EP1500791B1 - Guiding set for the external pivot of a variable angle vane system in a turbo engine - Google Patents

Guiding set for the external pivot of a variable angle vane system in a turbo engine 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
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EP
European Patent Office
Prior art keywords
pivot
bore
boss
bushing
stator
Prior art date
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Active
Application number
EP04103336A
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German (de)
French (fr)
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EP1500791A1 (en
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
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SNECMA SAS
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    • 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

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  • 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)

Description

Domaine de l'inventionField of the invention

L'invention concerne la commande des aubes à angle de calage variable dans les turbomachines, notamment les turbomachines destinées à l'aéronautique. Elle s'applique en particulier à la commande des aubes directrices d'entrée d'air dans les compresseurs de turbomachines appelées aubes à angle de calage variable.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.

Art antérieur et problème poséPrior art and problem

Les dispositifs connus pour la commande des aubes à calage variable dans les turbomachines, notamment à l'entrée des compresseurs, comportent habituellement un organe de commande sous la forme d'un anneau entourant le carter de la turbomachine et une pluralité de leviers de commande. Chacun de ces derniers possède une première extrémité montée sur un pivot extérieur d'une aube dont l'axe est celui du pivotement de l'aube et une deuxième extrémité reliée, par une articulation, à l'anneau de commande voir par exemple le document US 3325087 A. La modification synchronisée de la position angulaire des aubes est donc obtenue par la rotation de l'anneau autour de l'axe de la turbomachine, afin de pouvoir suivre le mouvement de rotation de l'anneau de commande. La liaison entre chaque levier et l'anneau comprend au moins un degré de liberté en rotation autour d'un axe dirigé sensiblement radialement par rapport à l'anneau.Known devices for controlling the variable pitch vanes in the turbomachines, especially at the inlet of the compressors, 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.

Le mouvement de rotation prodigué aux aubes est indispensable pour optimiser le rendement de la turbomachine et la marge au « pompage ». La précision et l'hystérésis sont très importantes pour les corps de haute pression modernes dans les turbomachines. En d'autres termes, la fixation de l'extrémité du levier de commande sur le pivot extérieur de l'aube doit être très précise.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.

La figure 1 permet d'illustrer le montage du pivot extérieur 11 d'une aube 10 sur un bossage 21 du carter 2 d'un stator de compresseur. Le pivot extérieur 11 est monté tournant dans un alésage 22 du bossage 21 par l'intermédiaire de deux douilles 5 et 6 montées serrées ou glissantes dans l'alésage 22. Ainsi, un levier de commande 3 fixé sur l'extrémité du pivot extérieur 11 au moyen d'un écrou 4 permet d'orienter en calage l'aube 10.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. Thus, 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.

Or, on souhaite pouvoir diminuer la pression de contact entre le pivot extérieur 11 de l'aube 10 et les douilles 5 et 6, sachant qu'un espace 12 subsiste entre les deux douilles 5 et 6. Par contre, une augmentation de la hauteur de guidage du pivot extérieur 11 dans l'alésage 22 du bossage 21 entraînerait une augmentation de la hauteur de celui-ci. Une telle augmentation de hauteur du bossage 22 implique, bien évidemment, une augmentation du diamètre extérieur du carter du stator 2, donc une augmentation du coût accru du carter brut de fonderie et des usinages de celui-ci qui s'ensuivent.However, it is desired to be able to reduce the contact pressure between the outer pivot 11 of the blade 10 and the sockets 5 and 6, knowing that a space 12 remains between the two sockets 5 and 6. On the other hand, an increase in the height guiding the outer pivot 11 in the bore 22 of the boss 21 would cause an increase in the height thereof. Such an increase in the height of the boss 22 obviously involves an increase in the outer diameter of the stator housing 2, so an increase in the increased cost of the crankcase and the resulting machining thereof.

Le but de l'invention est donc d'augmenter la hauteur de guidage des douilles 5 et 6 sans augmenter le diamètre extérieur du carter 2, afin de conserver le carter brut initial.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.

Résumé de l'inventionSummary of the invention

A cet effet, l'objet principal de l'invention est un système de guidage du pivot extérieur d'une aube à angle de calage variable de stator de turbomachine possédant un pivot extérieur destiné à pivoter dans un alésage de longueur déterminée du carter du stator de la turbomachine.For this purpose, 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.

Selon l'invention, on utilise une douille unique étant en un matériau ayant un faible coefficient de frottement, dont la longueur est supérieure à celle de l'alésage, dépassant vers l'extérieur de ce dernier et dont le diamètre intérieur est légèrement supérieur au diamètre extérieur du pivot extérieur et en ce qu'il comprend une chemise métallique dont le diamètre extérieur est légèrement supérieur au diamètre intérieur de l'alésage et dont le diamètre intérieur correspond au diamètre extérieur de la douille pour être placée autour de cette dernière et possédant un crochet extérieur à son extrémité extérieure.According to the invention, 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.

Dans la réalisation préférentielle de l'invention, la douille est métallique et un crochet extérieur périphérique est prévu à l'extrémité extérieure de la chemise métallique, de manière à pouvoir constituer un élément de préhension pour l'extraction de la douille.In the preferred embodiment of the invention, 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.

Il est également avantageux de doter la chemise métallique d'un rebord de positionnement pour prendre appui sur le bossage du carter du stator.It is also advantageous to provide the metal sleeve with a positioning flange to bear on the boss of the stator housing.

Liste des figuresList of Figures

L'invention et ses différentes caractéristiques techniques seront mieux comprises à la lecture de la description suivante complétée de deux figures décrivant respectivement :

  • figure 1, en coupe, un montage de guidage selon l'art antérieur, et
  • figure 2, en coupe, la principale réalisation du système de guidage selon l'invention.
The invention and its various technical characteristics will be better understood on reading the following description supplemented by two figures respectively describing:
  • FIG. 1, in section, a guide assembly according to the prior art, and
  • Figure 2, in section, the main embodiment of the guide system according to the invention.

Description détaillée de deux réalisations de l'inventionDetailed description of two embodiments of the invention

Sur la figure 2, on retrouve le pivot extérieur 11 d'une aube, tout du moins sa partie extrême et le bossage 21 du carter du stator de la turbomachine. L'extrémité du pivot extérieur 11 possède un filetage 13 sur lequel est vissé un écrou 4. Celui-ci serre l'extrémité d'entraînement du levier 3 devant faire pivoter l'aube.In Figure 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.

Le positionnement du pivot extérieur 11 dans l'alésage du bossage 21 se fait par l'intermédiaire d'une douille 50 qui s'étend sur plus de la longueur du bossage 21 et dont le diamètre intérieur est légèrement supérieur au diamètre extérieur du pivot extérieur 11.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.

La douille 50 est en matériau composite et est toujours en contact direct par son diamètre intérieur avec le diamètre extérieur du pivot extérieur 11. Du fait du matériau composite qui la constitue, le coefficient de frottement contre une autre pièce métallique est très faible et un déplacement relatif de ces deux pièces est favorisé. On utilise une chemise métallique 40 intercalée entre la douille 50 et le bossage 21 du stator. Cette chemise métallique 40 a un diamètre extérieur légèrement supérieur au diamètre intérieur de l'alésage du bossage 21 pour permettre une fixation par frettage. De plus, elle possède un crochet extérieur 41 à son extrémité extérieure 44 qui est complétée par un rebord de positionnement 42 prenant appui sur le bossage 21 du stator. Le glissement relatif se fait d'une part entre la douille 50 en matériau composite et le pivot extérieur 11 de l'aube et d'autre part entre la douille 50 en matériau composite et la chemise métallique 44. Ce système permet l'extraction, au moyen de griffe 60 pénétrant sous le crochet 41, de la douille 50 en matériau composite et de la chemise métallique 44 sans démonter l'aube. De plus, si la douille 50 en matériau composite se dégrade, le bossage 21 du carter est protégé par la chemise métallique.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. In addition, if the sleeve 50 of composite material is degraded, the boss 21 of the housing is protected by the metal jacket.

On remarque que la douille 50 possède un crochet extérieur 51 pour pouvoir être entraînée lors de son extraction. En effet, ce crochet extérieur 51 prend appui sur le crochet extérieur 41 de la chemise métallique 40.Note that 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.

On comprend ainsi que la longueur de la portée du contact du pivot extérieur 11 par rapport au bossage 21 est prolongée.It is thus understood that the length of the contact surface of the outer pivot 11 relative to the boss 21 is extended.

L'extraction de la douille 50 permet son changement sans avoir à ouvrir le carter du stator de la turbomachine.The extraction of the sleeve 50 allows its change without having to open the casing of the stator of the turbomachine.

De plus, un tel montage permet un meilleur guidage du pivot extérieur 11 sans augmenter le diamètre du carter.In addition, such a mounting allows better guidance of the outer pivot 11 without increasing the diameter of the housing.

Dans cette première réalisation, la douille est métallique, et en particulier est composée d'un acier présentant de bonnes caractéristiques de frottement avec le matériau du pivot, par exemple une douille en Z12CNDV12 en vis-à-vis d'un pivot en Z6NCT25.In this first embodiment, 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.

Claims (3)

  1. Guide system for the outer pivot (11) of a variable stator vane (10) for a turbojet stator having an outer pivot (11) of a vane intended to pivot in a bore (22) with a determined length in the turbojet stator casing,
    characterized in that it comprises a single bushing (50) made from a material with a low coefficient of friction, for which the length is greater than the length of the bore (22), projecting outwards from the bore and for which the inside diameter is slightly greater than the outside diameter of the outer pivot (11) and in that it comprises a metallic liner (40) for which the outside diameter is slightly greater than the inside diameter of the bore and for which the inside diameter corresponds to the outside diameter of the bushing (50) so that it is placed around the bushing, and is provided with an outer hook (41) at its outer end (44).
  2. Guide system according to claim 1,
    characterized in that the bushing (50) is metallic and is provided with a peripheral outer hook (51) at the outer end (44) of the metallic liner.
  3. Guide system according to claim 1,
    characterized in that the metallic liner (40) has a positioning edge (42) to bear on a boss (21) of the stator casing.
EP04103336A 2003-07-17 2004-07-13 Guiding set for the external pivot of a variable angle vane system in a turbo engine Active EP1500791B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0350343 2003-07-17
FR0350343A FR2857692B1 (en) 2003-07-17 2003-07-17 SYSTEM FOR GUIDING THE EXTERNAL PIVOT OF A VANE WITH A VARIABLE SETTING ANGLE, TURBOMACHINE STATOR

Publications (2)

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

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ID=33484736

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04103336A Active EP1500791B1 (en) 2003-07-17 2004-07-13 Guiding set for the external pivot of a variable angle vane system in a turbo engine

Country Status (9)

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

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2868490B1 (en) * 2004-04-05 2006-07-28 Snecma Moteurs Sa CERAMIC SOCKET FOR A VARIABLE TURBOMACHINE AUBING TIMING SYSTEM
FR2881146B1 (en) 2005-01-27 2007-10-19 Snecma Moteurs Sa PROCESS FOR REPAIRING A FRICTION SURFACE OF A VANEABLE TURBOMACHINE CALIBRATION
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 (en) 2007-02-22 2011-04-01 Snecma CONTROL OF AUBES WITH VARIABLE SETTING ANGLE
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 (en) * 2015-07-20 2017-07-14 Snecma VARIABLE SHAFT OF AUBES FOR A TURBOMACHINE
CN111288020B (en) * 2020-02-24 2021-05-28 中国航发沈阳发动机研究所 Compressor stator blade linkage structure
CN114251134B (en) * 2021-12-07 2024-01-26 萍乡德博科技股份有限公司 Turbocharging variable section nozzle ring of petrol engine

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

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