EP1331402B1 - Stator blade control apparatus - Google Patents

Stator blade control apparatus Download PDF

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Publication number
EP1331402B1
EP1331402B1 EP03290058A EP03290058A EP1331402B1 EP 1331402 B1 EP1331402 B1 EP 1331402B1 EP 03290058 A EP03290058 A EP 03290058A EP 03290058 A EP03290058 A EP 03290058A EP 1331402 B1 EP1331402 B1 EP 1331402B1
Authority
EP
European Patent Office
Prior art keywords
link
pivot
recess
clamping cap
vane
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
EP03290058A
Other languages
German (de)
French (fr)
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EP1331402A1 (en
Inventor
Michel Bouru
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
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1331402A1 publication Critical patent/EP1331402A1/en
Application granted granted Critical
Publication of EP1331402B1 publication Critical patent/EP1331402B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32008—Plural distinct articulation axes
    • Y10T403/32057—Angular and linear
    • Y10T403/32073—Pivot stud slidable in elongated opening
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32114—Articulated members including static joint
    • Y10T403/32163—Articulate joint intermediate end joints
    • Y10T403/32172—Variable angle
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/50—Bridged by diverse connector
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/54—Flexible member is joint component

Definitions

  • the present invention relates to the control of blades variable pitch angle as defined in the preamble of claim 1.
  • Such a device is known from the document US-A-5,024,580 .
  • the present invention finds particular application in the field of aeronautics, in particular for controlling the angular positions of air inlet guide vanes in turbomachine compressors, such as aircraft turbomachines.
  • Known devices for controlling variable pitch vanes in a turbomachine usually comprise a control member in the form of a ring surrounding a casing of the turbomachine and a plurality of levers or links, each link having a first end connected to the turbine engine. control ring by a hinge and a second end mounted on the pivot of a respective blade.
  • the synchronized modification of the angular position of the blades is made by rotation of the ring around the axis of the turbomachine.
  • the connection between each link and the ring comprises at least one degree of freedom in rotation about an axis directed substantially radially relative to the ring.
  • the link being rigidly mounted on the pivot of the corresponding blade, the rotation of the ring induces other relative movements between the ring and the portion of the rod mounted on the pivot of the blade.
  • connection in the form of a ball or a similar part which, in addition to the rotation around a substantially radial axis relative to the ring, allows rotation about an axis having a substantially circumferential direction relative to the ring. It has also been proposed to provide a link providing an additional degree of freedom in translation in a substantially radial direction relative to the ring.
  • US 5,024,580 discloses a control device having an inverted V truncated vane pivot, a correspondingly shaped link and a clamping cap exerting a point contact on the link.
  • the present invention therefore aims to overcome such drawbacks by providing a control device using fastening means of the link which can maintain without play it on the pivot of the blade.
  • An object of the invention is also to eliminate the drive imprecision.
  • a blade control device variable pitch angle for turbomachine compressor rectifier comprising a rod, connecting means forming an articulation between a first end of the rod and a control ring, and means for fixing a second end of the rod on a pivot of a blade to be controlled, characterized in that it further comprises a radial recess formed in the pivot of the blade and intended to receive the second end of the link, the recess comprising at least one inclined plane edge with respect to a plane longitudinal median of the recess and cooperating with a corresponding inclined edge of the second end of the link, and a clamping cap applied on the second end of the rod and on which act the fastening means, the clamping cap having a surface planar inner surface providing a plane contact with the outer face of the second end of the rod on which is applied the clamping cap to maintain without play the second end of the rod on the pivot of the blade by contact between the inclined edges.
  • the second end of the rod is positioned without play on the pivot of the blade through the inclined planes made at the radial recess and the second end of the rod.
  • the immobilization of the second end of the rod on the pivot of the blade is obtained by the clamping cap, and its locking in rotation by the fastening means.
  • the precision of rotation drive between the rod and the pivot of the blade is improved.
  • a groove formed on the inner surface of the clamping cap and in which is partially engaged the second end of the rod advantageously provides an anti-rotation of the clamping cap relative to other parts.
  • the radial recess formed in the pivot of the blade advantageously has two flat inclined edges symmetrical with respect to a median longitudinal plane of the recess in order to obtain a symmetrical locking of the link on the pivot of the blade.
  • the two inclined plane edges may also be asymmetrical with respect to the median plane of the recess to provide a keying between a leading edge and a trailing edge of the rod.
  • FIG. 1 represents, in a very partial way, a part of a turbomachine, for example an airplane turbojet, provided with vanes 10 with a variable pitch angle. These vanes are, for example, guide vanes at the turbomachine compressor inlet, distributed around the axis of the turbomachine. In this Figure 1, only one blade is shown.
  • the control of the angular positions of the blades 10 is performed by a control ring 20 surrounding a casing 22 of the turbomachine (shown only partially in FIG. 1) and a plurality of links 30.
  • Each link 30 comprises a first end 32 connected to the control ring 20 by connecting means forming articulation.
  • this articulation is performed by an axis or finger 24 passing through the first end 32 of the link 30 and engaged in a housing 26 of the control ring 20.
  • a second end 34 of the rod 30 is mounted on a pivot 12 of the blade 10 by means of fixing means 40.
  • the fixing means 40 shown in FIG. 1 are conventionally formed of a screw-nut system comprising an axial threaded rod 14 secured to the pivot 12 of the blade and a clamping nut 42.
  • the fastening means may also be formed by a screw and a self-braking sleeve (not shown) implanted in the pivot 12 of the dawn if the height of the pivot of the blade allows the installation of such a socket. In this case, an orifice is made axially in the pivot of the blade for the passage of the reported screw.
  • FIGS. 2 and 3 illustrate in more detail an embodiment of a connection between rod and blade pivot in accordance with the invention.
  • a radial recess 16 delimited laterally by flat edges 16a, 16b inclined with respect to the longitudinal plane median P of the recess 16 and the rod 30.
  • the inclination angle is for example between 35 ° and 55 °.
  • the second end 34 of the rod 30 provided with an orifice 35 for the passage of the threaded rod 14 (or of the attached screw) is engaged in the radial recess 16 over a part of its thickness delimited by two lateral edges 34a, 34b inclined relative to the median longitudinal plane P of the rod.
  • the inclinations of the edges 34a, 34b correspond to those of the edges 16a, 16b of the recess 16 on which they rest.
  • a cap 44 provided with a bore 46 for the passage of the threaded rod 14 (or the screw insert) is supported on a flat outer face 36 of the second end 34 of the rod.
  • this support is provided by the planar bottom 48a of a groove 48 made radially in the cap 44 and matching the shape of the second end 34 of the rod in the portion thereof adjacent to the face 36 .
  • edges 34a, 34b are inclined symmetrically with respect to the median longitudinal plane P, as are the edges 16a, 16b. It may be otherwise. In particular, only two edges in contact, for example 34a and 16a, can be inclined, the others 34b, 16b are not.
  • position asymmetry of the inclined plane edges 16a, 16b with respect to the median plane P of the recess 16 so as to provide a keying between a leading edge and a trailing edge of the link 30
  • position asymmetry it is meant that the distance D1 (FIG. 2) between one of the plane edges 16a, 16b and the median plane P is greater or less than the distance D2 between the other plane edge 16a, 16b and the median plane P.
  • the link 30 has, at its second end 34, a portion having a greater thickness. large than that of a portion of its first end 32. This feature provides a better seat of the second end 34 of the link in the recess 16 formed in the pivot 12 of the blade.
  • the control device may also comprise a bushing 50 arranged around the pivot 12 of the blade, between the clamping cap 44 and the flange 52 of an opening of the casing 22 of the turbomachine in which is mounted the blade 10.
  • This sleeve 50 is intended to allow a centering of the pivot 12 of the blade with an anti-friction material interposed between the opening of the housing and the pivot of the blade.
  • a shim 54 for adjusting the clearance interposed between the clamping cap 44 and the sleeve 50 can then be advantageously provided to take account of any axial play between these parts.
  • the clamping cap 44 also bears at its periphery on the adjusting wedge 54.
  • an anti-friction washer 56 can be arranged between the rim 52 of the opening of the housing 22 and the base of the pivot 12 of dawn.

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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 Positive-Displacement Air Blowers (AREA)

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention concerne la commande d'aubes à angle de calage variable comme défini dans le préambule de la revendication 1. Un tel dispositif est connu du document US-A-5 024 580 . La présente invention trouve une application particulière dans le domaine de l'aéronautique, notamment pour la commande des positions angulaires d'aubes directrices d'entrée d'air dans des compresseurs de turbomachine, telles que des turbomachines d'avion.The present invention relates to the control of blades variable pitch angle as defined in the preamble of claim 1. Such a device is known from the document US-A-5,024,580 . The present invention finds particular application in the field of aeronautics, in particular for controlling the angular positions of air inlet guide vanes in turbomachine compressors, such as aircraft turbomachines.

Les dispositifs connus pour la commande d'aubes à calage variable dans une turbomachine comportent habituellement un organe de commande sous forme d'un anneau entourant un carter de la turbomachine et une pluralité de leviers ou biellettes, chaque biellette ayant une première extrémité reliée à l'anneau de commande par une articulation et une deuxième extrémité montée sur le pivot d'une aube respective.Known devices for controlling variable pitch vanes in a turbomachine usually comprise a control member in the form of a ring surrounding a casing of the turbomachine and a plurality of levers or links, each link having a first end connected to the turbine engine. control ring by a hinge and a second end mounted on the pivot of a respective blade.

La modification synchronisée de la position angulaire des aubes est réalisée par rotation de l'anneau autour de l'axe de la turbomachine. Afin de pouvoir suivre le mouvement de rotation de l'anneau, la liaison entre chaque biellette et l'anneau comprend au moins un degré de liberté en rotation autour d'un axe dirigé sensiblement radialement par rapport à l'anneau. Toutefois, la biellette étant montée rigidement sur le pivot de l'aube correspondante, la rotation de l'anneau induit d'autres mouvements relatifs entre l'anneau et la partie de la biellette montée sur le pivot de l'aube. Afin de s'accommoder de ces mouvements supplémentaires, ou d'au moins une partie d'entre eux, il est bien connu de réaliser la liaison sous forme d'une rotule ou d'une pièce analogue qui, outre la rotation autour d'un axe sensiblement radial par rapport à l'anneau, autorise une rotation autour d'un axe ayant une direction sensiblement circonférentielle par rapport à l'anneau. Il a aussi été proposé de réaliser une liaison offrant un degré de liberté supplémentaire en translation dans une direction sensiblement radiale par rapport à l'anneau. On pourra, en autres, se référer aux documents FR-A-2 608 678 ou FR-A-2 746 141 .The synchronized modification of the angular position of the blades is made by rotation of the ring around the axis of the turbomachine. In order to follow the rotational movement of the ring, the connection between each link and the ring comprises at least one degree of freedom in rotation about an axis directed substantially radially relative to the ring. However, the link being rigidly mounted on the pivot of the corresponding blade, the rotation of the ring induces other relative movements between the ring and the portion of the rod mounted on the pivot of the blade. In order to accommodate these additional movements, or at least part of them, it is well known to make the connection in the form of a ball or a similar part which, in addition to the rotation around a substantially radial axis relative to the ring, allows rotation about an axis having a substantially circumferential direction relative to the ring. It has also been proposed to provide a link providing an additional degree of freedom in translation in a substantially radial direction relative to the ring. We can, in other words, refer to the documents FR-A-2,608,678 or FR-A-2,746,141 .

On connaît également le brevet US 6,019,574 qui propose de réaliser l'articulation mécanique entre le pivot de l'aube et l'extrémité de la biellette montée sur celui-ci par un système de tenon et de mortaise : le pivot de l'aube comporte une extrémité filetée qui traverse un orifice percé dans la biellette de commande. Un écrou serré sur l'extrémité filetée du pivot permet de lier en rotation l'ensemble de ces pièces. De même, la demande de brevet européen EP 1 010 862 décrit une articulation obtenue par des ergots d'entraînement solidaires du pivot de l'aube et traversant des encoches pratiquées sur l'extrémité de la biellette montée sur le pivot. L'ensemble est également maintenu en rotation par un écrou vissé sur une extrémité filetée du pivot de l'aube.We also know the US Patent 6,019,574 which proposes to realize the mechanical articulation between the pivot of the blade and the end of the link mounted thereon by a system of tenon and mortise: the pivot of the blade has a threaded end which passes through an orifice pierced in the control rod. A nut tightened on the threaded end of the pivot makes it possible to bind all these parts in rotation. Similarly, the request for European patent EP 1 010 862 describes a joint obtained by integral drive pins of the blade pivot and through notches formed on the end of the rod mounted on the pivot. The assembly is also maintained in rotation by a nut screwed onto a threaded end of the blade pivot.

US 5,024,580 décrit un dispositif de commande ayant un pivot d'aube tronqué en V inversé, une biellette de forme correspondante et un chapeau de serrage exerçant un contact ponctuel sur la biellette. US 5,024,580 discloses a control device having an inverted V truncated vane pivot, a correspondingly shaped link and a clamping cap exerting a point contact on the link.

Toutefois, dans ces documents, la précision d'entraînement en rotation de la biellette de commande par rapport au pivot de l'aube varie de 0,4° à 0,6° en pratique courante. Cette faible précision provient du fait qu'il existe, entre les différentes pièces, des jeux dus aux tolérances d'assemblage du dispositif de commande. Un jeu s'installe notamment entre le pivot et l'extrémité de la biellette montée sur celui-ci. Il en résulte une imprécision au niveau de l'entraînement de la biellette qui est particulièrement préjudiciable au bon fonctionnement de l'ensemble.However, in these documents, the precision of rotation drive of the control rod relative to the pivot of the blade varies from 0.4 ° to 0.6 ° in common practice. This low accuracy comes from the fact that there are games between the different parts due to the assembly tolerances of the control device. A game is installed in particular between the pivot and the end of the rod mounted on it. This results in inaccuracy in the drive of the rod which is particularly detrimental to the proper functioning of the assembly.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention vise donc à pallier de tels inconvénients en proposant un dispositif de commande utilisant des moyens de fixation de la biellette qui permettent de maintenir sans jeu celle-ci sur le pivot de l'aube. Un but de l'invention est aussi de supprimer l'imprécision d'entraînement.The present invention therefore aims to overcome such drawbacks by providing a control device using fastening means of the link which can maintain without play it on the pivot of the blade. An object of the invention is also to eliminate the drive imprecision.

A cet effet, il est prévu un dispositif de commande d'aube à angle de calage variable pour redresseur de compresseur de turbomachine, comportant une biellette, des moyens de liaison formant articulation entre une première extrémité de la biellette et un anneau de commande, et des moyens de fixation d'une deuxième extrémité de la biellette sur un pivot d'une aube à commander, caractérisé en ce qu'il comporte en outre un évidement radial pratiqué dans le pivot de l'aube et destiné à recevoir la deuxième extrémité de la biellette, l'évidement comportant au moins un bord plan incliné par rapport à un plan longitudinal médian de l'évidement et coopérant avec un bord incliné correspondant de la deuxième extrémité de la biellette, et un chapeau de serrage appliqué sur la deuxième extrémité de la biellette et sur lequel agissent les moyens de fixation, le chapeau de serrage comportant une surface interne plane assurant un contact plan avec la face externe de la deuxième extrémité de la biellette sur laquelle est appliqué le chapeau de serrage pour maintenir sans jeu la deuxième extrémité de la biellette sur le pivot de l'aube par contact entre les bords inclinés.For this purpose, there is provided a blade control device variable pitch angle for turbomachine compressor rectifier, comprising a rod, connecting means forming an articulation between a first end of the rod and a control ring, and means for fixing a second end of the rod on a pivot of a blade to be controlled, characterized in that it further comprises a radial recess formed in the pivot of the blade and intended to receive the second end of the link, the recess comprising at least one inclined plane edge with respect to a plane longitudinal median of the recess and cooperating with a corresponding inclined edge of the second end of the link, and a clamping cap applied on the second end of the rod and on which act the fastening means, the clamping cap having a surface planar inner surface providing a plane contact with the outer face of the second end of the rod on which is applied the clamping cap to maintain without play the second end of the rod on the pivot of the blade by contact between the inclined edges.

De la sorte, la deuxième extrémité de la biellette est positionnée sans jeu sur le pivot de l'aube grâce aux plans inclinés réalisés au niveau de l'évidement radial et de la deuxième extrémité de la biellette. L'immobilisation de la deuxième extrémité de la biellette sur le pivot de l'aube est obtenue par le chapeau de serrage, et son blocage en rotation par les moyens de fixation. Ainsi, la précision d'entraînement en rotation entre la biellette et le pivot de l'aube est améliorée.In this way, the second end of the rod is positioned without play on the pivot of the blade through the inclined planes made at the radial recess and the second end of the rod. The immobilization of the second end of the rod on the pivot of the blade is obtained by the clamping cap, and its locking in rotation by the fastening means. Thus, the precision of rotation drive between the rod and the pivot of the blade is improved.

Une rainure pratiquée sur la surface interne du chapeau de serrage et dans laquelle est partiellement engagée la deuxième extrémité de la biellette permet d'assurer avantageusement une anti-rotation du chapeau de serrage par rapport aux autres pièces.A groove formed on the inner surface of the clamping cap and in which is partially engaged the second end of the rod advantageously provides an anti-rotation of the clamping cap relative to other parts.

L'évidement radial pratiqué dans le pivot de l'aube présente avantageusement deux bords plans inclinés symétriques par rapport à un plan longitudinal médian de l'évidement afin d'obtenir un blocage symétrique de la biellette sur le pivot de l'aube. Les deux bords plans inclinés peuvent également être asymétriques par rapport au plan médian de l'évidement afin d'assurer un détrompage entre un bord d'attaque et un bord de fuite de la biellette.The radial recess formed in the pivot of the blade advantageously has two flat inclined edges symmetrical with respect to a median longitudinal plane of the recess in order to obtain a symmetrical locking of the link on the pivot of the blade. The two inclined plane edges may also be asymmetrical with respect to the median plane of the recess to provide a keying between a leading edge and a trailing edge of the rod.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue en coupe longitudinale d'un dispositif de commande selon l'invention ;
  • la figure 2 est une vue en coupe selon le plan II-II de la figure 1 ; et
  • la figure 3 est une vue en perspective et en écorché du dispositif de commande de la figure 1.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • Figure 1 is a longitudinal sectional view of a control device according to the invention;
  • Figure 2 is a sectional view along the plane II-II of Figure 1; and
  • FIG. 3 is a perspective and cutaway view of the control device of FIG. 1.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

La figure 1 représente, de façon très partielle, une partie de turbomachine, par exemple d'un turboréacteur d'avion, munie d'aubes 10 à angle de calage variable. Ces aubes sont par exemple des aubes directrices en entrée de compresseur de turbomachine, réparties autour de l'axe de la turbomachine. Sur cette figure 1, seule une aube est représentée.FIG. 1 represents, in a very partial way, a part of a turbomachine, for example an airplane turbojet, provided with vanes 10 with a variable pitch angle. These vanes are, for example, guide vanes at the turbomachine compressor inlet, distributed around the axis of the turbomachine. In this Figure 1, only one blade is shown.

De façon bien connue, la commande des positions angulaires des aubes 10 est réalisée par un anneau de commande 20 entourant un carter 22 de la turbomachine (montré seulement partiellement sur la figure 1) et une pluralité de biellettes 30. Chaque biellette 30 comporte une première extrémité 32 reliée à l'anneau de commande 20 par des moyens de liaison formant articulation. Par exemple, cette articulation est réalisée par un axe ou doigt 24 traversant la première extrémité 32 de la biellette 30 et engagé dans un logement 26 de l'anneau de commande 20.In a well known manner, the control of the angular positions of the blades 10 is performed by a control ring 20 surrounding a casing 22 of the turbomachine (shown only partially in FIG. 1) and a plurality of links 30. Each link 30 comprises a first end 32 connected to the control ring 20 by connecting means forming articulation. For example, this articulation is performed by an axis or finger 24 passing through the first end 32 of the link 30 and engaged in a housing 26 of the control ring 20.

Une deuxième extrémité 34 de la biellette 30 est montée sur un pivot 12 de l'aube 10 par l'intermédiaire de moyens de fixation 40. Les moyens de fixation 40 représentés sur la figure 1 sont classiquement formés d'un système vis-écrou comportant une tige filetée axiale 14 solidaire du pivot 12 de l'aube et un écrou de serrage 42. Les moyens de fixation peuvent également être réalisés par une vis rapportée et une douille auto-freinante (non représentées) implantée dans le pivot 12 de l'aube si la hauteur du pivot de l'aube permet la pose d'une telle douille. Dans ce cas, un orifice est pratiqué axialement dans le pivot de l'aube pour le passage de la vis rapportée.A second end 34 of the rod 30 is mounted on a pivot 12 of the blade 10 by means of fixing means 40. The fixing means 40 shown in FIG. 1 are conventionally formed of a screw-nut system comprising an axial threaded rod 14 secured to the pivot 12 of the blade and a clamping nut 42. The fastening means may also be formed by a screw and a self-braking sleeve (not shown) implanted in the pivot 12 of the dawn if the height of the pivot of the blade allows the installation of such a socket. In this case, an orifice is made axially in the pivot of the blade for the passage of the reported screw.

Les figures 2 et 3 illustrent plus en détail un mode de réalisation d'une liaison entre biellette et pivot d'aube conformément à l'invention.Figures 2 and 3 illustrate in more detail an embodiment of a connection between rod and blade pivot in accordance with the invention.

A la face supérieure 12a du pivot 12 de l'aube 10 d'où fait saillie la tige filetée 14, est formé un évidement radial 16 délimité latéralement par des bords plans 16a, 16b inclinés par rapport au plan longitudinal médian P de l'évidement 16 et de la biellette 30. L'angle d'inclinaison est par exemple compris entre 35° et 55°.At the upper face 12a of the pivot 12 of the blade 10 from which protrudes the threaded rod 14, is formed a radial recess 16 delimited laterally by flat edges 16a, 16b inclined with respect to the longitudinal plane median P of the recess 16 and the rod 30. The inclination angle is for example between 35 ° and 55 °.

La deuxième extrémité 34 de la biellette 30 munie d'un orifice 35 pour le passage de la tige filetée 14 (ou de la vis rapportée) est engagée dans l'évidement radial 16 sur une partie de son épaisseur délimitée par deux bords latéraux 34a, 34b inclinés par rapport au plan longitudinal médian P de la biellette. Les inclinaisons des bords 34a, 34b correspondent à celles des bords 16a, 16b de l'évidement 16 sur lesquels ils s'appuient.The second end 34 of the rod 30 provided with an orifice 35 for the passage of the threaded rod 14 (or of the attached screw) is engaged in the radial recess 16 over a part of its thickness delimited by two lateral edges 34a, 34b inclined relative to the median longitudinal plane P of the rod. The inclinations of the edges 34a, 34b correspond to those of the edges 16a, 16b of the recess 16 on which they rest.

Un chapeau 44 muni d'un perçage 46 pour le passage de la tige filetée 14 (ou de la vis rapportée) s'appuie sur une face externe plane 36 de la deuxième extrémité 34 de la biellette. Dans l'exemple illustré, cet appui est réalisé par le fond plan 48a d'une rainure 48 pratiquée radialement dans le chapeau 44 et épousant la forme de la deuxième extrémité 34 de la biellette dans la partie de celle-ci adjacente à la face 36.A cap 44 provided with a bore 46 for the passage of the threaded rod 14 (or the screw insert) is supported on a flat outer face 36 of the second end 34 of the rod. In the illustrated example, this support is provided by the planar bottom 48a of a groove 48 made radially in the cap 44 and matching the shape of the second end 34 of the rod in the portion thereof adjacent to the face 36 .

L'effort de serrage axial exercé par l'écrou 42 (ou par la vis rapportée) sur le chapeau 44 et transmis par le contact plan entre les surfaces planes 36, 48a maintient les bords inclinés 34a, 34b de la biellette 30 contre les bords inclinés 16a, 16b de l'évidement 16 de sorte qu'une liaison sans jeu en rotation est établie entre la biellette 30 et le pivot 12 de l'aube.The axial clamping force exerted by the nut 42 (or the attached screw) on the cap 44 and transmitted by the plane contact between the flat surfaces 36, 48a maintains the inclined edges 34a, 34b of the link 30 against the edges inclined 16a, 16b of the recess 16 so that a connection without play in rotation is established between the rod 30 and the pivot 12 of the blade.

Dans l'exemple illustré, les bords 34a, 34b sont inclinés symétriquement par rapport au plan longitudinal médian P, de même que les bords 16a, 16b. Il pourra en être autrement. En particulier, seuls deux bords en contact, par exemple 34a et 16a, peuvent être inclinés, les autres 34b, 16b ne l'étant pas.In the example shown, the edges 34a, 34b are inclined symmetrically with respect to the median longitudinal plane P, as are the edges 16a, 16b. It may be otherwise. In particular, only two edges in contact, for example 34a and 16a, can be inclined, the others 34b, 16b are not.

Par ailleurs, il peut avantageusement exister une asymétrie de position des bords plans inclinés 16a, 16b par rapport au plan médian P de l'évidement 16 afin d'assurer un détrompage entre un bord d'attaque et un bord de fuite de la biellette 30. Par asymétrie de position, on entend que la distance D1 (figure 2) entre l'un des bords plans 16a, 16b et le plan médian P est supérieure ou inférieure à la distance D2 entre l'autre bord plan 16a, 16b et le plan médian P.Furthermore, it can advantageously exist a position asymmetry of the inclined plane edges 16a, 16b with respect to the median plane P of the recess 16 so as to provide a keying between a leading edge and a trailing edge of the link 30 By position asymmetry, it is meant that the distance D1 (FIG. 2) between one of the plane edges 16a, 16b and the median plane P is greater or less than the distance D2 between the other plane edge 16a, 16b and the median plane P.

On remarquera également que la biellette 30 présente, au niveau de sa deuxième extrémité 34, une partie ayant une épaisseur plus grande que celle d'une partie de sa première extrémité 32. Cette caractéristique permet d'obtenir une meilleure assise de la deuxième extrémité 34 de la biellette dans l'évidement 16 pratiqué dans le pivot 12 de l'aube.It will also be noted that the link 30 has, at its second end 34, a portion having a greater thickness. large than that of a portion of its first end 32. This feature provides a better seat of the second end 34 of the link in the recess 16 formed in the pivot 12 of the blade.

Le dispositif de commande selon l'invention peut également comporter une douille 50 disposée autour du pivot 12 de l'aube, entre le chapeau de serrage 44 et le rebord 52 d'une ouverture du carter 22 de la turbomachine dans laquelle est montée l'aube 10. Cette douille 50 est destinée à permettre un centrage du pivot 12 de l'aube avec une matière anti-friction interposée entre l'ouverture du carter et le pivot de l'aube. Une cale 54 de réglage du jeu interposée entre le chapeau de serrage 44 et la douille 50 peut être alors avantageusement prévue afin de tenir compte d'un éventuel jeu axial entre ces pièces. Dans ce cas, le chapeau de serrage 44 s'appuie également à sa périphérie sur la cale de réglage 54. De plus, une rondelle anti-friction 56 peut être disposée entre le rebord 52 de l'ouverture du carter 22 et la base du pivot 12 de l'aube.The control device according to the invention may also comprise a bushing 50 arranged around the pivot 12 of the blade, between the clamping cap 44 and the flange 52 of an opening of the casing 22 of the turbomachine in which is mounted the blade 10. This sleeve 50 is intended to allow a centering of the pivot 12 of the blade with an anti-friction material interposed between the opening of the housing and the pivot of the blade. A shim 54 for adjusting the clearance interposed between the clamping cap 44 and the sleeve 50 can then be advantageously provided to take account of any axial play between these parts. In this case, the clamping cap 44 also bears at its periphery on the adjusting wedge 54. In addition, an anti-friction washer 56 can be arranged between the rim 52 of the opening of the housing 22 and the base of the pivot 12 of dawn.

Claims (10)

  1. A device for controlling a variable-angle vane for a stator of a turbomachine compressor, the device comprising a link (30), connection means (24, 26) forming a hinge between a first end (32) of the link and a control ring (20), and fixing means (40) for fixing a second end (34) of the link on a pivot (12) of a vane (10) to be controlled,
    the device being characterised in that it further comprises:
    .a radial recess (16) formed in the vane pivot for receiving the second end (34) of the link (30), said recess having at least one plane edge (16a, 16b) inclined relative to a longitudinal midplane (P) of the recess (16) and of the link (30) and co-operating with a corresponding inclined edge (34a, 34b) of the second end of the link; and
    .a clamping cap (44) bearing against the second end of the link and on which the fixing means (40) act, said clamping cap having a plane inside surface (48a) providing plane contact with the outside face (36) of the second end of the link against which said clamping cap bears in order to maintain the second end (34) of the link (30) against the vane pivot (12) without slack by means of contact between said inclined edges.
  2. A device according to claim 1, characterised in that the radial recess (16) formed in the vane pivot (12) has two inclined plane edges (16a, 16b) that are symmetrical about the longitudinal midplane (P) of the recess.
  3. A device according to claim 1, characterised in that the radial recess (16) formed in the vane pivot (12) presents two inclined plane edges (16a, 16b) that are asymmetrical about the longitudinal midplane (P) of the recess.
  4. A device according to any one of the preceding claims, characterised in that the inside surface (48a) of the clamping cap (44) has a groove (48) that is complementary in shape to the outside face (36) of the second end (34) of the link (30) against which said clamping cap bears.
  5. A device according to any one of the preceding claims, characterised in that, at its second end (34), the link (30) presents a portion of thickness that is greater than the thickness of its first end (32).
  6. A device according to any one of the preceding claims, characterised in that it further comprises a bushing (50) placed around the vane pivot (12) for centring the vane pivot in an opening in a casing (22).
  7. A device according to claim 6, characterised in that it further comprises a shim (54) interposed between the clamping cap (44) and the bushing (50).
  8. A device according to claim 7, characterised in that the clamping cap (44) also bears at its periphery against the shim (54).
  9. A turbomachine compressor stator including a plurality of control devices for variable-angle vanes according to any one of the preceding claims.
  10. A turbomachine including a device for controlling a variable-angle vane according to any one of the preceding claims.
EP03290058A 2002-01-29 2003-01-10 Stator blade control apparatus Expired - Lifetime EP1331402B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0201022 2002-01-29
FR0201022A FR2835294B1 (en) 2002-01-29 2002-01-29 VANE VARIABLE SETTING ANGLE DRIVE DEVICE WITH GAMELESS LINK

Publications (2)

Publication Number Publication Date
EP1331402A1 EP1331402A1 (en) 2003-07-30
EP1331402B1 true EP1331402B1 (en) 2007-10-31

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Family Applications (1)

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EP03290058A Expired - Lifetime EP1331402B1 (en) 2002-01-29 2003-01-10 Stator blade control apparatus

Country Status (9)

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US (1) US6796767B2 (en)
EP (1) EP1331402B1 (en)
JP (1) JP4073794B2 (en)
CA (1) CA2418233C (en)
DE (1) DE60317119T2 (en)
ES (1) ES2292916T3 (en)
FR (1) FR2835294B1 (en)
RU (1) RU2295655C2 (en)
UA (1) UA79734C2 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008124758A1 (en) * 2007-04-10 2008-10-16 Elliott Company Centrifugal compressor having adjustable inlet guide vanes
US8414248B2 (en) 2008-12-30 2013-04-09 Rolls-Royce Corporation Variable geometry vane
IT1401664B1 (en) * 2010-08-31 2013-08-02 Nuova Pignone S R L CENTERING DEVICE AND GUIDE RING SYSTEM.
GB201711582D0 (en) * 2017-07-19 2017-08-30 Rolls Royce Plc Unison ring assembly
CN109986386B (en) * 2019-05-13 2024-03-15 福建省华银铝业有限公司 Elevator brake pad processing device and processing method
CN116907436B (en) * 2023-09-12 2023-11-14 沈阳华钛实业有限公司 Aeroengine blade detection device and detection method thereof

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US2842305A (en) * 1955-11-01 1958-07-08 Gen Electric Compressor stator assembly
DE2253030A1 (en) * 1972-10-28 1974-05-09 Sljusarew DEVICE FOR BLADE ADJUSTMENT OF THE CONTROL UNIT OF A FLOW MACHINE
DE2810240C2 (en) * 1978-03-09 1985-09-26 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Adjustable grille for turbines with axial flow, in particular high-pressure turbines for gas turbine engines
FR2599785B1 (en) * 1986-06-04 1990-10-12 Snecma VARIABLE SETTING AIR INTAKE DIRECTOR FOR TURBOJET
GB8913988D0 (en) * 1989-06-17 1989-08-09 Rolls Royce Plc Improvements in or relating to control of variable stator vanes
FR2696208B1 (en) * 1992-09-30 1994-11-10 Snecma Dawn with variable setting.
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
US6146093A (en) * 1998-12-16 2000-11-14 General Electric Company Variable vane seal and washer
FR2814206B1 (en) * 2000-09-18 2002-12-20 Snecma Moteurs VARIABLE SETTING BLADE CONTROL DEVICE

Also Published As

Publication number Publication date
DE60317119T2 (en) 2008-08-07
CA2418233C (en) 2011-05-31
US20030143066A1 (en) 2003-07-31
ES2292916T3 (en) 2008-03-16
UA79734C2 (en) 2007-07-25
FR2835294B1 (en) 2004-04-16
DE60317119D1 (en) 2007-12-13
CA2418233A1 (en) 2003-07-29
FR2835294A1 (en) 2003-08-01
US6796767B2 (en) 2004-09-28
EP1331402A1 (en) 2003-07-30
JP4073794B2 (en) 2008-04-09
JP2003227494A (en) 2003-08-15
RU2295655C2 (en) 2007-03-20

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