EP1500791B1 - Führungszusammenbau für aussenliegendes Lager einer verstellbaren Schaufel einer Turbomaschine - Google Patents

Führungszusammenbau für aussenliegendes Lager einer verstellbaren Schaufel einer Turbomaschine Download PDF

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Publication number
EP1500791B1
EP1500791B1 EP04103336A EP04103336A EP1500791B1 EP 1500791 B1 EP1500791 B1 EP 1500791B1 EP 04103336 A EP04103336 A EP 04103336A EP 04103336 A EP04103336 A EP 04103336A EP 1500791 B1 EP1500791 B1 EP 1500791B1
Authority
EP
European Patent Office
Prior art keywords
pivot
bore
boss
bushing
stator
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
EP04103336A
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English (en)
French (fr)
Other versions
EP1500791A1 (de
Inventor
Jean-Baptiste Arilla
Pierre-Yves Maillard
Alain Marc Lucien Bromann
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 EP1500791A1 publication Critical patent/EP1500791A1/de
Application granted granted Critical
Publication of EP1500791B1 publication Critical patent/EP1500791B1/de
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

Definitions

  • the invention relates to the control of blades variable pitch angle in turbomachines, including turbomachines for aeronautics. It applies in particular to the control of the air inlet guide vanes in the turbomachine compressors called variable pitch angle vanes.
  • Known devices for controlling the variable pitch vanes in the turbomachines usually comprise a control member in the form of a ring surrounding the casing of the turbomachine and a plurality of control levers.
  • Each of these has a first end mounted on an outer pivot of a blade whose axis is that of the pivoting of the blade and a second end connected by a joint to the control ring, see for example the document US Pat. No. 3,322,587 A.
  • the synchronized modification of the angular position of the blades is thus obtained by the rotation of the ring around the axis of the turbomachine, in order to be able to follow the rotation movement of the control ring.
  • the connection between each lever and the ring comprises at least one degree of freedom in rotation about an axis directed substantially radially relative to the ring.
  • the rotational movement provided to the blades is essential to optimize the efficiency of the turbomachine and the margin to "pumping". Precision and hysteresis are very important for modern high pressure bodies in turbomachines. In other words, the attachment of the end of the control lever on the outer pivot of the blade must be very precise.
  • Figure 1 illustrates the mounting of the outer pivot 11 of a blade 10 on a boss 21 of the housing 2 of a compressor stator.
  • the outer pivot 11 is rotatably mounted in a bore 22 of the boss 21 via two bushes 5 and 6 mounted tight or sliding in the bore 22.
  • a control lever 3 fixed on the end of the outer pivot 11 by means of a nut 4 makes it possible to steer the dawn 10 in wedge.
  • the object of the invention is therefore to increase the guide height of the sleeves 5 and 6 without increasing the outer diameter of the casing 2, in order to keep the initial crankcase.
  • the main object of the invention is a system for guiding the outer pivot of a turbine engine stator variable pitch angle blade having an outer pivot intended to pivot in a bore of a predetermined length of the stator housing. of the turbomachine.
  • a single bushing is made of a material having a low coefficient of friction, the length of which is greater than that of the bore, protruding outwardly from the latter and whose inside diameter is slightly greater than outer diameter of the outer pivot and in that it comprises a metal jacket whose outer diameter is slightly greater than the inner diameter of the bore and whose inner diameter corresponds to the outer diameter of the sleeve to be placed around the latter and having an outer hook at its outer end.
  • the socket is metallic and a peripheral outer hook is provided at the end. outer of the metal jacket, so as to be a gripping element for the extraction of the sleeve.
  • FIG 2 there is the outer pivot 11 of a blade, at least its end portion and the boss 21 of the stator housing of the turbomachine.
  • the end of the outer pivot 11 has a thread 13 on which is screwed a nut 4. This tightens the driving end of the lever 3 to rotate the blade.
  • the positioning of the outer pivot 11 in the bore of the boss 21 is via a sleeve 50 which extends over the length of the boss 21 and whose inner diameter is slightly greater than the outer diameter of the outer pivot 11.
  • the sleeve 50 is made of composite material and is always in direct contact with its inner diameter with the outer diameter of the outer pivot 11. Because of the composite material which constitutes it, the coefficient of friction against another metal part is very low and a displacement relative of these two parts is favored.
  • a metal jacket 40 interposed between the bushing 50 and the boss 21 of the stator is used. This metal jacket 40 has an outside diameter slightly greater than the inside diameter of the bore of the boss 21 to allow attachment by hooping. In addition, it has an outer hook 41 at its outer end 44 which is completed by a positioning flange 42 bearing on the boss 21 of the stator.
  • the relative sliding is on the one hand between the sleeve 50 of composite material and the outer pivot 11 of the blade and on the other hand between the sleeve 50 of composite material and the metal jacket 44.
  • This system allows the extraction, by means of claw 60 penetrating under the hook 41, the sleeve 50 of composite material and the metal jacket 44 without disassembling the blade.
  • the boss 21 of the housing is protected by the metal jacket.
  • the sleeve 50 has an outer hook 51 to be driven during its extraction. Indeed, this outer hook 51 bears on the outer hook 41 of the metal jacket 40.
  • the extraction of the sleeve 50 allows its change without having to open the casing of the stator of the turbomachine.
  • the sleeve is metallic, and in particular is composed of a steel having good friction characteristics with the material of the pivot, for example a sleeve Z12CNDV12 vis-à-vis a pivot Z6NCT25.

Landscapes

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

Claims (3)

  1. Führungssystem für den außenliegenden Drehzapfen (11) einer winkelverstellbaren Statorschaufel (10) eines Turbotriebwerks, die einen außenliegenden Schaufeldrehzapfen (11) aufweist, der dazu bestimmt ist, sich in einer Bohrung (22) von bestimmter Länge in dem Statorgehäuse des Turbotriebwerks zu drehen,
    dadurch gekennzeichnet,
    dass es eine einzelne Hülse (50) aus einem Werkstoff mit geringem Reibungskoeffizienten umfasst, die länger ist als die Bohrung (22), wobei sie aus dieser herausragt, und deren Innendurchmesser etwas größer ist als der Außendurchmesser des außenliegenden Drehzapfens (11), und dass es einen Metallmantel (40) umfasst, dessen Außendurchmesser etwas größer ist als der Innendurchmesser der Bohrung, und dessen Innendurchmesser dem Außendurchmesser der Hülse (50) entspricht, so dass er um Letztere herum angeordnet werden kann, und der an seinem äußeren Ende (44) einen Außenhaken (41) aufweist.
  2. Führungssystem nach Anspruch 1,
    dadurch gekennzeichnet,
    dass die Hülse (50) aus Metall besteht und am äußeren Ende (44) des Metallmantels einen Außenhaken (51) an der Umfangslinie aufweist.
  3. Führungssystem nach Anspruch 1,
    dadurch gekennzeichnet,
    dass der Metallmantel (40) einen Positionierrand (42) aufweist, um auf einer Erhebung (21) des Statorgehäuses aufzuliegen.
EP04103336A 2003-07-17 2004-07-13 Führungszusammenbau für aussenliegendes Lager einer verstellbaren Schaufel einer Turbomaschine Expired - Lifetime EP1500791B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0350343 2003-07-17
FR0350343A FR2857692B1 (fr) 2003-07-17 2003-07-17 Systeme de guidage du pivot exterieur d'une aube a angle de calage variable, de stator de turbomachine

Publications (2)

Publication Number Publication Date
EP1500791A1 EP1500791A1 (de) 2005-01-26
EP1500791B1 true EP1500791B1 (de) 2007-05-02

Family

ID=33484736

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04103336A Expired - Lifetime EP1500791B1 (de) 2003-07-17 2004-07-13 Führungszusammenbau für aussenliegendes Lager einer verstellbaren Schaufel einer Turbomaschine

Country Status (9)

Country Link
US (1) US7214030B2 (de)
EP (1) EP1500791B1 (de)
JP (1) JP4056995B2 (de)
CA (1) CA2473819C (de)
DE (1) DE602004006197T2 (de)
ES (1) ES2285356T3 (de)
FR (1) FR2857692B1 (de)
RU (1) RU2340778C2 (de)
UA (1) UA83794C2 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2868490B1 (fr) * 2004-04-05 2006-07-28 Snecma Moteurs Sa Douille a base de ceramique pour un systeme de calage variable d'aubes de turbomachines
FR2881146B1 (fr) * 2005-01-27 2007-10-19 Snecma Moteurs Sa Procede de reparation d'une surface de frottement d'une aube a calage variable de turbomachine
US8517661B2 (en) * 2007-01-22 2013-08-27 General Electric Company Variable vane assembly for a gas turbine engine having an incrementally rotatable bushing
FR2913052B1 (fr) 2007-02-22 2011-04-01 Snecma Commande des aubes a angle de calage variable
US8215902B2 (en) * 2008-10-15 2012-07-10 United Technologies Corporation Scalable high pressure compressor variable vane actuation arm
US8858165B2 (en) * 2010-09-30 2014-10-14 Rolls-Royce Corporation Seal arrangement for variable vane
US10030533B2 (en) 2012-09-21 2018-07-24 United Technologies Corporation Flanged bushing for variable vane
FR3039226B1 (fr) 2015-07-20 2017-07-14 Snecma Etage d'aubes a calage variable pour une turbomachine
CN111288020B (zh) * 2020-02-24 2021-05-28 中国航发沈阳发动机研究所 一种压气机静子叶片联动结构
CN114251134B (zh) * 2021-12-07 2024-01-26 萍乡德博科技股份有限公司 一种汽油机涡轮增压可变截面喷嘴环

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3325087A (en) 1965-04-28 1967-06-13 David R Davis Stator casing construction for gas turbine engines
GB1083156A (en) 1965-05-17 1967-09-13 Gen Electric Improvements in control mechanism
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
US6481960B2 (en) * 2001-03-30 2002-11-19 General Electric Co. Variable gas turbine compressor vane structure with sintered-and-infiltrated bushing and washer bearings
US6767183B2 (en) * 2002-09-18 2004-07-27 General Electric Company Methods and apparatus for sealing gas turbine engine variable vane assemblies

Also Published As

Publication number Publication date
JP2005036806A (ja) 2005-02-10
US7214030B2 (en) 2007-05-08
CA2473819A1 (en) 2005-01-17
FR2857692B1 (fr) 2007-05-11
US20050036885A1 (en) 2005-02-17
EP1500791A1 (de) 2005-01-26
CA2473819C (en) 2012-08-28
RU2340778C2 (ru) 2008-12-10
DE602004006197T2 (de) 2007-12-20
ES2285356T3 (es) 2007-11-16
DE602004006197D1 (de) 2007-06-14
FR2857692A1 (fr) 2005-01-21
JP4056995B2 (ja) 2008-03-05
UA83794C2 (uk) 2008-08-26
RU2004121995A (ru) 2006-01-20

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