[go: up one dir, main page]

EP1564381B1 - Actuator lever for setting the angular position of guide vanes in a turbo machine - Google Patents

Actuator lever for setting the angular position of guide vanes in a turbo machine Download PDF

Info

Publication number
EP1564381B1
EP1564381B1 EP05290139.4A EP05290139A EP1564381B1 EP 1564381 B1 EP1564381 B1 EP 1564381B1 EP 05290139 A EP05290139 A EP 05290139A EP 1564381 B1 EP1564381 B1 EP 1564381B1
Authority
EP
European Patent Office
Prior art keywords
lever
washer
control lever
control
crimping
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
EP05290139.4A
Other languages
German (de)
French (fr)
Other versions
EP1564381A1 (en
Inventor
Claude Lejars
Bruce Pontoizeau
Richard Staessen
Nicolas Triconnet
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 EP1564381A1 publication Critical patent/EP1564381A1/en
Application granted granted Critical
Publication of EP1564381B1 publication Critical patent/EP1564381B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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

Definitions

  • the present invention relates to a lever for controlling the angular setting of a blade in a turbomachine, in particular the angular setting of a rectifier in a compressor stage of the turbomachine.
  • the document FR-A1-2 793 521 discloses a control rod formed by a laminated structure.
  • Adjusting the angular setting of certain stator blades in a turbomachine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the various flight configurations.
  • This adjustment is generally carried out, for one or more rows of blades, by means of a control ring which externally surrounds the stator of the turbomachine and which is displaceable in rotation around the longitudinal axis of the stator by a motor means. such as a cylinder or an electric motor.
  • the rotation of the ring is transmitted by lever-type control levers to the blades of the row, each control lever being integral with a blade at one of its ends and carrying at its other end a pin which is engaged. in a cylindrical housing of the control ring.
  • the pin is mounted in an orifice of the end of the lever and is fixed on the lever by crimping, this operation consisting in crushing the end of the pin on the end of the lever which rests on an annular collar of the pin. This operation generates significant constraints in the portion of the lever on which the crimping of the pin is made, which weakens this part of the lever.
  • the mechanical strength of the lever being reduced by crimping the pin, cracks or cracks may appear on the lever after a certain time of operation of the turbomachine and cause the rupture of the control lever, which can cause the stop of the turbomachine and must therefore be considered a very serious incident.
  • the present invention is essentially to eliminate this risk of breaking control levers.
  • a lever for controlling the angular setting of a blade in a turbomachine said lever having a first end intended to be mounted on a blade pivot to drive it in rotation and a second end comprising a cylindrical pin of mounting on a control ring, this pin being fixed by crimping one of its ends in an orifice of the second end of the lever and having an annular collar on which is applied the second end of the lever, characterized in that a washer crimping stress distribution is interposed between the second end of the lever and the crimped end of the pin.
  • the surface of the lever is no longer in direct contact with the crimped portion of the pin and the crimping stresses are distributed over a surface of the lever which is sufficient to avoid embrittlement of the lever.
  • the washer makes it possible to distribute the crimping stresses over a sufficient surface and has the advantage of being simple and very inexpensive.
  • the washer is made of a softer material than that of the control lever. This allows the washer to absorb mechanical crimping forces by deforming plastically and effectively protect the second lever end against mechanical aggression during crimping.
  • the washer is made of a material harder than that of the control lever. This washer has less tendency to deform than in the first embodiment and better distributes crimping constraints.
  • the substantially flat annular surface of the washer, applied on the second end of the lever has a convex annular edge or bevelled at its outer periphery.
  • an advantage of the present invention is to avoid in a simple, effective and inexpensive way the risks of rupture of the control levers of the angular setting of the rectifiers of the compressor stages in a turbomachine, which could result from the crimping of the pieces at the ends of the levers.
  • each stage of the compressor comprises a row of vanes 2 mounted on the stator and a row of vanes 3 carried by the rotor.
  • the blades 2 of the stator are rectifiers whose angular orientation is adjustable using control levers 4, driven in rotation by a control ring 5 actuated by a cylinder or an electric motor.
  • Each control lever 4 is fixed by one end 6 on a radial pivot 7 of a blade 2, the pivot 7 being guided in rotation in a bearing 8 mounted in a radial orifice of the housing 9.
  • the other end 10 of the lever control 4 carries a pin 11 which is crimped on this end 10 of the control lever 4 and is guided in rotation in a cylindrical sleeve 12 of the control ring 6.
  • FIGS. 2 and 3 illustrate the crimping of a pin 11 on the end 10 of the control lever in the known art, the pin being generally made of steel and the lever made of titanium.
  • the pin Before crimping, the pin is a straight cylindrical element which has an annular collar 13 in the vicinity of one of its ends.
  • This flange 13 forms a support for the end 10 of the lever 4, which has an orifice in which is engaged the upper end 14 of the pin.
  • This end of the pin 11 comprises, above the flange 13, a cylindrical axial bore for crimping the pin on the end 10 of the lever. The crimping is accomplished by press-fitting a suitable tool into the bore to fold down and flatten the top end 14 of the pin on the end 10 of the lever as shown in FIG. figure 3 .
  • the present invention makes it possible to eliminate this risk by means of stress distribution means interposed between the crimped end of the pin and the end of the control lever 4.
  • FIGS. 4 and 5 illustrate two embodiments of these stress distribution means, which are formed of a flat washer 16, 17 with a circular contour having an axial circular orifice whose diameter is slightly greater than the diameter of the pin 11.
  • the thickness of the washer is of the order of a millimeter and the outer diameter of the washer does not exceed that of the flange 13 of the pin 11.
  • the washer 16 is a washer with two parallel and identical flat faces and is made of a softer material than that of the lever 4, that is to say of material which has a Young's modulus lower than that of the material of the lever 4, which is usually made of titanium.
  • the washer 16, for example of polymer, can deform plastically during crimping without damaging the control lever 4 and distributing the stresses on the end 10 of the lever 4.
  • the washer 17 interposed between the crimped end of the pin and the lever 4 is made of a material having a Young's modulus greater than that of the material of the control lever 4.
  • This material may be, for example, a polymer or a metal .
  • the washer 17 has a surface 18 in contact with the end 10 of the lever 4, which is formed with a convex annular edge 19 over its entire outer periphery ( figure 6 ) or with a chamfered outer edge ( figure 7 ).
  • This configuration of the washer 17 makes it possible not to create stress peaks in the lever 4 at the outer periphery of the washer, during crimping, the convex rounding 19 or the chamfer 20 to gradually release the stresses in the material of the lever 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Pivots And Pivotal Connections (AREA)
  • Control Of Turbines (AREA)

Description

La présente invention concerne un levier de commande du calage angulaire d'une aube dans une turbomachine, en particulier du calage angulaire d'un redresseur dans un étage de compresseur de la turbomachine.The present invention relates to a lever for controlling the angular setting of a blade in a turbomachine, in particular the angular setting of a rectifier in a compressor stage of the turbomachine.

Le document FR-A1-2 793 521 décrit une biellette de commande constituée par une structure lamifiée.The document FR-A1-2 793 521 discloses a control rod formed by a laminated structure.

Le document US-A-3,788,763 décrit une aube à calage variable dont une extrémité est articulée par un palier sphérique à un rivet porté par un anneau de commande.The document US Patent 3,788,763 describes a variable-pitch blade whose end is articulated by a spherical bearing to a rivet carried by a control ring.

Le réglage du calage angulaire de certaines aubes de stator dans une turbomachine est destiné à optimiser le rendement de cette turbomachine et à réduire sa consommation de carburant dans les différentes configurations de vol. Ce réglage est en général réalisé, pour une ou plusieurs rangées d'aubes, au moyen d'un anneau de commande qui entoure extérieurement le stator de la turbomachine et qui est déplaçable en rotation autour de l'axe longitudinal du stator par un moyen moteur tel qu'un vérin ou un moteur électrique. La rotation de l'anneau est transmise par des leviers de commande du type biellette aux aubes de la rangée, chaque levier de commande étant solidaire d'une aube à l'une de ses extrémités et portant à son autre extrémité un pion qui est engagé dans un logement cylindrique de l'anneau de commande.Adjusting the angular setting of certain stator blades in a turbomachine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the various flight configurations. This adjustment is generally carried out, for one or more rows of blades, by means of a control ring which externally surrounds the stator of the turbomachine and which is displaceable in rotation around the longitudinal axis of the stator by a motor means. such as a cylinder or an electric motor. The rotation of the ring is transmitted by lever-type control levers to the blades of the row, each control lever being integral with a blade at one of its ends and carrying at its other end a pin which is engaged. in a cylindrical housing of the control ring.

Le pion est monté dans un orifice de l'extrémité du levier et est fixé sur le levier par sertissage, cette opération consistant à écraser l'extrémité du pion sur l'extrémité du levier qui repose sur une collerette annulaire du pion. Cette opération engendre des contraintes importantes dans la partie du levier sur laquelle est réalisé le sertissage du pion, ce qui fragilise cette partie du levier.The pin is mounted in an orifice of the end of the lever and is fixed on the lever by crimping, this operation consisting in crushing the end of the pin on the end of the lever which rests on an annular collar of the pin. This operation generates significant constraints in the portion of the lever on which the crimping of the pin is made, which weakens this part of the lever.

Lors du réglage du calage angulaire des aubes, le levier de commande est soumis à des forces de flexion à son extrémité portant le pion et le pion est soumis à des forces de torsion.When adjusting the angular setting of the blades, the lever of control is subjected to bending forces at its end bearing the pin and the pin is subjected to torsional forces.

La résistance mécanique du levier étant diminuée par le sertissage du pion, des fissures ou criques peuvent apparaître sur le levier au bout d'un certain temps de fonctionnement de la turbomachine et provoquer la rupture du levier de commande, ce qui peut causer l'arrêt de la turbomachine et doit donc être considéré comme un incident très grave.The mechanical strength of the lever being reduced by crimping the pin, cracks or cracks may appear on the lever after a certain time of operation of the turbomachine and cause the rupture of the control lever, which can cause the stop of the turbomachine and must therefore be considered a very serious incident.

La présente invention a essentiellement pour but de supprimer ce risque de rupture des leviers de commande.The present invention is essentially to eliminate this risk of breaking control levers.

Elle propose pour cela un levier de commande du calage angulaire d'une aube dans une turbomachine, ledit levier ayant une première extrémité destinée à être montée sur un pivot d'aube pour l'entraîner en rotation et une seconde extrémité comportant un pion cylindrique de montage sur un anneau de commande, ce pion étant fixé par sertissage d'une de ses extrémités dans un orifice de la seconde extrémité du levier et comportant une collerette annulaire sur laquelle est appliquée la seconde extrémité du levier, caractérisé en ce qu'une rondelle de répartition de contraintes de sertissage est interposée entre la seconde extrémité du levier et l'extrémité sertie du pion.It proposes for this purpose a lever for controlling the angular setting of a blade in a turbomachine, said lever having a first end intended to be mounted on a blade pivot to drive it in rotation and a second end comprising a cylindrical pin of mounting on a control ring, this pin being fixed by crimping one of its ends in an orifice of the second end of the lever and having an annular collar on which is applied the second end of the lever, characterized in that a washer crimping stress distribution is interposed between the second end of the lever and the crimped end of the pin.

Ainsi, lors du sertissage du pion sur le levier, la surface du levier n'est plus en contact direct avec la partie sertie du pion et les contraintes de sertissage sont réparties sur une surface du levier qui est suffisante pour éviter une fragilisation du levier.Thus, during the crimping of the pin on the lever, the surface of the lever is no longer in direct contact with the crimped portion of the pin and the crimping stresses are distributed over a surface of the lever which is sufficient to avoid embrittlement of the lever.

La rondelle permet de répartir les contraintes de sertissage sur une surface suffisante et présente l'avantage d'être simple et très peu coûteuse.The washer makes it possible to distribute the crimping stresses over a sufficient surface and has the advantage of being simple and very inexpensive.

Dans un premier mode de réalisation de l'invention, la rondelle est réalisée en un matériau plus souple que celui du levier de commande. Cela permet à la rondelle d'absorber les efforts mécaniques de sertissage en se déformant plastiquement et de protéger efficacement la seconde extrémité de levier contre toute agression mécanique lors du sertissage.In a first embodiment of the invention, the washer is made of a softer material than that of the control lever. This allows the washer to absorb mechanical crimping forces by deforming plastically and effectively protect the second lever end against mechanical aggression during crimping.

Dans un autre mode de réalisation de l'invention, la rondelle est réalisée en un matériau plus dur que celui du levier de commande. Cette rondelle a moins tendance à se déformer que dans le premier mode de réalisation et répartit mieux les contraintes de sertissage.In another embodiment of the invention, the washer is made of a material harder than that of the control lever. This washer has less tendency to deform than in the first embodiment and better distributes crimping constraints.

Pour réduire dans ce cas les risques d'agression de la seconde extrémité du levier, la surface annulaire sensiblement plane de la rondelle, appliquée sur la seconde extrémité du levier, présente un bord annulaire convexe ou chanfreiné à sa périphérie extérieure.To reduce in this case the risk of aggression of the second end of the lever, the substantially flat annular surface of the washer, applied on the second end of the lever, has a convex annular edge or bevelled at its outer periphery.

De manière générale, un avantage de la présente invention est d'éviter de façon simple, efficace et peu coûteuse les risques de rupture des leviers de commande du calage angulaire des redresseurs des étages de compresseur dans une turbomachine, qui pourraient résulter des sertissages des pions aux extrémités des leviers.In general, an advantage of the present invention is to avoid in a simple, effective and inexpensive way the risks of rupture of the control levers of the angular setting of the rectifiers of the compressor stages in a turbomachine, which could result from the crimping of the pieces at the ends of the levers.

D'autres avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue schématique partielle illustrant le montage d'un levier de commande du calage angulaire d'un redresseur dans un étage de compresseur d'une turbomachine, selon la technique antérieure ;
  • les figures 2 et 3 sont des vues schématiques de côté illustrant le sertissage du pion sur le levier de commande dans la technique antérieure ;
  • la figure 4 est une vue schématique partielle d'un premier mode de réalisation du levier de commande selon l'invention ;
  • la figure 5 est une vue schématique partielle d'un second mode de réalisation du levier de commande selon l'invention ;
  • les figures 6 et 7 sont des vues schématiques agrandies en coupe axiale de la rondelle de répartition de contraintes du second mode de réalisation de l'invention.
Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
  • the figure 1 is a partial schematic view illustrating the mounting of a lever for controlling the angular setting of a rectifier in a compressor stage of a turbomachine, according to the prior art;
  • the Figures 2 and 3 are schematic side views illustrating the crimping of the pin on the control lever in the prior art;
  • the figure 4 is a partial schematic view of a first embodiment of the control lever according to the invention;
  • the figure 5 is a partial schematic view of a second embodiment of the control lever according to the invention;
  • the Figures 6 and 7 are enlarged schematic views in axial section of the stress distribution washer of the second embodiment of the invention.

En figure 1, on a représenté une partie d'un étage 1 de compresseur haute pression d'une turbomachine, dans laquelle chaque étage du compresseur comprend une rangée d'aubes 2 montées sur le stator et une rangée d'aubes 3 portées par le rotor.In figure 1 , there is shown a portion of a stage 1 of high pressure compressor of a turbomachine, wherein each stage of the compressor comprises a row of vanes 2 mounted on the stator and a row of vanes 3 carried by the rotor.

Les aubes 2 du stator sont des redresseurs dont l'orientation angulaire est réglable à l'aide de leviers de commande 4, entraînés en rotation par un anneau 5 de commande actionné par un vérin ou un moteur électrique.The blades 2 of the stator are rectifiers whose angular orientation is adjustable using control levers 4, driven in rotation by a control ring 5 actuated by a cylinder or an electric motor.

Chaque levier de commande 4 est fixé par une extrémité 6 sur un pivot radial 7 d'une aube 2, le pivot 7 étant guidé en rotation dans un palier 8 monté dans un orifice radial du carter 9. L'autre extrémité 10 du levier de commande 4 porte un pion 11 qui est serti sur cette extrémité 10 du levier de commande 4 et est guidé en rotation dans une douille cylindrique 12 de l'anneau de commande 6.Each control lever 4 is fixed by one end 6 on a radial pivot 7 of a blade 2, the pivot 7 being guided in rotation in a bearing 8 mounted in a radial orifice of the housing 9. The other end 10 of the lever control 4 carries a pin 11 which is crimped on this end 10 of the control lever 4 and is guided in rotation in a cylindrical sleeve 12 of the control ring 6.

Un déplacement angulaire de l'anneau de commande 5 autour de son axe se traduit par une rotation des leviers 4 autour des axes des pivots 7 et par l'entraînement en rotation des aubes 2 autour de ces axes.An angular displacement of the control ring 5 about its axis results in a rotation of the levers 4 about the axes of the pivots 7 and the driving in rotation of the blades 2 around these axes.

Les figures 2 et 3 illustrent le sertissage d'un pion 11 sur l'extrémité 10 du levier de commande dans la technique connue, le pion étant généralement en acier et le levier en titane.The Figures 2 and 3 illustrate the crimping of a pin 11 on the end 10 of the control lever in the known art, the pin being generally made of steel and the lever made of titanium.

Avant sertissage, le pion est un élément cylindrique droit qui présente une collerette 13 annulaire au voisinage d'une de ses extrémités. Cette collerette 13 forme un appui pour l'extrémité 10 du levier 4, qui comporte un orifice dans lequel est engagée l'extrémité supérieure 14 du pion. Cette extrémité du pion 11 comprend, au dessus de la collerette 13, un alésage axial cylindrique servant au sertissage du pion sur l'extrémité 10 du levier. Le sertissage est réalisé par enfoncement à la presse d'un outil approprié dans l'alésage pour rabattre et aplatir l'extrémité supérieure 14 du pion sur l'extrémité 10 du levier comme représenté en figure 3.Before crimping, the pin is a straight cylindrical element which has an annular collar 13 in the vicinity of one of its ends. This flange 13 forms a support for the end 10 of the lever 4, which has an orifice in which is engaged the upper end 14 of the pin. This end of the pin 11 comprises, above the flange 13, a cylindrical axial bore for crimping the pin on the end 10 of the lever. The crimping is accomplished by press-fitting a suitable tool into the bore to fold down and flatten the top end 14 of the pin on the end 10 of the lever as shown in FIG. figure 3 .

Lors du sertissage, l'extrémité 10 du levier appliquée sur la collerette 13 de l'extrémité supérieure 14 du pion subit directement les efforts de sertissage, qui peuvent la fragiliser. En fonctionnement, lors du réglage angulaire des aubes, ces extrémités des leviers travaillent en flexion tandis que les pions travaillent en torsion, et sont soumises aux vibrations de la turbomachine, qui accentuent la fragilisation des leviers. Cela peut provoquer à la longue la rupture de l'extrémité 10 d'un levier.During crimping, the end 10 of the lever applied to the collar 13 of the upper end 14 of the pin directly undergoes the crimping forces, which can weaken it. In operation, during the angular adjustment of the blades, these ends of the levers work in flexion while the pins work in torsion, and are subject to the vibrations of the turbomachine, which accentuate the embrittlement of the levers. This may eventually cause breakage of the end of a lever.

La présente invention permet d'éliminer ce risque grâce à des moyens de répartition de contraintes interposés entre l'extrémité sertie du pion et l'extrémité 10 du levier de commande 4.The present invention makes it possible to eliminate this risk by means of stress distribution means interposed between the crimped end of the pin and the end of the control lever 4.

Les figures 4 et 5 illustrent deux modes de réalisation de ces moyens de répartition de contraintes, qui sont formés d'une rondelle plate 16, 17 à contour circulaire présentant un orifice circulaire 15 axial dont le diamètre est légèrement supérieur au diamètre du pion 11. L'épaisseur de la rondelle est de l'ordre du millimètre et le diamètre extérieur de la rondelle ne dépasse pas celui de la collerette 13 du pion 11.The Figures 4 and 5 illustrate two embodiments of these stress distribution means, which are formed of a flat washer 16, 17 with a circular contour having an axial circular orifice whose diameter is slightly greater than the diameter of the pin 11. The thickness of the washer is of the order of a millimeter and the outer diameter of the washer does not exceed that of the flange 13 of the pin 11.

Dans le mode de réalisation de la figure 4, la rondelle 16 est une rondelle à deux faces planes parallèles et identiques et est réalisée en un matériau plus souple que celui du levier 4, c'est-à-dire en matériau qui présente un module d'Young inférieur à celui du matériau du levier 4, qui est généralement réalisé en titane. La rondelle 16, par exemple en polymère, peut se déformer plastiquement lors du sertissage sans endommager le levier de commande 4 et en répartissant les contraintes sur l'extrémité 10 du levier 4.In the embodiment of the figure 4 , the washer 16 is a washer with two parallel and identical flat faces and is made of a softer material than that of the lever 4, that is to say of material which has a Young's modulus lower than that of the material of the lever 4, which is usually made of titanium. The washer 16, for example of polymer, can deform plastically during crimping without damaging the control lever 4 and distributing the stresses on the end 10 of the lever 4.

Dans un second mode de réalisation selon l'invention, représenté en figure 5, la rondelle 17 interposée entre l'extrémité sertie du pion et le levier 4 est en un matériau ayant un module d'Young supérieur à celui du matériau du levier de commande 4. Ce matériau peut être, par exemple, un polymère ou un métal. Dans ce cas, comme représenté à plus grande échelle aux figures 6 et 7, la rondelle 17 a une surface 18 en contact avec l'extrémité 10 du levier 4, qui est formée avec un bord 19 annulaire convexe sur toute sa périphérie extérieure (figure 6) ou avec un bord 20 extérieur chanfreiné (figure 7).In a second embodiment according to the invention, represented in figure 5 , the washer 17 interposed between the crimped end of the pin and the lever 4 is made of a material having a Young's modulus greater than that of the material of the control lever 4. This material may be, for example, a polymer or a metal . In this case, as shown on a larger scale Figures 6 and 7 , the washer 17 has a surface 18 in contact with the end 10 of the lever 4, which is formed with a convex annular edge 19 over its entire outer periphery ( figure 6 ) or with a chamfered outer edge ( figure 7 ).

Cette configuration de la rondelle 17 permet de ne pas créer de pics de contraintes dans le levier 4 à la périphérie extérieure de la rondelle, lors du sertissage, l'arrondi convexe 19 ou le chanfrein 20 permettant de libérer progressivement les contraintes dans le matériau du levier 4.This configuration of the washer 17 makes it possible not to create stress peaks in the lever 4 at the outer periphery of the washer, during crimping, the convex rounding 19 or the chamfer 20 to gradually release the stresses in the material of the lever 4.

Claims (9)

  1. A control lever for the pitch angle of a blade in a turbomachine, said lever (4) having a first end (6) intended to be mounted on a blade (2) pivot (7) so as to rotate it and a second end (10) comprising a cylindrical peg (11) for mounting on a control annulus (5), this peg (11) being fixed by crimping of one of its ends in an orifice of the second end (10) of the lever (4) and comprising an annular flange(13) to which is applied the second end (10) of the lever (4), characterized in that a crimping stress distribution washer (16, 17) is interposed between the second end (10) of the lever (4) and the crimped end (14) of the peg.
  2. Control lever (4) as claimed in claim 1, characterized in that the washer (16) is made of a more flexible material than that of the control lever (4).
  3. Control lever as claimed in claim 2, characterized in that the washer (16) is made of polymer.
  4. Control lever as claimed in claim 1, characterized in that the washer (17) is made of a harder material than that of the control lever (4).
  5. Control lever as claimed in claim 4, characterized in that the washer (17) is made of polymer or of metal.
  6. Control lever as claimed in claim 4 or 5, characterized in that the washer (17) comprises a substantially plane annular surface applied to the second end (10) of the lever (4) and exhibiting a convex (19) or chamfered (20) annular edge at its outer periphery.
  7. Control lever according to anyone of claims 1 to 6, characterized in that the thickness of the washer (16, 17) is of the order of a millimeter.
  8. Control lever according to anyone of claims 1 to 7, characterized in that the washer (16, 17) has an outer diameter equal to or slightly less than that of the flange (13) of the peg (14).
  9. Control lever according to one of the preceeding claims, characterized in that the lever is made of titanium and the peg (11) is made of steel.
EP05290139.4A 2004-02-05 2005-01-21 Actuator lever for setting the angular position of guide vanes in a turbo machine Expired - Lifetime EP1564381B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0401086 2004-02-05
FR0401086A FR2866058B1 (en) 2004-02-05 2004-02-05 LEVER FOR CONTROLLING THE ANGULAR SETTING OF A DAWN IN A TURBOMACHINE

Publications (2)

Publication Number Publication Date
EP1564381A1 EP1564381A1 (en) 2005-08-17
EP1564381B1 true EP1564381B1 (en) 2015-10-28

Family

ID=34684992

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290139.4A Expired - Lifetime EP1564381B1 (en) 2004-02-05 2005-01-21 Actuator lever for setting the angular position of guide vanes in a turbo machine

Country Status (7)

Country Link
US (1) US7281892B2 (en)
EP (1) EP1564381B1 (en)
JP (1) JP4806199B2 (en)
CA (1) CA2494770C (en)
FR (1) FR2866058B1 (en)
RU (1) RU2355893C2 (en)
UA (1) UA83466C2 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1722073B1 (en) * 2005-05-13 2013-01-23 BorgWarner, Inc. Variable geometry turbocharger unison ring
US9353643B2 (en) * 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
US8668444B2 (en) * 2010-09-28 2014-03-11 General Electric Company Attachment stud for a variable vane assembly of a turbine compressor
DE102013002968A1 (en) * 2013-02-22 2014-08-28 Dt Swiss Ag Impeller for at least partially muscle-powered vehicles and in particular bicycles
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

Family Cites Families (12)

* 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
US3788463A (en) * 1972-01-31 1974-01-29 Maryland Cup Corp Bundling method and article produced thereby
US3788763A (en) * 1972-11-01 1974-01-29 Gen Motors Corp Variable vanes
FR2608678B1 (en) * 1986-12-17 1991-02-08 Snecma VARIABLE SETTING BLADE CONTROL DEVICE FOR TURBOMACHINE RECTIFIER
GB8913988D0 (en) * 1989-06-17 1989-08-09 Rolls Royce Plc Improvements in or relating to control of variable stator vanes
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
RU2117826C1 (en) * 1995-03-27 1998-08-20 Акционерное общество открытого типа "А.Люлька-Сатурн" Gas-turbine engine compressor stator
JP2000210737A (en) * 1999-01-25 2000-08-02 Yuusu Kitaura:Kk Swaging method and swaging structure
FR2793521B1 (en) 1999-05-10 2005-09-23 Techlam VARIABLE CALIBRATION CONTROL ROD
FR2814206B1 (en) * 2000-09-18 2002-12-20 Snecma Moteurs VARIABLE SETTING BLADE CONTROL DEVICE
FR2835562B1 (en) * 2002-02-07 2004-07-16 Snecma Moteurs STATOR BLADE SWIVEL ARRANGEMENT IN A TURBOMACHINE
RU2219378C1 (en) * 2002-10-01 2003-12-20 Иванов Адольф Павлович Compressor stator of gas-turbine engine

Also Published As

Publication number Publication date
FR2866058B1 (en) 2006-06-02
CA2494770C (en) 2012-08-28
CA2494770A1 (en) 2005-08-05
JP4806199B2 (en) 2011-11-02
EP1564381A1 (en) 2005-08-17
UA83466C2 (en) 2008-07-25
FR2866058A1 (en) 2005-08-12
US7281892B2 (en) 2007-10-16
JP2005220907A (en) 2005-08-18
RU2005102775A (en) 2006-07-10
RU2355893C2 (en) 2009-05-20
US20050175445A1 (en) 2005-08-11

Similar Documents

Publication Publication Date Title
EP1637742B1 (en) Actuator lever for setting the angular position of guide vanes in a turbo machine.
EP1870600B1 (en) Bearing for the trunnion of a turbomachine stator vane with variable setting, corresponding stator vane and turbomachine
CA2869919C (en) Coupling of shafts using variable-profile splines
FR2915150A1 (en) ENERGY ABSORPTION DEVICE FOR MOTOR VEHICLE SEAT, ASSEMBLY AND ASSEMBLY COMPRISING THE DEVICE
EP1967695A1 (en) Turbomachine fan
EP2007995B1 (en) Pressed joint yoke for a motor vehicle steering column universal joint
FR2836186A1 (en) AXIAL FLOW FAN
EP1605139B1 (en) Turbomachine with axial retention means for the rotor
EP1564381B1 (en) Actuator lever for setting the angular position of guide vanes in a turbo machine
EP1500791B1 (en) Guiding set for the external pivot of a variable angle vane system in a turbo engine
EP2554480B1 (en) Linking device more specifically suited to providing the link between an air intake and an engine of an aircraft nacelle
EP2837557B1 (en) Device for coupling a motor-driven landing gear wheel of an aircraft
FR2922588A1 (en) Rotor disk or drum i.e. booster drum, for e.g. turbojet engine of airplane, has flange including orifice for mounting bolt, where rim of bolt cooperates with edges of reinforcement of flange for immobilizing bolt in orifice
FR3118785A1 (en) BLOCKING PART FOR ASSEMBLY OF TURBOMACHINE ELEMENTS COMPRISING FUSE MEANS AND CORRESPONDING TURBOMACHINE
EP2733340B1 (en) Threaded rod of a system for deploying a deployable propellant nozzle
EP1331402B1 (en) Stator blade control apparatus
FR2882577A1 (en) Actuating ring`s centering adjusting device for rotary blade of turbomachine, has brake shoe comprising rod with longitudinal groove, and washer comprising radial pin engaged in groove and radial slots engaged in slots of cavity of ring
EP2435686B1 (en) Part for attaching together the mobile portion of a deployable divergent nozzle of a propulsive unit and a mechanism for deploying said mobile portion
WO2010061123A1 (en) Linear actuator
FR2877059A1 (en) Connecting rod for driving variable pitch vane, has drill and opening, where rod is under form of U shaped tongue folded on itself according to single folding along transversal direction so that drill and opening are opposite to each other
EP3390228B1 (en) De-icing device and configuration method for a de-icing installation
EP3794243B1 (en) Torque transmission device with reduced friction
FR2926613A1 (en) Blower disk for e.g. turbopropeller engine of airplane, has clamps at its external periphery, and bush authorizing pivotment of platform around rod of pin, where ends of bush is in support on head of pin and each clamp during tightening nut
FR3091915A1 (en) "Metal part for an internal combustion engine and assembly comprising such a part"
EP1936125A1 (en) Turbomachine compressor

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA

17P Request for examination filed

Effective date: 20050914

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

17Q First examination report despatched

Effective date: 20080612

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150527

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602005047777

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151028

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602005047777

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20160729

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231219

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20231219

Year of fee payment: 20

Ref country code: FR

Payment date: 20231219

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20231219

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240102

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 602005047777

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20250120

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20250120