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EP1843008B1 - Aube de stator à calage variable de turbomachine - Google Patents

Aube de stator à calage variable de turbomachine Download PDF

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Publication number
EP1843008B1
EP1843008B1 EP07290419A EP07290419A EP1843008B1 EP 1843008 B1 EP1843008 B1 EP 1843008B1 EP 07290419 A EP07290419 A EP 07290419A EP 07290419 A EP07290419 A EP 07290419A EP 1843008 B1 EP1843008 B1 EP 1843008B1
Authority
EP
European Patent Office
Prior art keywords
zone
plate
pivot
blade
blade according
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.)
Active
Application number
EP07290419A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1843008A1 (fr
Inventor
Yvon Cloarec
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1843008A1 publication Critical patent/EP1843008A1/fr
Application granted granted Critical
Publication of EP1843008B1 publication Critical patent/EP1843008B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed

Definitions

  • the present invention relates to the field of turbomachines such as an axial compressor of gas turbine engine, and aims in particular stator vanes with variable pitch of the machine.
  • An articulated system such as the variable pitch stator vanes of a gas turbine engine compressor, includes moving parts relative to one another.
  • a blade 1 of variable-pitch rectifier mounted in the housing 3 of the machine.
  • the stator blade comprises a blade 12, a plate or platform 13 and a pivot rod 14 at one end.
  • the pivot 14 is housed in a bore or radial orifice formed in the wall of the casing 3 by means of different bearings. Dawn is held only by this extremity.
  • the other end retains a floating annular element 16 in which it is pivotally mounted by a second pivot 17.
  • the ring is provided with sealing means for the portion of the rotor 18 which is adjacent thereto.
  • the pivot 14 is journalled in the corresponding bore of the casing via bearings, for example a low bearing 4.
  • the platform 13 is housed in a recess shaped machined in the wall of this housing.
  • the housing wall is in radial contact with the platform 13 either directly or via a bushing or washer.
  • the upper part of the pivot 14 is retained in a high bearing 5.
  • the opposite face of the platform 13 with respect to the bearing 4 forms the base of the blade and is swept by the gases set in motion by the compressor. This face of the plate is shaped to ensure the continuity of the vein formed by the housing.
  • a nut keeps the blade in its housing and a lever actuated by appropriate control members, controls the rotation of the blade around the axis XX of the rod to put it in the required position relative to the direction gas flow.
  • the relative movements result from the sliding of the surfaces in contact with each other.
  • the blade 12 In the case of an axial compressor of gas turbine engine or of a single axial compressor of air or other gas, such as blast furnace or natural gas, the blade 12 is subjected over its entire length to the aerodynamic forces and pressure generated by the gas flow.
  • the component of these forces oriented perpendicular to the chord in the direction intrados towards extrados, passing generally by the axis of the pivot is the most important. Note, however, that in cases of major robberies the component may deviate from this axis.
  • the blade is also subjected to axial forces of static pressure directed upstream due to the pressure difference between the downstream and the upstream. The resulting force is illustrated by the arrow F in the figures.
  • the applicant also has a permanent goal to find solutions that can lighten the machine without affecting its performance and reliability. Any gain in mass improves the efficiency of the machine and reduces operating costs.
  • the turbomachine stator vane, variable pitch comprising a blade, extended on one side by a pivot by which it is rotatably mounted in a bore of the casing of the turbomachine, and a plate, between the blade and the pivot, perpendicular to the direction formed by the blade and the pivot, is characterized in that the face of the plate opposite the blade comprises a first zone and a second zone, the first zone being subjected to friction with the wall of the casing due to the transverse forces applied to the blade and the second zone being subjected in normal operation to a lower friction than the first zone, the thickness of the plate on the second zone is reduced compared to the thickness of the plate on the first zone.
  • the blades with variable pitch, in particular axial compressor, of the prior art have a plate of uniform thickness if one does not take into account the curvature and / or nonlinearity of the gas stream. So thanks to the invention we can reduce the mass of this part of the blade without impairing its functionality, namely ensure continuity of the vein and reduce leakage along the pivot.
  • the second zone of lower thickness extends practically over an arc of 60 to 120 degrees around the axis of the pivot.
  • the first zone is located on the extrados side and the second zone extends on the intrados side.
  • the second zone of reduced thickness is delimited by a thicker edge - in particular the upper face of this edge is in the extension of the upper plane surface of the plate - than the first zone so as to form a decompression chamber between the periphery of the plate and the pivot which improves the seal.
  • this edge makes it possible to form a contact in the event that the forces become reversed, in particular when compressor pumping phenomena occur.
  • this arrangement is appreciable when mounting the machine by preventing the parts from tilting too much.
  • a simple and economical way to make blades with a second zone thus fitted is to machine the plate.
  • the cavity is flat-bottomed, curved or any other shape.
  • the plate 13 is viewed from above in perspective.
  • a cavity 22A has been machined in the face of the plate facing towards the casing 3 in the second zone 22, which is not subjected to compression forces resulting from the application of the force F on the blade 12.
  • This cavity 22A has been machined here by means known per se.
  • the bottom of the cavity is flat, it could be curved if the machining head was ball-shaped. Shapes other than the one shown are possible.
  • the cavity can come from foundry, forging or metallurgy powders.
  • the cavity preferably extends over an arc, of a circle for example, of 60 to 120 degrees, advantageously corresponding to the arc underlying the zone of intense friction.
  • This cavity has the function of reducing the mass of the blade but not reducing its mechanical characteristics.
  • the resulting thickness of the plate is therefore sufficient to ensure the mechanical strength of the plate. It is observed that a border 23 has been preserved on the periphery of the plate. This border has a dual function. The first is to form a decompression chamber reducing air leakage between the vein of the turbomachine and the pivot 14 through the bore of the housing in which is housed the pivot 14.
  • the second function is to form a surface of support in the event of inversion of the forces resulting from a malfunction of the turbomachine, such as the pumping of the compressor or to simplify assembly operations.
  • the width of this border may not be constant. For example, it could be wider in an area to be strengthened.
  • its upper plane is in the plane of the plate facing the housing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP07290419A 2006-04-06 2007-04-05 Aube de stator à calage variable de turbomachine Active EP1843008B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0651243A FR2899637B1 (fr) 2006-04-06 2006-04-06 Aube de stator a calage variable de turbomachine

Publications (2)

Publication Number Publication Date
EP1843008A1 EP1843008A1 (fr) 2007-10-10
EP1843008B1 true EP1843008B1 (fr) 2009-06-17

Family

ID=37491722

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07290419A Active EP1843008B1 (fr) 2006-04-06 2007-04-05 Aube de stator à calage variable de turbomachine

Country Status (10)

Country Link
US (1) US7980815B2 (ja)
EP (1) EP1843008B1 (ja)
JP (1) JP5143465B2 (ja)
CN (1) CN101054908B (ja)
AT (1) ATE434116T1 (ja)
CA (1) CA2583850C (ja)
DE (1) DE602007001294D1 (ja)
ES (1) ES2328530T3 (ja)
FR (1) FR2899637B1 (ja)
RU (1) RU2436967C2 (ja)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009004933A1 (de) * 2009-01-16 2010-07-29 Mtu Aero Engines Gmbh Leitschaufel für einen Stator eines Turboverdichters
US9309778B2 (en) 2010-12-30 2016-04-12 Rolls-Royce North American Technologies, Inc. Variable vane for gas turbine engine
US9062560B2 (en) 2012-03-13 2015-06-23 United Technologies Corporation Gas turbine engine variable stator vane assembly
US9334751B2 (en) 2012-04-03 2016-05-10 United Technologies Corporation Variable vane inner platform damping
CN103397912B (zh) * 2013-08-19 2015-07-15 中国航空动力机械研究所 涡轮发动机转子叶片及涡轮和涡轮发动机
CN104153822B (zh) * 2014-07-22 2015-09-30 哈尔滨工程大学 一种包括叶端带有凹槽状小翼结构的可调静叶的变几何涡轮
US9784285B2 (en) * 2014-09-12 2017-10-10 Honeywell International Inc. Variable stator vane assemblies and variable stator vanes thereof having a locally swept leading edge and methods for minimizing endwall leakage therewith
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
CN104533544B (zh) * 2015-01-26 2016-01-06 成都成发科能动力工程有限公司 用于trt的静叶调节装置
DE102015110249A1 (de) * 2015-06-25 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln
DE102015110250A1 (de) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln
EP3421754B1 (en) * 2016-03-30 2021-12-01 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Variable geometry turbocharger
US10436050B2 (en) 2017-04-11 2019-10-08 United Technologies Corporation Guide vane arrangement for gas turbine engine
US11572798B2 (en) * 2020-11-27 2023-02-07 Pratt & Whitney Canada Corp. Variable guide vane for gas turbine engine
CN113623021B (zh) * 2021-07-30 2023-01-17 中国航发沈阳发动机研究所 一种变几何低压涡轮导向叶片
CN114321019A (zh) * 2021-12-27 2022-04-12 中国航发沈阳发动机研究所 一种压气机可调静子结构
CN115853599B (zh) * 2022-12-28 2025-01-07 西安鑫垚陶瓷复合材料股份有限公司 一种陶瓷基复合材料可调涡轮导向器叶片

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE496713A (ja) * 1949-07-01
US3542484A (en) * 1968-08-19 1970-11-24 Gen Motors Corp Variable vanes
US4498790A (en) * 1983-11-21 1985-02-12 United Technologies Corporation Bushing securing apparatus
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
FR2685033B1 (fr) * 1991-12-11 1994-02-11 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
US5593275A (en) * 1995-08-01 1997-01-14 General Electric Company Variable stator vane mounting and vane actuation system for an axial flow compressor of a gas turbine engine
US5622473A (en) * 1995-11-17 1997-04-22 General Electric Company Variable stator vane assembly
JPH1054206A (ja) * 1996-08-09 1998-02-24 Mitsubishi Heavy Ind Ltd 可変翼の支持軸受装置
FR2775731B1 (fr) * 1998-03-05 2000-04-07 Snecma Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison
US6209198B1 (en) * 1998-12-16 2001-04-03 General Electric Company Method of assembling a variable stator vane assembly
US6283705B1 (en) * 1999-02-26 2001-09-04 Allison Advanced Development Company Variable vane with winglet
US6682299B2 (en) * 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
US6843638B2 (en) * 2002-12-10 2005-01-18 Honeywell International Inc. Vane radial mounting apparatus
US6808364B2 (en) * 2002-12-17 2004-10-26 General Electric Company Methods and apparatus for sealing gas turbine engine variable vane assemblies
US7220098B2 (en) * 2003-05-27 2007-05-22 General Electric Company Wear resistant variable stator vane assemblies
US20050084190A1 (en) * 2003-10-15 2005-04-21 Brooks Robert T. Variable vane electro-graphitic bushing
US7112039B2 (en) * 2003-10-29 2006-09-26 United Technologies Corporation Variable vane electro-graphic thrust washer

Also Published As

Publication number Publication date
ES2328530T3 (es) 2009-11-13
CN101054908B (zh) 2010-09-08
RU2436967C2 (ru) 2011-12-20
DE602007001294D1 (de) 2009-07-30
JP2007278291A (ja) 2007-10-25
CA2583850A1 (fr) 2007-10-06
FR2899637A1 (fr) 2007-10-12
CA2583850C (fr) 2014-02-18
JP5143465B2 (ja) 2013-02-13
EP1843008A1 (fr) 2007-10-10
US20100266389A1 (en) 2010-10-21
CN101054908A (zh) 2007-10-17
US7980815B2 (en) 2011-07-19
RU2007112880A (ru) 2008-10-20
ATE434116T1 (de) 2009-07-15
FR2899637B1 (fr) 2010-10-08

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