EP1331402A1 - Stator blade control apparatus - Google Patents

Stator blade control apparatus Download PDF

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Publication number
EP1331402A1
EP1331402A1 EP03290058A EP03290058A EP1331402A1 EP 1331402 A1 EP1331402 A1 EP 1331402A1 EP 03290058 A EP03290058 A EP 03290058A EP 03290058 A EP03290058 A EP 03290058A EP 1331402 A1 EP1331402 A1 EP 1331402A1
Authority
EP
European Patent Office
Prior art keywords
link
pivot
blade
recess
clamping cap
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.)
Granted
Application number
EP03290058A
Other languages
German (de)
French (fr)
Other versions
EP1331402B1 (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 Moteurs SA
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Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
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 angle blades variable setting. It finds a particular application in the field aeronautics, especially for controlling angular positions air inlet guide vanes in turbomachine compressors, such as aircraft turbomachines.
  • Known devices for controlling wedging vanes variable in a turbomachine usually include a control 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 control ring by a articulation and a second end mounted on the pivot of a blade respectively.
  • Synchronized modification of the angular position of the blades is produced by rotation of the ring around the axis of the turbomachine.
  • the link between each link and the ring includes at least one degree of freedom in rotation about an axis directed substantially radially with respect to the ring.
  • the link being rigidly mounted on the pivot of the corresponding dawn, the rotation of the ring induces other movements relative between the ring and the part of the rod mounted on the pivot dawn.
  • connection in the form of a ball joint or the like which, in addition to rotation around a substantially radial axis relative to the ring, allows a rotation about an axis having a substantially circumferential direction relative to the ring. It has also been proposed to make a connection offering an additional degree of freedom in translation in a substantially radial direction relative to the ring.
  • the present invention therefore aims to overcome such drawbacks by proposing a control device using fixing means of the link which allow it to be held without play on the pivot of dawn.
  • An object of the invention is also to remove the imprecision drive.
  • variable setting angle for compressor rectifier turbomachine comprising a rod, connecting means forming articulation between a first end of the link and a ring of control, 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 made in the pivot of the blade and intended to receive the second end of the link, the recess having at least one plane edge inclined with respect to a plane median longitudinal of the recess and cooperating with an inclined edge matching the second end of the link, and a hat tightening applied to the second end of the link and on which the fixing means act, the clamping cap comprising a internal surface ensuring flat contact with the external face of the second end of the link on which the cap is applied tightening to keep the second end of the link without play on the pivot of the blade by contact between the inclined edges.
  • the second end of the link is positioned no play on the dawn pivot thanks to the inclined planes made at level of the radial recess and of the second end of the link.
  • the immobilization of the second end of the link on the pivot of the blade is obtained by the clamping cap, and its blocking in rotation by the fixing means.
  • the precision of rotation drive between the link and the pivot of the blade is improved.
  • a groove on the inner surface of the hat tightening and in which the second end is partially engaged of the link advantageously ensures anti-rotation of the tightening cap compared to other parts.
  • the radial recess in the pivot of the blade presents advantageously two edges inclined planes symmetrical with respect to a median longitudinal plane of the recess in order to obtain a blockage symmetrical of the rod on the pivot of the blade.
  • the two flat edges inclined can also be asymmetrical with respect to the median plane of the recess to ensure a polarization between a leading edge and a trailing edge of the link.
  • FIG. 1 very partially represents part of turbomachine, for example of an airplane turbojet, provided with blades 10 with variable pitch angle. These blades are for example blades turbomachine compressor input guidelines, distributed around of the axis of the turbomachine. In this figure 1, only one blade is represented.
  • the control of angular positions blades 10 is produced by a control ring 20 surrounding a casing 22 of the turbomachine (shown only partially on the Figure 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 a joint.
  • this joint is produced by an axis or finger 24 passing through the first end 32 of the rod 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 fastening means 40 shown in Figure 1 are conventionally formed of a screw-nut system comprising an axial threaded rod 14 integral with the pivot 12 of the blade and a clamping nut 42.
  • the means of fixing can also be achieved by an attached screw and a self-locking sleeve (not shown) located in pivot 12 of the blade if the height of the blade pivot allows the fitting of such a socket. In this case, an orifice is made axially in the pivot of the blade for the passage of the attached screw.
  • Figures 2 and 3 illustrate in more detail an embodiment of a connection between link and pivot of blade according to the invention.
  • a radial recess 16 delimited laterally by planar edges 16a, 16b inclined relative to the longitudinal plane median P of the recess 16 and the connecting rod 30.
  • the angle of inclination 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 part of its thickness delimited by two lateral edges 34a, 34b inclined relative to the plane longitudinal median P of the link.
  • the inclinations of the edges 34a, 34b correspond to those of the edges 16a, 16b of the recess 16 on which they support each other.
  • this support is achieved by the flat bottom 48a of a groove 48 formed radially in the cap 44 and matching the shape of the second end 34 of the link in the part thereof adjacent to the face 36.
  • edges 34a, 34b are inclined symmetrically with respect to the median longitudinal plane P, as well as the edges 16a, 16b. It could be otherwise. In particular, only two edges in contact, for example 34a and 16a, can be inclined, the others 34b, 16b not being.
  • position asymmetry is meant that the distance D1 (FIG. 2) between one of the planar edges 16a, 16b and the plane median P is greater or less than the distance D2 between the other edge plane 16a, 16b and the median plane P.
  • the link 30 has, at level of its second end 34, a part having a thickness more as large as that of part of its first end 32. This characteristic allows better seating of the second end 34 of the link in the recess 16 formed in the pivot 12 from dawn.
  • the control device can also have a sleeve 50 disposed 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 the blade 10 is mounted.
  • This sleeve 50 is intended to allow centering of the pivot 12 of the blade with a material anti-friction interposed between the opening of the casing and the pivot of the blade.
  • a shim 54 for adjusting the clearance interposed between the clamping cap 44 and the socket 50 can then be advantageously provided in order to hold account for a possible axial clearance between these parts.
  • the hat clamp 44 is also supported at its periphery on the adjustment shim 54.
  • an anti-friction washer 56 can be disposed between the rim 52 of the opening of the casing 22 and the base of the pivot 12 of the blade.

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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)

Abstract

The control mechanism, comprising a lever (30) with a coupling member (24) at its first end (32) to engage with a control ring, has the second end (34) of the lever connected to a radial slot (16) in a blade pivot. The slot has at least one edge (16a) inclined relative to its lengthwise median plane and co-operating with a matching inclined edge (34a) on the second end of the lever. The mechanism has a locking cap (44) applied to the second end of the lever, having an inner surface (48a) that ensures a flat contact with the outer surface of the second end of the lever and ensures its clearance-free contact with the inclined edges of the pivot.

Description

Arrière-plan de l'inventionInvention background

La présente invention concerne la commande d'aubes à angle de calage variable. Elle 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 angle blades variable setting. It finds a particular application in the field aeronautics, especially for controlling angular positions 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 wedging vanes variable in a turbomachine usually include a control 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 control ring by a articulation and a second end mounted on the pivot of a blade respectively.

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. Synchronized modification of the angular position of the blades is produced by rotation of the ring around the axis of the turbomachine. In order to be able to follow the rotational movement of the ring, the link between each link and the ring includes at least one degree of freedom in rotation about an axis directed substantially radially with respect to the ring. However, the link being rigidly mounted on the pivot of the corresponding dawn, the rotation of the ring induces other movements relative between the ring and the part of the rod mounted on the pivot dawn. In order to accommodate these additional movements, or at least some of them, it is well known to make the connection in the form of a ball joint or the like which, in addition to rotation around a substantially radial axis relative to the ring, allows a rotation about an axis having a substantially circumferential direction relative to the ring. It has also been proposed to make a connection offering an additional degree of freedom in translation in a substantially radial direction relative to the ring. We can, in others, refer to documents FR-A-2 608 678 or FR-A-2 746 141.

On connaít 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'entraínement 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 US Patent 6,019,574 which proposes make the mechanical joint between the pivot of the blade and the end of the rod mounted thereon by a tenon and mortise system: the pivot of the blade has a threaded end which passes through a drilled orifice in the control rod. A nut tightened on the threaded end of the pivot allows to link in rotation all of these parts. Likewise, the European patent application EP 1 010 862 describes a joint obtained by drive pins integral with the pivot of the blade and passing through notches made on the end of the rod mounted on the pivot. The assembly is also kept in rotation by a nut screwed on a threaded end of the blade pivot.

Toutefois, dans ces documents, la précision d'entraínement 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'entraínement de la biellette qui est particulièrement préjudiciable au bon fonctionnement de l'ensemble.However, in these documents, the precision of training in rotation of the control rod relative to the pivot of the blade varies from 0.4 ° to 0.6 ° in current practice. This low precision comes from the fact that there are clearances between the different parts due to tolerances assembly of the control device. A game is installed in particular between the pivot and the end of the link mounted thereon. The result inaccuracy in the drive of the link which is particularly detrimental to the proper functioning of the whole.

Objet et résumé de l'inventionSubject 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'entraínement.The present invention therefore aims to overcome such drawbacks by proposing a control device using fixing means of the link which allow it to be held without play on the pivot of dawn. An object of the invention is also to remove the imprecision drive.

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 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, a blade control device is provided. variable setting angle for compressor rectifier turbomachine, comprising a rod, connecting means forming articulation between a first end of the link and a ring of control, 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 made in the pivot of the blade and intended to receive the second end of the link, the recess having at least one plane edge inclined with respect to a plane median longitudinal of the recess and cooperating with an inclined edge matching the second end of the link, and a hat tightening applied to the second end of the link and on which the fixing means act, the clamping cap comprising a internal surface ensuring flat contact with the external face of the second end of the link on which the cap is applied tightening to keep the second end of the link without play 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'entraínement en rotation entre la biellette et le pivot de l'aube est améliorée.In this way, the second end of the link is positioned no play on the dawn pivot thanks to the inclined planes made at level of the radial recess and of the second end of the link. The immobilization of the second end of the link on the pivot of the blade is obtained by the clamping cap, and its blocking in rotation by the fixing means. Thus, the precision of rotation drive between the link 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 on the inner surface of the hat tightening and in which the second end is partially engaged of the link advantageously ensures anti-rotation of the tightening cap compared 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 in the pivot of the blade presents advantageously two edges inclined planes symmetrical with respect to a median longitudinal plane of the recess in order to obtain a blockage symmetrical of the rod on the pivot of the blade. The two flat edges inclined can also be asymmetrical with respect to the median plane of the recess to ensure a polarization between a leading edge and a trailing edge of the link.

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 characteristics and advantages of the present invention will emerge from the description given below, with reference to the appended drawings which illustrate an embodiment thereof devoid of any 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 in 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 very partially represents part of turbomachine, for example of an airplane turbojet, provided with blades 10 with variable pitch angle. These blades are for example blades turbomachine compressor input guidelines, distributed around of the axis of the turbomachine. In this figure 1, only one blade is represented.

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.As is well known, the control of angular positions blades 10 is produced by a control ring 20 surrounding a casing 22 of the turbomachine (shown only partially on the Figure 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 a joint. For example, this joint is produced by an axis or finger 24 passing through the first end 32 of the rod 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 fastening means 40 shown in Figure 1 are conventionally formed of a screw-nut system comprising an axial threaded rod 14 integral with the pivot 12 of the blade and a clamping nut 42. The means of fixing can also be achieved by an attached screw and a self-locking sleeve (not shown) located in pivot 12 of the blade if the height of the blade pivot allows the fitting of such a socket. In this case, an orifice is made axially in the pivot of the blade for the passage of the attached 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 link and pivot of blade according to 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 planar edges 16a, 16b inclined relative to the longitudinal plane median P of the recess 16 and the connecting rod 30. The angle of inclination 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 part of its thickness delimited by two lateral edges 34a, 34b inclined relative to the plane longitudinal median P of the link. The inclinations of the edges 34a, 34b correspond to those of the edges 16a, 16b of the recess 16 on which they support each other.

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 rod threaded 14 (or attached screw) rests on a flat external face 36 of the second end 34 of the link. In the example shown, this support is achieved by the flat bottom 48a of a groove 48 formed radially in the cap 44 and matching the shape of the second end 34 of the link in the part 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 tightening force exerted by the nut 42 (or by the screw reported) on the cap 44 and transmitted by the flat contact between the flat surfaces 36, 48a maintains the inclined edges 34a, 34b of the rod 30 against the inclined edges 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 dawn.

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 illustrated, the edges 34a, 34b are inclined symmetrically with respect to the median longitudinal plane P, as well as the edges 16a, 16b. It could be otherwise. In particular, only two edges in contact, for example 34a and 16a, can be inclined, the others 34b, 16b not being.

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, there may advantageously be an asymmetry of position of the edges inclined planes 16a, 16b relative to the median plane P of the recess 16 in order to ensure a polarization between a leading edge and a trailing edge of the rod 30. By position asymmetry is meant that the distance D1 (FIG. 2) between one of the planar edges 16a, 16b and the plane median P is greater or less than the distance D2 between the other edge plane 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 level of its second end 34, a part having a thickness more as large as that of part of its first end 32. This characteristic allows better seating of the second end 34 of the link in the recess 16 formed in the pivot 12 from dawn.

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 can also have a sleeve 50 disposed 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 the blade 10 is mounted. This sleeve 50 is intended to allow centering of the pivot 12 of the blade with a material anti-friction interposed between the opening of the casing and the pivot of the blade. A shim 54 for adjusting the clearance interposed between the clamping cap 44 and the socket 50 can then be advantageously provided in order to hold account for a possible axial clearance between these parts. In this case, the hat clamp 44 is also supported at its periphery on the adjustment shim 54. In addition, an anti-friction washer 56 can be disposed between the rim 52 of the opening of the casing 22 and the base of the pivot 12 of the blade.

Claims (10)

Dispositif de commande d'aube à angle de calage variable pour redresseur de compresseur de turbomachine, comportant une biellette (30), des moyens de liaison (24, 26) formant articulation entre une première extrémité (32) de la biellette et un anneau de commande (20), et des moyens de fixation (40) d'une deuxième extrémité (34) de la biellette sur un pivot (12) d'une aube (10) à commander,
   caractérisé en ce qu'il comporte en outre un évidement radial (16) pratiqué dans le pivot de l'aube et destiné à recevoir la deuxième extrémité (34) de la biellette (30), ledit évidement comportant au moins un bord plan (16a, 16b) incliné par rapport à un plan longitudinal médian (P) de l'évidement et coopérant avec un bord incliné correspondant (34a, 34b) de la deuxième extrémité de la biellette, et un chapeau de serrage (44) appliqué sur la deuxième extrémité de la biellette et sur lequel agissent les moyens de fixation (40), ledit chapeau de serrage comportant une surface interne (48a) assurant un contact plan avec la face externe (36) de la deuxième extrémité de la biellette sur laquelle est appliqué ledit chapeau de serrage pour maintenir sans jeu la deuxième extrémité (34) de la biellette (30) sur le pivot (12) de l'aube par contact entre lesdits bords inclinés. Variable pitch angle vane control device for a turbomachine compressor rectifier, comprising a link (30), connection means (24, 26) forming an articulation between a first end (32) of the link and a ring control (20), and means (40) for fixing a second end (34) of the link to a pivot (12) of a blade (10) to be controlled,
characterized in that it further comprises a radial recess (16) formed in the pivot of the blade and intended to receive the second end (34) of the rod (30), said recess comprising at least one plane edge (16a, 16b) inclined relative to a plane longitudinal median (P) of the recess and cooperating with a corresponding inclined edge (34a, 34b) of the second end of the link, and a clamping cap (44) applied to the second end of the link and on which the fixing means (40) act, said clamping cap having an internal surface (48a) ensuring a flat contact with the external face (36) of the second end of the link on which said clamping cap is applied to hold the second end (34) of the link (30) on the pivot (12) of the blade without contact between said inclined edges. Dispositif selon la revendication 1, caractérisé en ce que l'évidement radial (16) pratiqué dans le pivot (12) de l'aube présente deux bords plans inclinés (16a, 16b) symétriques par rapport au plan longitudinal médian (P) de l'évidement.Device according to claim 1, characterized in that the radial recess (16) formed in the pivot (12) of the blade has two inclined planar edges (16a, 16b) symmetrical with respect to the median longitudinal plane (P) of l recess. Dispositif selon la revendication 1, caractérisé en ce que l'évidement radial (16) pratiqué dans le pivot (12) de l'aube présente deux bords plans inclinés (16a, 16b) asymétriques par rapport au plan longitudinal médian (P) de l'évidement.Device according to claim 1, characterized in that the radial recess (16) made in the pivot (12) of the blade has two inclined planar edges (16a, 16b) asymmetrical with respect to the median longitudinal plane (P) of l recess. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que la surface interne (48a) du chapeau de serrage (44) comporte une rainure (48) de forme complémentaire à la face externe (36) de la deuxième extrémité (34) de la biellette (30) sur laquelle est appliqué ledit chapeau de serrage.Device according to any one of the preceding claims, characterized in that the internal surface (48a) of the clamping cap (44) has a groove (48) of complementary shape to the external face (36) of the second end (34) of the rod (30) on which said clamping cap is applied. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que la biellette (30) présente, au niveau de sa deuxième extrémité (34), une partie ayant une épaisseur plus grande que celle de sa première extrémité (32).Device according to any one of the preceding claims, characterized in that the link (30) has, at its second end (34), a part having a thickness greater than that of its first end (32). Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il comporte en outre une douille (50) disposée autour du pivot (12) de l'aube et destinée à permettre un centrage du pivot de l'aube dans une ouverture d'un carter (22).Device according to any one of the preceding claims, characterized in that it further comprises a bush (50) disposed around the pivot (12) of the blade and intended to allow centering of the pivot of the blade in an opening a housing (22). Dispositif selon la revendication 6, caractérisé en ce qu'il comporte en outre une cale de réglage (54) interposée entre le chapeau de serrage (44) et la douille (50).Device according to claim 6, characterized in that it further comprises an adjustment shim (54) interposed between the clamping cap (44) and the sleeve (50). Dispositif selon la revendication 7, caractérisé en ce le chapeau de serrage (44) s'appuie également à sa périphérie sur la cale de réglage (54).Device according to claim 7, characterized in that the clamping cap (44) also bears at its periphery on the adjustment shim (54). Dispositif de commande d'aube à angle de calage variable pour redresseur de compresseur de turbomachine, comportant une biellette (30), des moyens de liaison (24, 26) formant articulation entre une première extrémité (32) de la biellette et un anneau de commande (20), et des moyens de fixation (40) d'une deuxième extrémité (34) de la biellette sur un pivot (12) d'une aube (10) à commander,
   caractérisé en ce qu'il comporte en outre un évidement radial (16) pratiqué dans le pivot de l'aube et destiné à recevoir la deuxième extrémité (34) de la biellette, ledit évidement comportant au moins un bord plan (16a, 16b) incliné par rapport à un plan longitudinal médian (P) de l'évidement et coopérant avec un bord incliné correspondant (34a, 34b) de la deuxième extrémité de la biellette, et un chapeau de serrage (44) appliqué sur la deuxième extrémité de la biellette et sur lequel agissent les moyens de fixation (40), ledit chapeau de serrage comportant, au niveau d'une surface interne (48a), une rainure (48) de forme complémentaire à la partie adjacente à la face externe (36) de la deuxième extrémité de la biellette sur laquelle est appliqué ledit chapeau de serrage pour maintenir sans jeu la deuxième extrémité (34) de la biellette (30) sur le pivot (12) de l'aube par contact entre lesdits bords inclinés. Variable pitch angle vane control device for a turbomachine compressor rectifier, comprising a link (30), connection means (24, 26) forming an articulation between a first end (32) of the link and a ring control (20), and means (40) for fixing a second end (34) of the link to a pivot (12) of a blade (10) to be controlled,
characterized in that it further comprises a radial recess (16) formed in the pivot of the blade and intended to receive the second end (34) of the link, said recess comprising at least one plane edge (16a, 16b) inclined relative to a median longitudinal plane ( P) of the recess and cooperating with a corresponding inclined edge (34a, 34b) of the second end of the link, and a clamping cap (44) applied to the second end of the link and on which the fixing means (40) act, said clamping cap comprising, at an internal surface (48a), a groove (48) of complementary shape to the part adjacent to the external face (36) of the second end of the link on which said tightening cap is applied to hold the second end (34) of the link (30) on the pivot (12) without play ) of the blade by contact between said inclined edges. Redresseur de compresseur de turbomachine comportant une pluralité de dispositifs de commande d'aube à angle de calage variable selon l'une quelconque des revendications précédentes.Turbomachine compressor rectifier comprising a plurality of blade angle control devices variable 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
FR0201022A FR2835294B1 (en) 2002-01-29 2002-01-29 VANE VARIABLE SETTING ANGLE DRIVE DEVICE WITH GAMELESS LINK
FR0201022 2002-01-29

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

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

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US (1) US6796767B2 (en)
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JP (1) JP4073794B2 (en)
CA (1) CA2418233C (en)
DE (1) DE60317119T2 (en)
ES (1) ES2292916T3 (en)
FR (1) FR2835294B1 (en)
RU (1) RU2295655C2 (en)
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Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010523898A (en) * 2007-04-10 2010-07-15 エリオット・カンパニー Centrifugal compressor with variable 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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2842305A (en) * 1955-11-01 1958-07-08 Gen Electric Compressor stator assembly
US4314791A (en) * 1978-03-09 1982-02-09 Motoren- Und Turbinen-Union Munchen Gmbh Variable stator cascades for axial-flow turbines of gas turbine engines
FR2599785A1 (en) * 1986-06-04 1987-12-11 Snecma Variable-pitch air intake directing vane assembly for a jet engine
US5024580A (en) * 1989-06-17 1991-06-18 Rolls-Royce Plc Control of variable stator vanes
US5407322A (en) * 1992-09-30 1995-04-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable phase vane
EP1010862A2 (en) * 1998-12-16 2000-06-21 General Electric Company Variable vane seal and washer

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2253030A1 (en) * 1972-10-28 1974-05-09 Sljusarew DEVICE FOR BLADE ADJUSTMENT OF THE CONTROL UNIT OF A FLOW MACHINE
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
FR2814206B1 (en) * 2000-09-18 2002-12-20 Snecma Moteurs VARIABLE SETTING BLADE CONTROL DEVICE

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2842305A (en) * 1955-11-01 1958-07-08 Gen Electric Compressor stator assembly
US4314791A (en) * 1978-03-09 1982-02-09 Motoren- Und Turbinen-Union Munchen Gmbh Variable stator cascades for axial-flow turbines of gas turbine engines
FR2599785A1 (en) * 1986-06-04 1987-12-11 Snecma Variable-pitch air intake directing vane assembly for a jet engine
US5024580A (en) * 1989-06-17 1991-06-18 Rolls-Royce Plc Control of variable stator vanes
US5407322A (en) * 1992-09-30 1995-04-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable phase vane
EP1010862A2 (en) * 1998-12-16 2000-06-21 General Electric Company Variable vane seal and washer

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Publication number Publication date
CA2418233A1 (en) 2003-07-29
FR2835294B1 (en) 2004-04-16
JP2003227494A (en) 2003-08-15
US6796767B2 (en) 2004-09-28
CA2418233C (en) 2011-05-31
RU2295655C2 (en) 2007-03-20
JP4073794B2 (en) 2008-04-09
ES2292916T3 (en) 2008-03-16
DE60317119D1 (en) 2007-12-13
DE60317119T2 (en) 2008-08-07
UA79734C2 (en) 2007-07-25
US20030143066A1 (en) 2003-07-31
FR2835294A1 (en) 2003-08-01
EP1331402B1 (en) 2007-10-31

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