EP2653666A1 - Variable Leitschaufelanordnung - Google Patents

Variable Leitschaufelanordnung Download PDF

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Publication number
EP2653666A1
EP2653666A1 EP13158889.9A EP13158889A EP2653666A1 EP 2653666 A1 EP2653666 A1 EP 2653666A1 EP 13158889 A EP13158889 A EP 13158889A EP 2653666 A1 EP2653666 A1 EP 2653666A1
Authority
EP
European Patent Office
Prior art keywords
platform
washer
spindle
guide vane
variable guide
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.)
Withdrawn
Application number
EP13158889.9A
Other languages
English (en)
French (fr)
Inventor
Peter Allford
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
Publication of EP2653666A1 publication Critical patent/EP2653666A1/de
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F05D2240/00—Components
    • F05D2240/70—Slinger plates or washers
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/434—Polyimides, e.g. AURUM

Definitions

  • the invention relates to turbine engines and variable guide vanes and / or inlet guide vanes for turbine engines in particular.
  • the rotor In a gas turbine engine having a multi-stage axial compressor the rotor is turned at high speed so that air introduced into the compressor is accelerated by the rotating blades and swept rearwards onto an adjacent row of stator vanes. Each rotor stage increases the pressure of the air passing through the stage and at final stage of the compressor the air is many times that of the inlet air pressure.
  • stator vanes In addition to converting the kinetic energy of the air into pressure the stator vanes also serve to correct the deflection given to the air by the rotor blades and to present the air at the correct angle to the next stage of the rotor blades.
  • variable stator vanes which permit the angle of one or more rows of stator vanes in a compressor to be adjusted while the engine is running in accordance with the rotational and mass flows of the engine.
  • variable inlet guide vanes typically incorporate an integral outer platform which provides for an interface between the aerofoil and also that of the outer spindle. Often known as a "penny”, these platforms are round in geometry and positioned within a counterbore incorporated into a suitable casing to provide for a continuous aerodynamic profile at the casing / penny interface as the vane rotates.
  • a non metallic thrust washer may be sandwiched between the penny and the inner base surface of the counterbore to prevent metal to metal contact.
  • the counterbore must be sufficiently robust to accommodate the penny and platform and not distort in use. With large vanes the size and depth of the counterbore significantly increases the machining time and cost of the casing. Alternative manufacturing methods, such as forging, to form the casing can exhibit high levels of distortion in manufacture.
  • a variable guide vane assembly comprising a variable guide vane having an aerofoil and a spindle at one end of the aerofoil; wherein the vane further comprises a platform having a non-circular plan positioned between the aerofoil and the spindle, the platform having a surface facing in the direction of the spindle and at least one side face; the assembly also having a washer having a circular plan with an aperture through which the spindle extends, the washer having a portion which overhangs the at least one side face.
  • the washer is supported by the platform surface and portion overhangs one or more of the side faces of the platform.
  • the plan of the washer is circular.
  • the plan of the platform may be non-circular and may be rectangular, fluted or lobed.
  • the washer may be secured to the platform by its positioning between the platform and a further component or by an interference fit between the platform and the washer.
  • Adhesive, or another coating, may be used to further secure the platform with the washer.
  • the washer is formed from plastic.
  • An exemplary plastic is polyimide.
  • the washer may be formed from metal having a surface coating.
  • variable guide vane assembly may further comprise a casing having a chamber containing the platform and the washer.
  • the chamber is stepped from a casing surface wherein a surface of the platform opposing the spindle facing surface is flush with the casing surface.
  • Fig. 1 is a schematic of a VIGV and a rotor
  • Fig. 2 is a cross-section of a VIGV mounting arrangement 10
  • Fig. 3 is a partially exploded view of a vane platform and thrust washer
  • Fig. 4 is a top view of a vane platform and thrust washer
  • Fig. 5a to 5d are plan views (5a-5b) and side views (5c-5d) of alternative washer arrangements.
  • FIG. 1 shows a schematic of a variable inlet guide vane (VIGV) or variable stator vane (VSV) 2 in relation to an associated rotor 4.
  • VIGV variable inlet guide vane
  • VSV variable stator vane
  • each individual vane in a VIGV row is supported by bearings 8, 10 at the radially inner and outer ends of the vane aerofoil section.
  • the bearings permit the VIGV to rotate or pivot about its spanwise axis 12 which is typically radial, or nearly radial, relative to the compressor or engine axis 14.
  • the angular position of the vane is controlled by an actuating lever 16, which is attached to a spigot type extension at the radially outer end of the vane.
  • the actuating lever of each vane in a row is connected to an actuating ring 18, commonly known as a unison ring which rotates about the axis of the engine 14.
  • FIG. 2 depicts the radially outer bearing arrangement 10 in more detail.
  • the vane spindle 20 is integrally formed with the vane aerofoil 22 and has a platform 24 which has at least one side face which engages a thrust washer 26.
  • the thrust washer has a circular outer profile, an inner profile that compliments the profile of the platform, and is positioned within an outwardly stepped chamber 28 in the casing 30 carrying the vane.
  • the radially inner surface of the thrust washer provides, with the inner surface of the casing and the radially inner surface of the platform, a substantially flush continuous aerodynamic profile.
  • the radially outer surface of the thrust washer engages the shoulder 32 of the stepped chamber 28 and provides a bearing surface which prevents direct engagement of the aerofoil platform with the casing.
  • the actuating lever 16 has a mount which surrounds the vane spindle 20 and has an inner profile which engages the driving teeth 40 on the spindle ( Fig. 3 ).
  • a cylindrical bush 34 separates the outer surface of the actuating lever from the casing whilst permitting the mount to rotate within the casing about the axis 12.
  • a lever retention feature e.g. a nut, screw or other mechanical fastener secures the actuating lever to the spindle.
  • the thrust washer 26 is shown in more detail in Figure 3 .
  • the platform 24 in this embodiment has a rectangular shape with an upper surface supporting the underside of the thrust washer and side walls arranged such that the longer sides of the platform engage with the inside surfaces of the washer.
  • the washer is formed of a suitably formed plastic such as polyimide or a metal provided with a suitable coating which gives an acceptable interface with the platform and / or the casing which offers a combination of low friction and low wear at all contact points with the platform or casing.
  • the upper surface of the thrust washer may be provided with one or more sections 42 which provide relief for the local overhang of the actuating lever.
  • the washer is carried by the upper surface of the platform 24 which faces the spindle.
  • facing is meant that it is the surface from which the spindle protrudes.
  • the surface may be sloped towards the spindle, rather than perpendicular as shown in Figure 3 , but it will be appreciated that this increases the depth of the platform in the axial direction and may be undesirable.
  • a top view of the vane 22, washer26 and platform 24 is shown in Figure 4 and depicts the profiles of the vane platform and the interior and exterior surface of the thrust washer.
  • the invention offers a number of advantages.
  • the overhang of the thrust washer when presented to the platform of the vane, forms a full circular aerodynamic surface at the vane interface with the casing.
  • the arrangement provides a significant reduction to the time and cost required to machine the vane by virtue of a more efficient utilisation of the aerofoil initial material envelope as machining a platform with a circular cross-section requires significantly more material.
  • the thrust washer can be made of both cheaper and lighter material which also leads to an overall reduction in the weight of the engine.
  • the depth of the washer 26 has a significantly lower profile 48 than the conventional combinations of platform and washer. Accordingly, the manufacturing costs of the casing is reduced.
  • thrust washer can also reduce the profile of the vane which allows the vane, if forged, to be manufactured from smaller stock which results in reduced manufacturing cost of the aerofoil as less material is used with reduced machining time.
  • Figure 5a and 5b are top views of alternative washer arrangements.
  • the washer has a star-shaped feature which engages a complementary star shaped platform.
  • the washer has a cross-shaped feature which engages a complementary cross shaped platform.
  • Figure 5c is a side view of an embodiment of washer which does not have a portion that engages a spindle facing surface of the platform. The washer relies upon an interference fit and / or an adhesive to secure it in position against the platform.
  • a coating can be provided on the top surface of the washer and platform to prevent damage to the casing by the platform when the vane is assembled thereto.
  • the washer has a shoulder 52 which prevents the washer from becoming detached from the platform and entering the air flow through the engine.
  • the arrangement of Figure 5d has the advantage of being more robust but is thicker than the arrangement of Figure 5c .
  • the platform 24 is shown as rectangular but may be any other appropriate shape provided the thrush washer may fit around it.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13158889.9A 2012-04-16 2013-03-13 Variable Leitschaufelanordnung Withdrawn EP2653666A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1206603.1A GB201206603D0 (en) 2012-04-16 2012-04-16 Variable stator vane arrangement

Publications (1)

Publication Number Publication Date
EP2653666A1 true EP2653666A1 (de) 2013-10-23

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13158889.9A Withdrawn EP2653666A1 (de) 2012-04-16 2013-03-13 Variable Leitschaufelanordnung

Country Status (3)

Country Link
US (1) US20130272852A1 (de)
EP (1) EP2653666A1 (de)
GB (1) GB201206603D0 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2825759A1 (de) * 2012-03-13 2015-01-21 United Technologies Corporation Verstellbare leitschaufelanordnung für einen gasturbinenmotor
EP4180635A1 (de) * 2021-11-12 2023-05-17 MTU Aero Engines AG Verstellleitschaufelanordnung einer strömungsmaschine und verfahren zur montage einer verstellleitschaufelanordnung

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170159675A1 (en) * 2015-12-03 2017-06-08 General Electric Company Closed loop cooling method for a gas turbine engine
US20180156236A1 (en) * 2016-12-02 2018-06-07 Pratt & Whitney Canada Corp. Gas turbine engine bleed configuration
BE1025470B1 (fr) * 2017-08-14 2019-03-18 Safran Aero Boosters S.A. Systeme d'aubes a calage variable de compresseur pour turbomachine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5039277A (en) * 1989-04-26 1991-08-13 Societe National D'etude Et De Construction De Moteurs D'aviation Variable stator vane with separate guide disk
US20060237100A1 (en) * 2005-04-21 2006-10-26 Snecma Plain bearing between two parts which are movable with respect to each other
US20060245916A1 (en) * 2005-04-28 2006-11-02 Snecma Stator blades, turbomachines comprising such blades and method of repairing such blades
EP1959094A2 (de) * 2007-02-13 2008-08-20 United Technologies Corporation Lochauskleidungen zur Reparatur von Schaufelsenkbohrlöchern

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1936121B1 (de) * 2006-12-22 2012-05-02 Techspace Aero Winkelfixierung für Leitschaufeln von Turbomachinen

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5039277A (en) * 1989-04-26 1991-08-13 Societe National D'etude Et De Construction De Moteurs D'aviation Variable stator vane with separate guide disk
US20060237100A1 (en) * 2005-04-21 2006-10-26 Snecma Plain bearing between two parts which are movable with respect to each other
US20060245916A1 (en) * 2005-04-28 2006-11-02 Snecma Stator blades, turbomachines comprising such blades and method of repairing such blades
EP1959094A2 (de) * 2007-02-13 2008-08-20 United Technologies Corporation Lochauskleidungen zur Reparatur von Schaufelsenkbohrlöchern

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2825759A1 (de) * 2012-03-13 2015-01-21 United Technologies Corporation Verstellbare leitschaufelanordnung für einen gasturbinenmotor
EP2825759A4 (de) * 2012-03-13 2015-03-25 United Technologies Corp Verstellbare leitschaufelanordnung für einen gasturbinenmotor
US9062560B2 (en) 2012-03-13 2015-06-23 United Technologies Corporation Gas turbine engine variable stator vane assembly
EP4180635A1 (de) * 2021-11-12 2023-05-17 MTU Aero Engines AG Verstellleitschaufelanordnung einer strömungsmaschine und verfahren zur montage einer verstellleitschaufelanordnung

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Publication number Publication date
GB201206603D0 (en) 2012-05-30
US20130272852A1 (en) 2013-10-17

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