EP3084141B1 - Turbine engine compressor, in particular of an aeroplane turboprop or turbofan - Google Patents

Turbine engine compressor, in particular of an aeroplane turboprop or turbofan Download PDF

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Publication number
EP3084141B1
EP3084141B1 EP14827799.9A EP14827799A EP3084141B1 EP 3084141 B1 EP3084141 B1 EP 3084141B1 EP 14827799 A EP14827799 A EP 14827799A EP 3084141 B1 EP3084141 B1 EP 3084141B1
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EP
European Patent Office
Prior art keywords
control ring
compressor
hole
oblong hole
cylindrical
Prior art date
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EP14827799.9A
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German (de)
French (fr)
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EP3084141A1 (en
Inventor
Pierre-Alain Francis Claude SEBRECHT
Sébastien COCHON
Arnaud Langlois
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • 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
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/50—Control logic embodiments
    • F05D2270/58—Control logic embodiments by mechanical means, e.g. levers, gears or cams

Definitions

  • the present invention relates to a turbomachine compressor, in particular a high-pressure turboprop compressor or aircraft turbojet engine.
  • a turbomachine compressor comprises a plurality of compression stages each comprising an annular row of blades mounted on a rotor shaft and an annular row of variable-pitch stator vanes mounted at their radially outer ends on a substantially cylindrical outer casing.
  • the adjustment of the angular setting of the stator vanes in a turbomachine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the different phases of flight.
  • variable-pitch stator vanes each comprise at their radially outer end a radial pivot which is centered and guided in rotation in an orifice of the outer casing.
  • Each blade pivot is connected by a rod to a control ring which extends around the outer casing of the compressor and which is movable in rotation about the longitudinal axis of the compressor by actuating means for transmitting to the blades a rotational movement around the axes of their pivots.
  • Each link is attached to the blade pivot and has a cylindrical pin engaged in a cylindrical hole of the control ring.
  • control ring During the rotation of the control ring about its axis, it causes the pivoting rods and blades around the axis of the blade pivot.
  • the total angular range of rotation of the links is conventionally of the order of 50 to 90 °.
  • the ring is also axially movable so as to accompany the trajectory of the pieces. All the blades are then in the same angular position, for a given angular position of the control ring.
  • the flow of gas flowing into the vein passing through the high-pressure compressor is not homogeneous over its entire circumference, this flow may include pockets generating performance losses.
  • the turbomachine operates at high speed, significant forces and torques are exerted on the blades, which tends to slightly deform the control ring.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem, while avoiding a system hyperstatement, which requires having rods all having substantially the same length.
  • a turbomachine compressor in particular a turboprop or an airplane turbojet engine, comprising a stator comprising an annular housing and at least one annular row of variable-pitch vanes, each blade having a radially outer end comprising a pivot mounted in a housing orifice and connected by a connecting member to a control ring adapted to pivot axially relative to the housing, the connecting member having a first end attached to the pivot of the blade and a second end comprising a pin engaged in a hole of the control ring, characterized in that at least one of the holes of the control ring, for the engagement of the pins of the connecting members, is of oblong shape and extends in the circumferential direction so as to allow the displacement of the pin in said oblong hole, during the rotation of the control ring.
  • the oblong hole extending in the circumferential direction does not necessarily extend only in the circumferential direction, that is, in a radial plane perpendicular to the axis of the control ring. Indeed, the oblong hole can extend both in the axial direction and in the circumferential direction.
  • the pins are cylindrical.
  • the holes of the control ring for engaging the pins of the connecting members, may be of such shape that it blocks the movement of the pin in said hole.
  • the control ring comprises at least one cylindrical hole, in which is engaged a cylindrical pin of a connecting member, the diameters of the pin and the cylindrical hole being substantially identical, and at least one oblong hole. extending circumferentially, in which is engaged another cylindrical pin of another connecting member.
  • said oblong hole of the control ring has a first end located on the side of a first lateral edge of the control ring, a second end located on the side of a second lateral edge of the control ring, the two ends being connected by a curved connection zone having a point of inflection.
  • said oblong hole of the control ring extends only in the circumferential direction.
  • said oblong hole of the control ring extends obliquely with respect to the axial direction and with respect to the circumferential direction.
  • said oblong hole of the control ring has an arcuate shape.
  • said oblong hole of the control ring has a first end extending only circumferentially and located on the side of a lateral edge of the control ring, a second end s' extending only circumferentially and being located on the side of the other lateral edge of the control ring, said ends being connected by a connecting zone extending obliquely with respect to the circumferential direction and with respect to the axial direction.
  • the invention further relates to a turbomachine, such as for example a turboprop or an airplane turbojet, comprising at least one compressor of the aforementioned type.
  • a turbomachine such as for example a turboprop or an airplane turbojet, comprising at least one compressor of the aforementioned type.
  • FIG 1 represents a schematic half-view of the upstream portion of a high-pressure compressor 10 according to the prior art, in section along a plane passing through the axis of rotation 12 of the turbomachine.
  • the high-pressure compressor 10 comprises a rotor formed of disks 14, 16, 18, 20 assembled axially with each other, the rotor being supported on a bearing 22 by means of a pin 24.
  • Each disk is arranged downstream of an annular row of stator vanes 26 with variable pitch.
  • Each stator vane comprises at its radially inner and outer ends coaxial cylindrical pivots 28, 30.
  • the internal cylindrical pivot 28 extends inwardly from the stator vane 26 and is centered and guided in rotation in a cylindrical housing of an annular element of the stator, and the external cylindrical pivot 30 extends radially towards the outside. outside and is centered and guided in rotation in a cylindrical chimney 32 of a substantially cylindrical outer casing 34 of the high-pressure compressor 10.
  • the adjustment of the angular setting of the stator vanes 26 of a stage is ensured by means of rods 36 which are rotated by a control ring 38 pivotally mounted relative to the casing 34 about the axis 12.
  • the deflection total of the control ring is for example between 5 and 20 °.
  • a hydraulic cylinder 40 allows the simultaneous displacement in rotation of several control rings 38.
  • the ring 38 is for example formed of two parts 39 assembled to each other by means of bridges (not shown) attached to the ends said parts 39.
  • the links 36 are fixed at one end to the radial pivots 30 of the variable-pitch vanes 26, these pivots 30 being guided in rotation in bushes 42 mounted in the chimneys 32 of the casing 34 (FIG. figure 2 ).
  • the end of the rod attached to the blade pivot 30 is held radially on a rim 44 of the sleeve 42 by a nut 46 screwed onto the end of the pivot 30.
  • the other end of the rod 36 comprises an orifice in which is guided in rotation a radial cylindrical pin 48 mounted in a cylindrical hole 52 of the control ring 38.
  • the pins 48 are held in position by bent tabs 50 fixed to the control ring 38.
  • the control ring 38 is also axially displaceable in translation, so as to accompany the circular trajectory of the pins 48.
  • the portions 39 of the control ring 38 comprise other holes 54, 56 serving respectively for fixing the connecting members for connecting the ends of the two parts 39 of the control member 38 between them or used for the fixing centering pads coming to apply on a track formed on the outer surface of the casing.
  • control ring 38 During the rotation of the control ring 38 about its axis 12, it causes the pivoting rods 36 and vanes 26 to pivot about the axis of the pivots 28, 30 of the blades 26. All the blades 26 are located then in the same angular position, for a given angular position of the control ring 38, the rods 36 all having the same length.
  • the invention responds to this need by providing a control ring 38 for adapting the angular setting of the blades 26 individually or by group of blades 26, depending on the azimuthal positions of the blades 26 concerned or groups of blades 24 concerned.
  • FIGS. 5 and 6 illustrate a first embodiment of the invention in which part of the holes in which the cylindrical pins 48 are engaged have an oblong shape (holes 58), another part of said holes being cylindrical (holes 52) and of diameter substantially identical to that of the corresponding pawns 48.
  • the oblong holes 58 each comprise a first end 60 located on the side of a first lateral edge or upstream edge 62 of the control ring 38, a second end 64 located on the side of a second side edge or downstream edge 66 of the control ring 38, the two ends 60, 64 being connected by a curved connection zone 68 having a point of inflection.
  • the wedging angle of the blades 26 does not vary in the same way, as a function of the angular position of the control ring 38, for the blades 26 associated with the cylindrical holes 52 or for the blades 26 associated with them. to the oblong holes 58.
  • control ring 38 thus has two groups of blades 26, located in azimuthal zones different from the turbomachine, and according to different timing laws from one group to another.
  • center of the holes 52 is aligned circumferentially with one of the ends of the oblong holes 58.
  • the figure 7 illustrates a second embodiment of the invention wherein each elongate hole 58 of the control ring 38 extends only in the circumferential direction.
  • each oblong hole 58 of the control ring 38 extends obliquely with respect to the axial direction A and with respect to the circumferential direction C. More particularly, each hole oblong 58 extends rectilinearly, from upstream to downstream (i.e. from left to right at figure 8 ), in a first direction of rotation of the control ring indicated by the arrow S1, which is an opening direction of the blades 26.
  • each oblong hole 58 of the control ring 38 has a shape in an arc of circle or approaching an arc of a circle, plus especially in a quarter circle.
  • One end 70 of each oblong hole 58 is directed axially upstream, the other end 72 being directed circumferentially in a direction S2 opposite to the aforesaid direction S1, the direction S2 being a closing direction of the blades 26.
  • the figure 10 illustrates the blade registration law for blades 26 associated respectively with a cylindrical hole 52 (curve C1), with an oblong hole 58 of the figure 7 (curve C2), to an oblong hole 58 of the figure 8 (curve C3) and an oblong hole 58 of the figure 9 (curve C4).
  • the calibration laws are the curves representative of the evolution of the angular position of the blade 26 ( ⁇ aube) as a function of the angular position of the control ring 38 ( ⁇ anneau).
  • the angle ⁇ aube corresponds to the angle of the rods 36 with respect to the axis 12 of the turbomachine, by defining a straight line which passes through the center of the pivot 30 of the blade 26 and the center of the pin 48 which is inserted in the ring 38.
  • the open position corresponds to a negative angle ⁇ aube relative to the axis 12 of the turbomachine, considering that the positive direction is the trigonometric direction, and the closed position corresponds to an angle ⁇ aube positive with respect to the axis 12 of the turbomachine.
  • the angle ⁇ aube 0 corresponds to the position where the rods 36 are aligned with the axis 12 of the turbomachine.
  • the figure 11 illustrates a fifth embodiment of the invention in which each oblong hole 58 of the control ring 38 has a shape symmetrical to the shape of the oblong holes 58 of the figure 6 , with respect to a radial plane passing through the axially central zone of the control ring 38.
  • each oblong hole 58 of the control ring 38 has a first end 74 extending only circumferentially and located on the side of the upstream edge 62 of the control ring, a second end 76 extending only circumferentially and located on the side of the downstream edge 66 of the control ring 38, said ends 74, 76 being connected by a connecting zone 78 extending obliquely with respect to the circumferential direction C and with respect to the axial direction A.
  • the figure 13 illustrates a seventh embodiment of the invention in which each oblong hole 58 of the control ring 38 has a shape symmetrical to the shape of the oblong holes 58 of the figure 8 , with respect to a radial plane passing through the axially central zone of the control ring 38.
  • control ring 38 may comprise at least two types of oblong hole 58 among those described above.
  • Other forms of oblong holes 58 may also be used, provided that these oblong holes 58 extend in particular in the circumferential direction C.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

La présente invention concerne un compresseur de turbomachine, en particulier un compresseur haute-pression de turbopropulseur ou de turboréacteur d'avion.The present invention relates to a turbomachine compressor, in particular a high-pressure turboprop compressor or aircraft turbojet engine.

De façon connue, un compresseur de turbomachine comprend une pluralité d'étages de compression comportant chacun une rangée annulaire d'aubes mobiles montée sur un arbre de rotor et une rangée annulaire d'aubes de stator à calage variable montées à leurs extrémités radialement externes sur un carter externe sensiblement cylindrique.In known manner, a turbomachine compressor comprises a plurality of compression stages each comprising an annular row of blades mounted on a rotor shaft and an annular row of variable-pitch stator vanes mounted at their radially outer ends on a substantially cylindrical outer casing.

Le réglage du calage angulaire des aubes de stator dans une turbomachine est destiné à optimiser le rendement de cette turbomachine et à réduire sa consommation de carburant dans les différentes phases de vol.The adjustment of the angular setting of the stator vanes in a turbomachine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the different phases of flight.

Les aubes de stator à calage variable comprennent chacune à leur extrémité radialement externe un pivot radial qui est centré et guidé en rotation dans un orifice du carter externe. Chaque pivot d'aube est relié par une biellette à un anneau de commande qui s'étend autour du carter externe du compresseur et qui est déplaçable en rotation autour de l'axe longitudinal du compresseur par des moyens d'actionnement pour transmettre aux aubes un mouvement de rotation autour des axes de leurs pivots.The variable-pitch stator vanes each comprise at their radially outer end a radial pivot which is centered and guided in rotation in an orifice of the outer casing. Each blade pivot is connected by a rod to a control ring which extends around the outer casing of the compressor and which is movable in rotation about the longitudinal axis of the compressor by actuating means for transmitting to the blades a rotational movement around the axes of their pivots.

Chaque biellette est fixée au pivot d'aube et comporte un pion cylindrique engagé dans un trou cylindrique de l'anneau de commande.Each link is attached to the blade pivot and has a cylindrical pin engaged in a cylindrical hole of the control ring.

Lors de la rotation de l'anneau de commande autour de son axe, celui-ci entraîne le pivotement des biellettes et des aubes autour de l'axe du pivot des aubes. La plage angulaire totale de rotation des biellettes est classiquement de l'ordre de 50 à 90°. L'anneau est également déplaçable axialement de façon à accompagner la trajectoire des pions. Toutes les aubes se trouvent alors dans la même position angulaire, pour une position angulaire donnée de l'anneau de commande.During the rotation of the control ring about its axis, it causes the pivoting rods and blades around the axis of the blade pivot. The total angular range of rotation of the links is conventionally of the order of 50 to 90 °. The ring is also axially movable so as to accompany the trajectory of the pieces. All the blades are then in the same angular position, for a given angular position of the control ring.

Or, en fonction du régime de la turbomachine, il existe un besoin de pouvoir adapter le calage des aubes en fonction notamment de leur position azimutale, c'est-à-dire de la position circonférentielle de l'aube de stator dans l'étage correspondant. Les angles de calage permettant de maximiser le rendement de la turbomachine peuvent donc être différents en en fonction des positions azimutales des aubes de stator d'un même étage.However, depending on the speed of the turbomachine, there is a need to be able to adapt the setting of the blades depending in particular on their azimuth position, that is to say, the circumferential position of the stator vane in the floor corresponding. The wedging angles making it possible to maximize the efficiency of the turbomachine may therefore be different as a function of the azimuthal positions of the stator vanes of the same stage.

En effet, le flux de gaz s'écoulant dans la veine traversant le compresseur haute-pression n'est pas homogène sur toute sa circonférence, ce flux pouvant comporter des poches générant des pertes de performance. Par ailleurs, lorsque la turbomachine fonctionne à haut régime, des efforts et des couples importants sont exercés sur les aubes, ce qui a tendance à déformer légèrement l'anneau de commande.Indeed, the flow of gas flowing into the vein passing through the high-pressure compressor is not homogeneous over its entire circumference, this flow may include pockets generating performance losses. Moreover, when the turbomachine operates at high speed, significant forces and torques are exerted on the blades, which tends to slightly deform the control ring.

Les documents US 4,737,071 et EP 2 204 549 divulguent des compresseurs de turbomachine selon l'art antérieur.The documents US 4,737,071 and EP 2,204,549 disclose turbomachine compressors according to the prior art.

L'invention a notamment pour but d'apporter une solution simple, efficace et économique à ce problème, tout en évitant un hyperstatisme du système, ce qui impose d'avoir des biellettes ayant toutes sensiblement la même longueur.The invention aims in particular to provide a simple, effective and economical solution to this problem, while avoiding a system hyperstatement, which requires having rods all having substantially the same length.

A cet effet, elle propose un compresseur de turbomachine, en particulier de turbopropulseur ou de turboréacteur d'avion, comprenant un stator comportant un carter annulaire et au moins une rangée annulaire d'aubes à calage variable, chaque aube comportant une extrémité radialement externe comprenant un pivot monté dans un orifice du carter et relié par un organe de liaison à un anneau de commande apte à pivoter axialement par rapport au carter, l'organe de liaison comportant une première extrémité fixée au pivot de l'aube et une seconde extrémité comportant un pion engagé dans un trou de l'anneau de commande, caractérisé en ce que l'un au moins des trous de l'anneau de commande, servant à l'engagement des pions des organes de liaison, est de forme oblongue et s'étend dans la direction circonférentielle de façon à autoriser le déplacement du pion dans ledit trou oblong, lors de la rotation de l'anneau de commande.For this purpose, it proposes a turbomachine compressor, in particular a turboprop or an airplane turbojet engine, comprising a stator comprising an annular housing and at least one annular row of variable-pitch vanes, each blade having a radially outer end comprising a pivot mounted in a housing orifice and connected by a connecting member to a control ring adapted to pivot axially relative to the housing, the connecting member having a first end attached to the pivot of the blade and a second end comprising a pin engaged in a hole of the control ring, characterized in that at least one of the holes of the control ring, for the engagement of the pins of the connecting members, is of oblong shape and extends in the circumferential direction so as to allow the displacement of the pin in said oblong hole, during the rotation of the control ring.

De cette manière, en fonction de la forme du trou, il est possible d'adapter l'angle de calage de chaque aube, de façon individuelle ou par groupes d'aubes, tout en conservant des organes de liaison (par exemple des biellettes) ayant la même longueur. Cette adaptation permet de s'adapter à l'hétérogénéité du flux de gaz et de corriger d'éventuelles déformations à haut régime moteur.In this way, depending on the shape of the hole, it is possible to adapt the wedging angle of each blade, individually or in groups of blades, while maintaining connecting members (for example rods) having the same length. This adaptation makes it possible to adapt to the heterogeneity of the gas flow and to correct possible deformations at high engine speed.

Le trou oblong s'étendant dans la direction circonférentielle ne s'étend pas nécessairement uniquement dans la direction circonférentielle, c'est-à-dire dans un plan radial perpendiculaire à l'axe de l'anneau de commande. En effet, le trou oblong peut s'étendre à la fois dans la direction axiale et dans la direction circonférentielle.The oblong hole extending in the circumferential direction does not necessarily extend only in the circumferential direction, that is, in a radial plane perpendicular to the axis of the control ring. Indeed, the oblong hole can extend both in the axial direction and in the circumferential direction.

Selon une caractéristique de l'invention, les pions sont cylindriques.According to one characteristic of the invention, the pins are cylindrical.

En outre, l'un au moins des trous de l'anneau de commande, servant à l'engagement des pions des organes de liaison, peut être de forme telle qu'il bloque le déplacement du pion dans ledit trou. Selon l'invention, l'anneau de commande comprend au moins un trou cylindrique, dans lequel est engagé un pion cylindrique d'un organe de liaison, les diamètres du pion et du trou cylindrique étant sensiblement identiques, et au moins un trou oblong s'étendant circonférentiellement, dans lequel est engagé un autre pion cylindrique d'un autre organe de liaison.In addition, at least one of the holes of the control ring, for engaging the pins of the connecting members, may be of such shape that it blocks the movement of the pin in said hole. According to the invention, the control ring comprises at least one cylindrical hole, in which is engaged a cylindrical pin of a connecting member, the diameters of the pin and the cylindrical hole being substantially identical, and at least one oblong hole. extending circumferentially, in which is engaged another cylindrical pin of another connecting member.

Selon une première forme de réalisation de l'invention, ledit trou oblong de l'anneau de commande comporte une première extrémité située du côté d'un premier bord latéral de l'anneau de commande, une seconde extrémité située du côté d'un second bord latéral de l'anneau de commande, les deux extrémités étant reliées par une zone de liaison courbe présentant un point d'inflexion.According to a first embodiment of the invention, said oblong hole of the control ring has a first end located on the side of a first lateral edge of the control ring, a second end located on the side of a second lateral edge of the control ring, the two ends being connected by a curved connection zone having a point of inflection.

Selon une deuxième forme de réalisation de l'invention, ledit trou oblong de l'anneau de commande s'étend uniquement dans la direction circonférentielle.According to a second embodiment of the invention, said oblong hole of the control ring extends only in the circumferential direction.

Selon une troisième forme de réalisation de l'invention, ledit trou oblong de l'anneau de commande s'étend de façon oblique par rapport à la direction axiale et par rapport à la direction circonférentielle.According to a third embodiment of the invention, said oblong hole of the control ring extends obliquely with respect to the axial direction and with respect to the circumferential direction.

Selon une quatrième forme de réalisation de l'invention, ledit trou oblong de l'anneau de commande a une forme d'arc de cercle.According to a fourth embodiment of the invention, said oblong hole of the control ring has an arcuate shape.

Selon une cinquième forme de réalisation de l'invention, ledit trou oblong de l'anneau de commande comporte une première extrémité s'étendant uniquement circonférentiellement et située du côté d'un bord latéral de l'anneau de commande, une seconde extrémité s'étendant uniquement circonférentiellement et étant située du côté de l'autre bord latéral de l'anneau de commande, lesdites extrémités étant reliées par une zone de liaison s'étendant de façon oblique par rapport à la direction circonférentielle et par rapport à la direction axiale.According to a fifth embodiment of the invention, said oblong hole of the control ring has a first end extending only circumferentially and located on the side of a lateral edge of the control ring, a second end s' extending only circumferentially and being located on the side of the other lateral edge of the control ring, said ends being connected by a connecting zone extending obliquely with respect to the circumferential direction and with respect to the axial direction.

L'invention concerne en outre une turbomachine, telle par exemple qu'un turbopropulseur ou un turboréacteur d'avion, comportant au moins un compresseur du type précité.The invention further relates to a turbomachine, such as for example a turboprop or an airplane turbojet, comprising at least one compressor of the aforementioned type.

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

  • la figure 1 est une demi-vue schématique partielle en coupe axiale d'un compresseur haute-pression d'un turboréacteur équipé d'un système de commande d'aubes à calage variable selon la technique antérieure,
  • la figure 2 est une vue schématique en coupe axiale à plus grande échelle du système de calage angulaire d'un étage du compresseur de la figure 1,
  • la figure 3 est une vue en perspective d'une partie d'un anneau de commande,
  • la figure 4 est une vue schématique, de dessus, d'une zone de l'anneau de commande illustré à la figure 3,
  • les figures 5 et 6 sont des vues correspondant respectivement aux figures 3 et 4 et illustrant une première forme de réalisation de l'invention,
  • la figure 7 est une vue correspondant à la figure 4 et illustrant une deuxième forme de réalisation de l'invention,
  • la figure 8 est une vue correspondant à la figure 4 et illustrant une troisième forme de réalisation de l'invention,
  • la figure 9 est une vue correspondant à la figure 4 et illustrant une quatrième forme de réalisation de l'invention,
  • la figure 10 est un diagramme représentant l'évolution de l'angle de calage des aubes de stator en fonction de la position angulaire de l'anneau de commande, pour chacune des formes de réalisation des figures 7, 8 et 9.
  • la figure 11 est une vue correspondant à la figure 4 et illustrant une cinquième forme de réalisation de l'invention,
  • la figure 12 est une vue correspondant à la figure 4 et illustrant une sixième forme de réalisation de l'invention,
  • la figure 13 est une vue correspondant à la figure 4 et illustrant une septième forme de réalisation de l'invention.
The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of non-limiting example with reference to the accompanying drawings in which:
  • the figure 1 is a partial diagrammatic half-view in axial section of a high-pressure compressor of a turbojet engine equipped with a variable pitch blade control system according to the prior art,
  • the figure 2 is a schematic view in axial section on a larger scale of the angular wedging system of a compressor stage of the figure 1 ,
  • the figure 3 is a perspective view of a portion of a control ring,
  • the figure 4 is a diagrammatic view, from above, of an area of the control ring illustrated in FIG. figure 3 ,
  • the Figures 5 and 6 are views corresponding respectively to Figures 3 and 4 and illustrating a first embodiment of the invention,
  • the figure 7 is a view corresponding to the figure 4 and illustrating a second embodiment of the invention,
  • the figure 8 is a view corresponding to the figure 4 and illustrating a third embodiment of the invention,
  • the figure 9 is a view corresponding to the figure 4 and illustrating a fourth embodiment of the invention,
  • the figure 10 is a diagram showing the evolution of the stub angle of the stator vanes as a function of the angular position of the control ring, for each of the embodiments of the Figures 7, 8 and 9 .
  • the figure 11 is a view corresponding to the figure 4 and illustrating a fifth embodiment of the invention,
  • the figure 12 is a view corresponding to the figure 4 and illustrating a sixth embodiment of the invention,
  • the figure 13 is a view corresponding to the figure 4 and illustrating a seventh embodiment of the invention.

On se réfère tout d'abord à la figure 1 qui représente une demi-vue schématique de la partie amont d'un compresseur haute-pression 10 selon la technique antérieure, en coupe selon un plan passant par l'axe de rotation 12 de la turbomachine. Le compresseur haute-pression 10 comprend un rotor formé de disques 14, 16, 18, 20 assemblés axialement les uns aux autres, le rotor étant en appui sur un palier 22 par l'intermédiaire d'un tourillon 24.We first refer to the figure 1 which represents a schematic half-view of the upstream portion of a high-pressure compressor 10 according to the prior art, in section along a plane passing through the axis of rotation 12 of the turbomachine. The high-pressure compressor 10 comprises a rotor formed of disks 14, 16, 18, 20 assembled axially with each other, the rotor being supported on a bearing 22 by means of a pin 24.

Chaque disque est agencé en aval d'une rangée annulaire d'aubes de stator 26 à calage variable. Chaque aube de stator comprend à ses extrémités radialement interne et externe des pivots cylindriques 28, 30 coaxiaux. Le pivot cylindrique interne 28 s'étend vers l'intérieur depuis l'aube de stator 26 et est centré et guidé en rotation dans un logement cylindrique d'un élément annulaire du stator, et le pivot cylindrique externe 30 s'étend radialement vers l'extérieur et est centré et guidé en rotation dans une cheminée cylindrique 32 d'un carter externe 34 sensiblement cylindrique du compresseur haute-pression 10.Each disk is arranged downstream of an annular row of stator vanes 26 with variable pitch. Each stator vane comprises at its radially inner and outer ends coaxial cylindrical pivots 28, 30. The internal cylindrical pivot 28 extends inwardly from the stator vane 26 and is centered and guided in rotation in a cylindrical housing of an annular element of the stator, and the external cylindrical pivot 30 extends radially towards the outside. outside and is centered and guided in rotation in a cylindrical chimney 32 of a substantially cylindrical outer casing 34 of the high-pressure compressor 10.

Le réglage du calage angulaire des aubes de stator 26 d'un étage est assuré à l'aide de biellettes 36 qui sont entraînées en rotation par un anneau de commande 38 monté pivotant par rapport au carter 34 autour de l'axe 12. Le débattement total de l'anneau de commande est par exemple compris entre 5 et 20°. Un vérin hydraulique 40 permet le déplacement simultané en rotation de plusieurs anneaux de commande 38. L'anneau 38 est par exemple formé de deux parties 39 assemblées l'une à l'autre par l'intermédiaire de pontets (non représentés) fixés aux extrémités desdites parties 39.The adjustment of the angular setting of the stator vanes 26 of a stage is ensured by means of rods 36 which are rotated by a control ring 38 pivotally mounted relative to the casing 34 about the axis 12. The deflection total of the control ring is for example between 5 and 20 °. A hydraulic cylinder 40 allows the simultaneous displacement in rotation of several control rings 38. The ring 38 is for example formed of two parts 39 assembled to each other by means of bridges (not shown) attached to the ends said parts 39.

Les biellettes 36 sont fixées par une extrémité sur les pivots radiaux 30 des aubes 26 à calage variable, ces pivots 30 étant guidés en rotation dans des douilles 42 montés dans les cheminées 32 du carter 34 (figure 2). L'extrémité de la biellette fixée au pivot d'aube 30 est maintenue radialement sur un rebord 44 de la douille 42 par un écrou 46 vissé sur l'extrémité du pivot 30. L'autre extrémité de la biellette 36 comprend un orifice dans lequel est guidé en rotation un pion cylindrique radial 48 monté dans un trou cylindrique 52 de l'anneau de commande 38. Les pions 48 sont maintenus en position par des pattes coudées 50 fixées sur l'anneau de commande 38. L'anneau de commande 38 est également déplaçable axialement en translation, de façon à accompagner la trajectoire circulaire des pions 48.The links 36 are fixed at one end to the radial pivots 30 of the variable-pitch vanes 26, these pivots 30 being guided in rotation in bushes 42 mounted in the chimneys 32 of the casing 34 (FIG. figure 2 ). The end of the rod attached to the blade pivot 30 is held radially on a rim 44 of the sleeve 42 by a nut 46 screwed onto the end of the pivot 30. The other end of the rod 36 comprises an orifice in which is guided in rotation a radial cylindrical pin 48 mounted in a cylindrical hole 52 of the control ring 38. The pins 48 are held in position by bent tabs 50 fixed to the control ring 38. The control ring 38 is also axially displaceable in translation, so as to accompany the circular trajectory of the pins 48.

Comme cela est mieux visible à la figure 3, les parties 39 de l'anneau de commande 38 comportent d'autres trous 54, 56 servant respectivement à la fixation des organes de liaison permettant de relier les extrémités des deux parties 39 de l'organe de commande 38 entre elles ou servant à la fixation de patins de centrage venant s'appliquer sur une piste ménagée sur la surface externe du carter.As is best seen in the figure 3 , the portions 39 of the control ring 38 comprise other holes 54, 56 serving respectively for fixing the connecting members for connecting the ends of the two parts 39 of the control member 38 between them or used for the fixing centering pads coming to apply on a track formed on the outer surface of the casing.

Lors de la rotation de l'anneau de commande 38 autour de son axe 12, celui-ci entraîne le pivotement des biellettes 36 et des aubes 26 autour de l'axe des pivots 28, 30 des aubes 26. Toutes les aubes 26 se trouvent alors dans une même position angulaire, pour une position angulaire donnée de l'anneau de commande 38, les biellettes 36 ayant toutes la même longueur.During the rotation of the control ring 38 about its axis 12, it causes the pivoting rods 36 and vanes 26 to pivot about the axis of the pivots 28, 30 of the blades 26. All the blades 26 are located then in the same angular position, for a given angular position of the control ring 38, the rods 36 all having the same length.

Or, comme indiqué précédemment, en fonction du régime de la turbomachine, il existe un besoin de pouvoir adapter le calage des aubes 26 en fonction notamment de leur position azimutale, c'est-à-dire de la position circonférentielle de l'aube 26 de stator dans l'étage correspondant.However, as indicated above, depending on the speed of the turbomachine, there is a need to be able to adapt the wedging of the blades 26 in particular according to their azimuthal position, that is to say, the circumferential position of the blade 26 stator in the corresponding stage.

L'invention répond à ce besoin en proposant un anneau de commande 38 permettant d'adapter le calage angulaire des aubes 26 de façon individuelle ou par groupe d'aubes 26, en fonction des positions azimutales des aubes 26 concernées ou des groupes d'aubes 26 concernés.The invention responds to this need by providing a control ring 38 for adapting the angular setting of the blades 26 individually or by group of blades 26, depending on the azimuthal positions of the blades 26 concerned or groups of blades 24 concerned.

Les figures 5 et 6 illustrent une première forme de réalisation de l'invention dans laquelle une partie des trous dans lesquels sont engagés les pions cylindriques 48 ont une forme oblongue (trous 58), une autre partie desdits trous étant cylindriques (trous 52) et de diamètre sensiblement identique à celui des pions 48 correspondants.The Figures 5 and 6 illustrate a first embodiment of the invention in which part of the holes in which the cylindrical pins 48 are engaged have an oblong shape (holes 58), another part of said holes being cylindrical (holes 52) and of diameter substantially identical to that of the corresponding pawns 48.

En particulier, les trous oblongs 58 comportent chacun une première extrémité 60 située du côté d'un premier bord latéral ou bord amont 62 de l'anneau de commande 38, une seconde extrémité 64 située du côté d'un second bord latéral ou bord aval 66 de l'anneau de commande 38, les deux extrémités 60, 64 étant reliées par une zone de liaison courbe 68 présentant un point d'inflexion.In particular, the oblong holes 58 each comprise a first end 60 located on the side of a first lateral edge or upstream edge 62 of the control ring 38, a second end 64 located on the side of a second side edge or downstream edge 66 of the control ring 38, the two ends 60, 64 being connected by a curved connection zone 68 having a point of inflection.

Ainsi, en fonctionnement, l'angle de calage des aubes 26 ne varie pas de la même manière, en fonction de la position angulaire de l'anneau de commande 38, pour les aubes 26 associées aux trous cylindriques 52 ou pour les aubes 26 associées aux trous oblongs 58. En fonction de la forme des trous 58, il est donc possible d'adapter la variation de l'angle de calage en fonction de la position angulaire de l'anneau de commande 38 (également appelée ci-après loi de calage) pour chacune des aubes 26.Thus, in operation, the wedging angle of the blades 26 does not vary in the same way, as a function of the angular position of the control ring 38, for the blades 26 associated with the cylindrical holes 52 or for the blades 26 associated with them. to the oblong holes 58. Depending on the shape of the holes 58, it is therefore possible to adapt the variation of the wedging angle as a function of the angular position of the control ring 38 (also called hereinafter wedging) for each blade 26.

Dans ce cas, tous les trous oblongs 58 ont sensiblement la même forme, les autres trous 52 étant cylindriques. Un tel anneau de commande 38 possède donc deux groupes d'aubes 26, situées dans des zones azimutales différentes de la turbomachine, et suivant des lois de calage différentes d'un groupe à l'autre.In this case, all the oblong holes 58 have substantially the same shape, the other holes 52 being cylindrical. Such a control ring 38 thus has two groups of blades 26, located in azimuthal zones different from the turbomachine, and according to different timing laws from one group to another.

On notera que le centre des trous 52 est aligné circonférentiellement avec l'une des extrémités des trous oblongs 58.It will be noted that the center of the holes 52 is aligned circumferentially with one of the ends of the oblong holes 58.

La figure 7 illustre une deuxième forme de réalisation de l'invention dans laquelle chaque trou oblong 58 de l'anneau de commande 38 s'étend uniquement dans la direction circonférentielle.The figure 7 illustrates a second embodiment of the invention wherein each elongate hole 58 of the control ring 38 extends only in the circumferential direction.

La figure 8 représente une troisième forme de réalisation de l'invention dans laquelle chaque trou oblong 58 de l'anneau de commande 38 s'étend de façon oblique par rapport à la direction axiale A et par rapport à la direction circonférentielle C. Plus particulièrement, chaque trou oblong 58 s'étend de façon rectiligne, d'amont en aval (c'est-à-dire de gauche à droite à la figure 8), dans un premier sens de rotation de l'anneau de commande indiqué par la flèche S1, qui est un sens d'ouverture des aubes 26.The figure 8 represents a third embodiment of the invention in which each oblong hole 58 of the control ring 38 extends obliquely with respect to the axial direction A and with respect to the circumferential direction C. More particularly, each hole oblong 58 extends rectilinearly, from upstream to downstream (i.e. from left to right at figure 8 ), in a first direction of rotation of the control ring indicated by the arrow S1, which is an opening direction of the blades 26.

La figure 9 représente une quatrième forme de réalisation de l'invention dans laquelle chaque trou oblong 58 de l'anneau de commande 38 a une forme en arc de cercle ou approchant un arc de cercle, plus particulièrement en quart de cercle. Une extrémité 70 de chaque trou oblong 58 est dirigé axialement vers l'amont, l'autre extrémité 72 étant dirigée circonférentiellement dans un sens S2 opposé au sens S1 précité, le sens S2 étant un sens de fermeture des aubes 26.The figure 9 represents a fourth embodiment of the invention in which each oblong hole 58 of the control ring 38 has a shape in an arc of circle or approaching an arc of a circle, plus especially in a quarter circle. One end 70 of each oblong hole 58 is directed axially upstream, the other end 72 being directed circumferentially in a direction S2 opposite to the aforesaid direction S1, the direction S2 being a closing direction of the blades 26.

La figure 10 illustre la loi de calage d'aubes pour des aubes 26 associées respectivement à un trou cylindrique 52 (courbe C1), à un trou oblong 58 de la figure 7 (courbe C2), à un trou oblong 58 de la figure 8 (courbe C3) et à un trou oblong 58 de la figure 9 (courbe C4). Les lois de calage sont les courbes représentatives de l'évolution de la position angulaire de l'aube 26 (αaube) en fonction de la position angulaire de l'anneau de commande 38 (αanneau).The figure 10 illustrates the blade registration law for blades 26 associated respectively with a cylindrical hole 52 (curve C1), with an oblong hole 58 of the figure 7 (curve C2), to an oblong hole 58 of the figure 8 (curve C3) and an oblong hole 58 of the figure 9 (curve C4). The calibration laws are the curves representative of the evolution of the angular position of the blade 26 (αaube) as a function of the angular position of the control ring 38 (αanneau).

On remarque que ces lois de calage sont différentes les unes des autres, en particulier pour les angles de l'anneau de commande 38 correspondant à une ouverture des aubes 26 associées. L'angle αaube correspond à l'angle des biellettes 36 par rapport à l'axe 12 de la turbomachine, en définissant une droite qui passe par le centre du pivot 30 de l'aube 26 et le centre du pion 48 qui est inséré dans l'anneau 38. Par définition, la position d'ouverture correspond à un angle αaube négatif par rapport à l'axe 12 de la turbomachine, en considérant que le sens positif est le sens trigonométrique, et la position de fermeture correspond à un angle αaube positif par rapport à l'axe 12 de la turbomachine. L'angle αaube=0 correspond à la position où les biellettes 36 sont alignées avec l'axe 12 de la turbomachine.Note that these clamping laws are different from each other, especially for the angles of the control ring 38 corresponding to an opening of the associated blades 26. The angle αaube corresponds to the angle of the rods 36 with respect to the axis 12 of the turbomachine, by defining a straight line which passes through the center of the pivot 30 of the blade 26 and the center of the pin 48 which is inserted in the ring 38. By definition, the open position corresponds to a negative angle αaube relative to the axis 12 of the turbomachine, considering that the positive direction is the trigonometric direction, and the closed position corresponds to an angle αaube positive with respect to the axis 12 of the turbomachine. The angle αaube = 0 corresponds to the position where the rods 36 are aligned with the axis 12 of the turbomachine.

Si l'on cherche à modifier les lois de calage pour les angles correspondant à une fermeture des aubes 26, il est possible d'utiliser des trous oblongs 58 dont les formes générales sont les symétriques/axe de la turbomachine de celles décrites précédemment. Dans ce cas toutefois, il convient d'aligner le centre des trous 52 avec l'autre extrémité des trous oblongs 58.If one seeks to modify the clamping laws for the angles corresponding to a closure of the blades 26, it is possible to use oblong holes 58 whose general shapes are symmetrical / axis of the turbomachine of those described above. In this case, however, it is necessary to align the center of the holes 52 with the other end of the oblong holes 58.

En fonction de la forme choisie du trou 52, 58 (cylindrique, rectiligne oblique, arc de cercle, etc...), il est ainsi possible d'adapter aux besoins la loi de calage des aubes 26 associées.Depending on the chosen shape of the hole 52, 58 (cylindrical, rectilinear oblique, arc of circle, etc ...), it is thus possible to adapt to the requirements of the law of wedging of the blades 26 associated.

La figure 11 illustre une cinquième forme de réalisation de l'invention dans laquelle chaque trou oblong 58 de l'anneau de commande 38 a une forme symétrique à la forme des trous oblongs 58 de la figure 6, par rapport à un plan radial passant par la zone axialement médiane de l'anneau de commande 38.The figure 11 illustrates a fifth embodiment of the invention in which each oblong hole 58 of the control ring 38 has a shape symmetrical to the shape of the oblong holes 58 of the figure 6 , with respect to a radial plane passing through the axially central zone of the control ring 38.

La figure 12 illustre une sixième forme de réalisation de l'invention dans laquelle chaque trou oblong 58 de l'anneau de commande 38 comporte une première extrémité 74 s'étendant uniquement circonférentiellement et située du côté du bord amont 62 de l'anneau de commande, une seconde extrémité 76 s'étendant uniquement circonférentiellement et située du côté du bord aval 66 de l'anneau de commande 38, lesdites extrémités 74, 76 étant reliées par une zone de liaison 78 s'étendant de façon oblique par rapport à la direction circonférentielle C et par rapport à la direction axiale A.The figure 12 illustrates a sixth embodiment of the invention in which each oblong hole 58 of the control ring 38 has a first end 74 extending only circumferentially and located on the side of the upstream edge 62 of the control ring, a second end 76 extending only circumferentially and located on the side of the downstream edge 66 of the control ring 38, said ends 74, 76 being connected by a connecting zone 78 extending obliquely with respect to the circumferential direction C and with respect to the axial direction A.

La figure 13 illustre une septième forme de réalisation de l'invention dans laquelle chaque trou oblong 58 de l'anneau de commande 38 a une forme symétrique à la forme des trous oblongs 58 de la figure 8, par rapport à un plan radial passant par la zone axialement médiane de l'anneau de commande 38.The figure 13 illustrates a seventh embodiment of the invention in which each oblong hole 58 of the control ring 38 has a shape symmetrical to the shape of the oblong holes 58 of the figure 8 , with respect to a radial plane passing through the axially central zone of the control ring 38.

Bien entendu, l'anneau de commande 38 peut comporter au moins deux types de trou oblongs 58 parmi ceux décrits précédemment. D'autres formes de trous oblongs 58 peuvent également être utilisées, pour autant que ces trous oblongs 58 s'étendent notamment dans la direction circonférentielle C.Of course, the control ring 38 may comprise at least two types of oblong hole 58 among those described above. Other forms of oblong holes 58 may also be used, provided that these oblong holes 58 extend in particular in the circumferential direction C.

Claims (9)

  1. Turbine engine compressor (10), in particular of an aeroplane turboprop or turbofan, comprising a stator featuring an annular casing (34) and at least one annular row of variable-pitch vanes (26), wherein each vane (26) comprises a radially external end having a pivot (30) mounted in an orifice in the casing (34) and connected by a linking member (36) to an control ring (38) capable of pivoting axially in relation to the casing (34), wherein said linking member (36) comprises a first end fixed to the pivot (30) of the vane (26) and a second end having a pin (48) inserted in a hole (52,58) in the control ring (38), characterised in that the control ring (38) comprises at least one cylindrical hole (52), into which a cylindrical pin (48) of a linking member (36) is inserted, wherein the diameters of the cylindrical pin (48) and of the hole (52) are substantially identical and at least one oblong hole (58) extending circumferentially, into which another cylindrical pin (48) of another linking member (36) is inserted in order to allow movement of said pin (48) in said oblong hole (58), during rotation of the control ring (38).
  2. Compressor (10) according to claim 1, characterised in that the pins (48) are cylindrical.
  3. Compressor (10) according to claim 1 or 2, characterised in that one (52) at least of the holes (52, 58) in the control ring (38), serving for insertion of the pins (48) of the linking members (36), is shaped so as to inhibit movement of the pin (48) in said hole (52).
  4. Compressor (10) according to any of claims 1 to 3, characterised in that said oblong hole (58) in the control ring (38) comprises a first end (60) located on the side of a first lateral edge (62) of the control ring (38) and a second end (64) located on the side of a second lateral edge (66) of the control ring (38), wherein both ends (60, 64) are connected by a curved joining area (68) featuring an inflection point.
  5. Compressor (10) according to any of claims 1 to 4, characterised in that said oblong hole (58) in the control ring (38) extends solely in the circumferential direction (C).
  6. Compressor (10) according to any of claims 1 to 5, characterised in that said oblong hole (58) in the control ring (38) extends obliquely in relation to the axial direction (A) and in relation to the circumferential direction (C).
  7. Compressor (10) according to any of claims 1 to 6, characterised in that said oblong hole (58) in the control ring (38) forms an arc shape.
  8. Compressor (10) according to any of claims 1 to 6, characterised in that said oblong hole (58) in the control ring (38) comprises a first end (74) extending solely circumferentially and located on the side of a first lateral edge (62) of the control ring (38) and a second end (76) extending solely circumferentially located on the side of the other lateral edge (66) of the control ring (38), wherein said ends (74, 76) are connected by a joining area (78) extending obliquely in relation to the circumferential direction (C) and in relation to the axial direction (A).
  9. Turbine engine, such as for example an aeroplane turboprop or a turbofan, comprising at least one compressor (10) according to any of claims 1 to 8.
EP14827799.9A 2013-12-19 2014-12-04 Turbine engine compressor, in particular of an aeroplane turboprop or turbofan Active EP3084141B1 (en)

Applications Claiming Priority (2)

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FR1362972A FR3015594B1 (en) 2013-12-19 2013-12-19 TURBOMACHINE COMPRESSOR, ESPECIALLY AIRCRAFT TURBOPROPULSER OR AIRCRAFT TURBINEACTOR
PCT/FR2014/053163 WO2015092197A1 (en) 2013-12-19 2014-12-04 Turbine engine compressor, in particular of an aeroplane turboprop or turbofan

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EP3084141A1 EP3084141A1 (en) 2016-10-26
EP3084141B1 true EP3084141B1 (en) 2018-02-07

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EP (1) EP3084141B1 (en)
JP (1) JP6419831B2 (en)
CN (1) CN105874171B (en)
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CA (1) CA2932998C (en)
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FR3100272A1 (en) * 2019-08-27 2021-03-05 Safran Aircraft Engines GUIGNOL FOR A VARIABLE TIMING DEVICE OF A TURBOMACHINE

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US20160348530A1 (en) 2016-12-01
JP2017501334A (en) 2017-01-12
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FR3015594B1 (en) 2018-04-06
CA2932998C (en) 2022-04-19
BR112016013833A2 (en) 2017-08-08
EP3084141A1 (en) 2016-10-26
CN105874171B (en) 2018-06-12
CN105874171A (en) 2016-08-17
RU2016123656A (en) 2018-01-24
CA2932998A1 (en) 2015-06-25
US10590794B2 (en) 2020-03-17
FR3015594A1 (en) 2015-06-26
WO2015092197A1 (en) 2015-06-25
JP6419831B2 (en) 2018-11-07

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