axis. In the latter case, the loading of the working fluid on the vane can be used to assist or to oppose the torque applied to a vane by the pinion.
  • the piston and the cylinder are conveniently made of a ceramic or other non-metallic material capable of withstanding a high operating temperature, e.g., of the order of 11()0 0, thereby to avoid seizure of the piston in the cylinder.
  • the v-anes and their pinions may also be made of a ceramic or non-metallic material capable of withstanding a high operating temperature.
  • the invention also includes a gas turbine engine having an adjustable nozzle guide vane assembly as set out hereinbefore.
  • FIGURE 1 is an axial section through the assembly
  • FIGURE 2 is a half section on the line IIII in FIG- URE 1, and
  • FIGURE 3 is a scrap section on the line III-III in FIGURE 2.
  • the assembly comprises a plurality of nozzle guide vanes 1 spaced apart circumferentially in a circle co-axial with a low pressure turbine 2 and positioned between the low pressure turbine 2 and a high pressure turbine 9.
  • Each vane 1 has an integral pinion 3 by which the vane can be turned about an axis 4 (see FIGURE 2), thereby to alter the nozzle angle.
  • the pinions 3 are mounted in a block 10 and are arranged to be turned in unison by axial movement of a piston 5 arranged co-axially of the turbine 2 and the circle of vanes 1.
  • the piston 5 is movable axially in a cylinder 6 abutting the block 10.
  • the outer periphery of the piston 5 has a plurality of outwardly-extending ribs 11 formed with axially-extending toothed rack portions 7, spaced apart circumferentially around the periphery of the piston and each drivingly engaged with a respective pinion 3.
  • Compressed air is bled from a compressor (not shown) of the gas turbine engine and is introduced through means (not shown) into the end part 8 of the cylinder 6 adjacent the head of the piston 5, thereby to cause the piston 5 to move axially within the cylinder 6.
  • the axial movement of the piston 5 will cause the pinions 3 to be turned simultaneously about their axes 4, thereby to turn the respective guide vanes 1.
  • the supply and exhaust of compressed air from the end 8 of the cylinder may be controlled by the operator of the engine or the operation may be automatic, for example to maintain the inlet temperature of the turbine 2 substantially constant.
  • the axis of turning of each vane 1 is offset chordwise of the vane from the longitudinal center-line thereof through the center of pressure, whereby the fluid loading on the vane can be used to assist or to oppose the torque applied to the vane by the pinion 3.
  • the vanes 1, the pinions 3, the piston 5, the ribs 11, the toothed rack portions 7, the block 10 and the cylinder 6 are all made from a ceramic or other non-metallic material capable of withstanding a high operating temperature, e.g., of the order of 1100" C. By using these materials, the adjustable nozzle guide vane assembly provided by this invention can be successfully used in the very hot region between the turbines 9 and 2, where adequate cooling is not practicable.
  • An adjustable nozzle guide vane assembly for a turbine of the axial flow type, the assembly including a plurality of nozzle guide vanes spaced apart circumferentially about the axis of the turbine in a circle and each mounted for turning about at an axis extending transversely to the axis of the turbine, wherein the improvement comprises a pinion carried by each vane, an axially movable operating member co-axial with the circle of vanes and a plurality of circumferentially-spaced, axially-extending toothed rack portions, carried on said operating member and each engaging a respective pinion, whereby axial movement of the operating member will turn the vanes about their respective axes, said operating member, said rack portions, said pinions and said vanes being made of a ceramic material.
  • An assembly as claimed in claim 1 in which the operating member is a piston mounted in a cylinder coaxial with and positioned radially within the circle of vanes and the piston has a skirt portion extending axially of the cylinder and formed on its outer peripheral surface with the said toothed rack portions.
  • the cylinder includes fluid inlet means arranged to receive compressed air bled from a compresosr of a gas turbine engine of which the turbine is a component.

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  • 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)
US643454A 1966-06-03 1967-06-05 Adjustable nozzle guide vane assembly for an axial flow turbine Expired - Lifetime US3392958A (en)

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
US3392958A true US3392958A (en) 1968-07-16

Family

ID=10217784

Family Applications (1)

Application Number Title Priority Date Filing Date
US643454A Expired - Lifetime US3392958A (en) 1966-06-03 1967-06-05 Adjustable nozzle guide vane assembly for an axial flow turbine

Country Status (4)

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

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4239450A (en) * 1979-05-17 1980-12-16 Buffalo Forge Company Adjusting mechanism for variable inlet vane
US4278398A (en) * 1978-12-04 1981-07-14 General Electric Company Apparatus for maintaining variable vane clearance
US4302149A (en) * 1980-02-19 1981-11-24 General Motors Corporation Ceramic vane drive joint
EP0169779A1 (de) * 1984-07-26 1986-01-29 Alsthom Einrichtung zur Regelung des Entnahmedrucks einer Entnahme-Kondensationsturbine
US5380152A (en) * 1992-11-03 1995-01-10 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Adjustable guide vane for turbines, compressors, or the like
US5704762A (en) * 1993-11-08 1998-01-06 Alliedsignal Inc. Ceramic-to-metal stator vane assembly
EP2388436A3 (de) * 2010-05-21 2013-05-08 MTU Aero Engines GmbH Leitschaufel-Verstelleinrichtung für eine Strömungsmaschine

Citations (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

Patent Citations (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

Cited By (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
EP0169779A1 (de) * 1984-07-26 1986-01-29 Alsthom Einrichtung zur Regelung des Entnahmedrucks einer Entnahme-Kondensationsturbine
US5380152A (en) * 1992-11-03 1995-01-10 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Adjustable guide vane for turbines, compressors, or the like
US5704762A (en) * 1993-11-08 1998-01-06 Alliedsignal Inc. Ceramic-to-metal stator vane assembly
EP2388436A3 (de) * 2010-05-21 2013-05-08 MTU Aero Engines GmbH Leitschaufel-Verstelleinrichtung für eine Strömungsmaschine

Also Published As

Publication number Publication date
DE1601636A1 (de) 1970-06-18
DE1601636B2 (de) 1970-11-05
CH464607A (fr) 1968-10-31
GB1119439A (en) 1968-07-10

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