EP1801355A1 - Device for locking the blades of a turbomachine disk - Google Patents

Device for locking the blades of a turbomachine disk Download PDF

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Publication number
EP1801355A1
EP1801355A1 EP05292779A EP05292779A EP1801355A1 EP 1801355 A1 EP1801355 A1 EP 1801355A1 EP 05292779 A EP05292779 A EP 05292779A EP 05292779 A EP05292779 A EP 05292779A EP 1801355 A1 EP1801355 A1 EP 1801355A1
Authority
EP
European Patent Office
Prior art keywords
groove
lock
disk
turbomachine
latch
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
EP05292779A
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German (de)
French (fr)
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EP1801355B1 (en
Inventor
Philippe Ernst
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 Aero Boosters SA
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Techspace Aero SA
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Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP05292779.5A priority Critical patent/EP1801355B1/en
Publication of EP1801355A1 publication Critical patent/EP1801355A1/en
Application granted granted Critical
Publication of EP1801355B1 publication Critical patent/EP1801355B1/en
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the invention relates to a locking device used on a turbomachine disk carrying vanes.
  • a locking device used on a turbomachine disk carrying vanes.
  • Such a device serves to block said blades in the circumferential direction of the disk.
  • This device is housed in a circumferential groove of the disc, the blades being retained by their foot in this groove.
  • the invention also relates to a turbomachine disk and a turbomachine, equipped with such a locking device.
  • FIG. 1 An example of a disk equipped with a known locking device is shown in FIG. 1.
  • the device 101 comprises a lock 105 and a screw 103 passing through the lock.
  • the disk 107 has a circumferential groove 106 in which the lock 105 is housed.
  • the groove 106 is delimited, in its upper part, by first and second lips 109, 111.
  • the screw 103 is tightened.
  • the latter then bears against the bottom 108 of the groove 106 and forces the lock 105 to go up against the lips 109, 111 of the groove. More precisely, they are radial bearings 117, 122 projecting from opposite lateral faces 119, 121 of the lock which abut against said lips 109, 111.
  • the lock 105 thus moves in a translation movement, along the axis S of the screw.
  • This device has the disadvantage of being difficult to lock when the screw is not properly oriented inside the groove. This is the case, for example, when the axis S of the screw is oriented in the direction D shown in dotted line in FIG. 1. In such a situation, one of the radial bearing surfaces 117, 122 of the lock comes into abutment before the other, and the device tends to hang. To lock the device correctly, it is then necessary to increase the tightening torque, with the risk of damaging the threading of the screw 103 and / or the internal threading of the lock 105.
  • the wrong orientation of the screw 103 may cause the release of the lock, that is to say the output of one of the bearings 117, 122 outside the groove 106.
  • the invention aims to provide a device easy to lock, especially when the lips of the groove in which it is housed are not at the same distance from the axis of rotation of the disc.
  • the invention relates to a device of the aforementioned type comprising a lock passing from an unlocked position to a locked position under the action of pushing means resting on the bottom of the groove, this lock having a first and second opposite lateral faces, characterized in that the first lateral face of the latch has a bearing surface in rotation, and in that said latch is able to move in rotation around said bearing surface, in a plane perpendicular to the circumferential direction of the disk (that is to say a radial plane, containing the axis of rotation of the disk), to move from its unlocked position to its locked position.
  • said support surface is locked in the groove and activates the thrust means which generally comprise a screw cooperating with a threaded hole passing through the lock.
  • the thrust means which generally comprise a screw cooperating with a threaded hole passing through the lock.
  • the lock remains in support on this surface.
  • the locking of the device is obtained not by translation of the lock, but by rotation (or pivoting) thereof.
  • the first lateral face of the lock is curved and constitutes said bearing surface in rotation.
  • the curvature of the first side face facilitates rotation guidance.
  • the side face being devoid of projections (it has neither tenon nor radial bearing), its manufacture is simple and the cost price of the lock is low, compared to that of known locks.
  • the lock has on its second side face a pin or other means for preventing the circumferential movement of the latch when the latter is in its locked position.
  • This stud is protruding from the second side face and adapted to be housed in a notch formed in a lip of the groove, when the lock goes into its locked position.
  • the lock has on its second side face a radial bearing or other means for preventing the radial displacement of the latch, when the latter is in its locked position.
  • This scope is projecting relative to the second side face and is adapted to abut against a lip of the groove, when the lock passes into its locked position.
  • the radial direction is defined with respect to the axis of rotation of the disk (a radial line is perpendicular to the axis of rotation and intersects this axis).
  • the invention also relates to a turbomachine disk having a circumferential groove in which blades are capable of being retained by their feet, this groove being delimited, in its upper part, by first and second lips, the disk comprising a blocking device, as previously described, for blocking the blades in the circumferential direction of the disk.
  • the disc has a housing, between the upper edge of the first lip and the bottom of the groove, adapted to receive the bearing surface in rotation of the latch and whose shape is substantially complementary to that of the bearing surface. This improves the rotation guidance of the lock.
  • the bearing surface is formed by the first lateral face of the latch, the whole of this lateral face is located under the upper edge of the first lip of the groove and the upper part of the first lateral face abuts against this first lip, at least when the lock is in the locked position.
  • the subject of the invention is also a turbomachine rotor drum and, more generally, a turbomachine comprising a disc of the aforementioned type.
  • turbojet turbojet
  • turboprop land gas turbine
  • rotor of the low pressure compressor of this turbojet consists of a drum formed of a stack of disks on the periphery of which are fixed blades, whose head remains free.
  • FIG. 2 there is shown (see Figure 2) a disc 7 carrying vanes 13 forming part of the drum of such a rotor.
  • This drum is constituted by several disks 7 of this type and each disk carries at its periphery a plurality of vanes 13 (see FIG. 3).
  • the blades 13 are retained in a groove 6, extending circumferentially to the outer surface of the disk 7.
  • a blade 13 comprises at its base a platform 16 and a blade root 18, said to "hammer clip", which is extends under said platform 16 over part of the width thereof.
  • the blade root 18 is engaged and retained in said groove 6 of the disk 7. In FIG. 3, the position of the blade root 18 in the groove 6 appears in phantom.
  • the groove 6 is delimited in its upper part, by a first lip, or upstream lip 9, and by a second lip, or downstream lip 11.
  • the upstream and downstream are defined relative to the normal direction the circulation of gases through the turbomachine.
  • the platform 16 of a blade 13 comes to cover a sector of the groove 6. Once all the blades 13 are in place, the platforms 16, side by side, reconstruct an annular surface which externally delimits a portion of the conical flow of the compressor. inside which the gases circulate.
  • the mounting of the blades 13 requires at least one insertion slot 30 to be made on one of the annular lips 9, 11 of the groove 6, in this case the two lips have an insertion notch 30.
  • This notch 30 makes it possible to engage the dawning feet 18 one after the other in the groove 6.
  • Each locking device 1 comprises a latch 5 traversed by a screw 3.
  • the latch has two opposite upstream side faces 21 and downstream 21 opposite. Once the lock 5 in the groove 6, the upstream side faces 19 and downstream 21 respectively face the upstream lips 9 and downstream 11 of this groove.
  • the radial span 17 extends substantially over the entire width of the side face 21, while the pin 15 extends over only a portion of this width.
  • the pin 15 is intended to be housed in a notch 23 formed in the downstream lip 11 of the groove 6 and the radial bearing 17 is intended to abut against the downstream lip 11 when the latch 5 is in the locked position (see FIG. ).
  • the upstream side face 19 of the lock is devoid of tenon or radial bearing. This face 19 is curved and constitutes a rotating bearing surface around which the latch 5 pivots to move from its unlocked position to its locked position (or vice versa). The change of position is made during the screwing (or unscrewing) of the screw 3.
  • the upstream side face 19 of the lock 5 is housed between the upper edge of the upstream lip 9 of the groove 6 and the bottom 8 of this groove.
  • the wall of the housing receiving the upstream side face of the latch 5, is also curved. The shape of this wall and that of the upstream side face 19 correspond to promote the guiding of the latch 5 during its pivoting.
  • the downstream lateral face 21 of the lock 5 has, in regions where there is neither the tenon nor the radial bearing surface 17, a curvature such that the clearance J between the face 21 and the downstream lip 11 of the groove remains substantially constant during the rotation of the latch.
  • An example of a face 21 of this type is shown in FIGS. 3 and 4.
  • the face 21 is part of an arc of circle C of appropriate diameter, centered at the point O which belongs to the rotating support surface formed by the side face 19. Note that a point on the face 21 substantially describes part of the arc C when the latch 5 pivots.
  • downstream side face 21 is substantially flat. This simplifies the machining of the lock, but the assembly clearance between the lock 5 and the disc 7 varies during the rotation of the lock (so be careful that this game is not too high).
  • the locking device according to the invention is interesting when the lips 9 and 11 of the groove 6 are offset, that is to say located at different distances, D and d, of the axis of A rotation of the disc (see Figure 3).
  • FIG. 3 shows the average plane P passing through the lower faces of the lips 9, 11 against which the upper part of the upstream lateral face 19 and the radial bearing 17 respectively abut in the locked position of the lock 5.
  • the plane P is inclined at an angle with respect to the axis A of rotation of the disk, which also corresponds to the axis of the turbomachine.
  • the angle a is greater than or equal to 25 °, it is preferable to use a locking device according to the invention because the use of known devices, in which the lock is mounted in translation along the axis of the screw, gives very poor results in terms of locking.

Abstract

The blade lock (5), shaped to fix a turbine blade (13) in a disc groove (6), has a first side face (19) with a thrust surface that engages with the groove between the upper edge of a first lip (9) and the base of the groove as it is pivoted by a thrust element (3) between free and locked positions. The thrust element is in the form of a screw inserted in a threaded hole that made through the lock. The second side face (11) of the lock has a lug (15) that prevents any circumferential movement of the lock once it is in its locked position.

Description

L'invention concerne un dispositif de blocage utilisé sur un disque de turbomachine porteur d'aubes. Un tel dispositif sert à bloquer lesdites aubes, dans la direction circonférentielle du disque. Ce dispositif est logé dans une rainure circonférentielle du disque, les aubes étant retenues par leur pied dans cette rainure.The invention relates to a locking device used on a turbomachine disk carrying vanes. Such a device serves to block said blades in the circumferential direction of the disk. This device is housed in a circumferential groove of the disc, the blades being retained by their foot in this groove.

L'invention concerne également un disque de turbomachine et une turbomachine, équipés d'un tel dispositif de blocage.The invention also relates to a turbomachine disk and a turbomachine, equipped with such a locking device.

Un exemple de disque équipé d'un dispositif de blocage connu est représenté sur la figure 1. Le dispositif 101 comprend un verrou 105 et une vis 103 traversant le verrou. Le disque 107 présente une rainure circonférentielle 106 dans laquelle est logé le verrou 105. La rainure 106 est délimitée, dans sa partie supérieure, par des première et deuxième lèvres 109, 111. Pour faire passer le verrou 105 dans sa position verrouillée, représentée sur la figure 1, on serre la vis 103. Cette dernière prend alors appui sur le fond 108 de la rainure 106 et oblige le verrou 105 à remonter en butée contre les lèvres 109, 111 de la rainure. Plus précisément, ce sont des portées radiales 117, 122 faisant saillie sur des faces latérales 119, 121 opposées du verrou qui viennent en butée contre lesdites lèvres 109, 111. Le verrou 105 se déplace donc selon un mouvement de translation, suivant l'axe S de la vis.An example of a disk equipped with a known locking device is shown in FIG. 1. The device 101 comprises a lock 105 and a screw 103 passing through the lock. The disk 107 has a circumferential groove 106 in which the lock 105 is housed. The groove 106 is delimited, in its upper part, by first and second lips 109, 111. In order to pass the lock 105 into its locked position, represented on 1, the screw 103 is tightened. The latter then bears against the bottom 108 of the groove 106 and forces the lock 105 to go up against the lips 109, 111 of the groove. More precisely, they are radial bearings 117, 122 projecting from opposite lateral faces 119, 121 of the lock which abut against said lips 109, 111. The lock 105 thus moves in a translation movement, along the axis S of the screw.

Ce dispositif a pour inconvénient d'être difficile à verrouiller lorsque la vis n'est pas correctement orientée à l'intérieur de la rainure. C'est le cas, par exemple, lorsque l'axe S de la vis est orienté suivant la direction D représentée en pointillé sur la figure 1. Dans une telle situation, une des portées radiales 117, 122 du verrou vient en butée avant l'autre, et le dispositif a tendance à se bloquer. Pour verrouiller correctement le dispositif, il faut alors augmenter le couple de serrage, au risque d'endommager le filetage de la vis 103 et/ou le filetage interne du verrou 105. En outre, dans les cas où le jeu entre les faces latérales 119, 121 du verrou et les lèvres 109, 111 de la rainure 106 est important, la mauvaise orientation de la vis 103 peut entraîner le déchaussement du verrou, c'est-à-dire la sortie d'une des portées 117, 122 en dehors de la rainure 106.This device has the disadvantage of being difficult to lock when the screw is not properly oriented inside the groove. This is the case, for example, when the axis S of the screw is oriented in the direction D shown in dotted line in FIG. 1. In such a situation, one of the radial bearing surfaces 117, 122 of the lock comes into abutment before the other, and the device tends to hang. To lock the device correctly, it is then necessary to increase the tightening torque, with the risk of damaging the threading of the screw 103 and / or the internal threading of the lock 105. In addition, in cases where the clearance between the lateral faces 119 , 121 of the lock and the lips 109, 111 of the groove 106 is important, the wrong orientation of the screw 103 may cause the release of the lock, that is to say the output of one of the bearings 117, 122 outside the groove 106.

Les problèmes d'orientation de la vis 103 et de déchaussement du verrou sont plus fréquents lorsque les lèvres 109 et 111 ne sont pas à la même distance de l'axe A de rotation du disque 107, comme représenté sur la figure 1. C'est souvent le cas pour les disques des derniers étages du compresseur basse pression d'un turboréacteur d'avion.The problems of orientation of the screw 103 and loosening of the lock are more frequent when the lips 109 and 111 are not at the same distance from the axis A of rotation of the disk 107, as shown in FIG. 1. This is often the case for the discs of the last stages of the low pressure compressor of an airplane turbojet engine.

L'invention vise à proposer un dispositif facile à verrouiller, en particulier lorsque les lèvres de la rainure dans laquelle il est logé ne sont pas à la même distance de l'axe de rotation du disque.The invention aims to provide a device easy to lock, especially when the lips of the groove in which it is housed are not at the same distance from the axis of rotation of the disc.

Pour atteindre cet objectif, l'invention a pour objet un dispositif du type précité comprenant un verrou passant d'une position déverrouillée à une position verrouillée sous l'action de moyens de poussée en appui sur le fond de la rainure, ce verrou présentant une première et une deuxième faces latérales opposées, caractérisé en ce que la première face latérale du verrou présente une surface d'appui en rotation, et en ce que ledit verrou est apte à se déplacer en rotation autour de ladite surface d'appui, dans un plan perpendiculaire à la direction circonférentielle du disque (c'est-à-dire un plan radial, contenant l'axe de rotation du disque), pour passer de sa position déverrouillée à sa position verrouillée.To achieve this object, the invention relates to a device of the aforementioned type comprising a lock passing from an unlocked position to a locked position under the action of pushing means resting on the bottom of the groove, this lock having a first and second opposite lateral faces, characterized in that the first lateral face of the latch has a bearing surface in rotation, and in that said latch is able to move in rotation around said bearing surface, in a plane perpendicular to the circumferential direction of the disk (that is to say a radial plane, containing the axis of rotation of the disk), to move from its unlocked position to its locked position.

Pour verrouiller un tel dispositif, on cale ladite surface d'appui dans la rainure et on active les moyens de poussée qui comprennent, généralement, une vis coopérant avec un trou fileté traversant le verrou. Lors de son pivotement, le verrou reste en appui sur cette surface. Le verrouillage du dispositif est obtenu non plus par translation du verrou, mais par rotation (ou pivotement) de celui-ci. On évite ainsi, lors du verrouillage, les problèmes de blocage du dispositif ou de déchaussement du verrou.To lock such a device, said support surface is locked in the groove and activates the thrust means which generally comprise a screw cooperating with a threaded hole passing through the lock. During its pivoting, the lock remains in support on this surface. The locking of the device is obtained not by translation of the lock, but by rotation (or pivoting) thereof. Thus, during locking, the problems of locking the device or loosening the lock are avoided.

Selon un mode de réalisation, la première face latérale du verrou est courbe et constitue ladite surface d'appui en rotation. La courbure de la première face latérale facilite le guidage en rotation. En outre, la face latérale étant dépourvue de projections (elle ne présente ni tenon, ni portée radiale), sa fabrication est simple et le prix de revient du verrou est faible, comparé à celui des verrous connus.According to one embodiment, the first lateral face of the lock is curved and constitutes said bearing surface in rotation. The curvature of the first side face facilitates rotation guidance. In addition, the side face being devoid of projections (it has neither tenon nor radial bearing), its manufacture is simple and the cost price of the lock is low, compared to that of known locks.

Avantageusement, le verrou présente sur sa deuxième face latérale un tenon ou tout autre moyen permettant d'empêcher le déplacement circonférentiel du verrou lorsque celui-ci est dans sa position verrouillée. Ce tenon est en saillie par rapport à la deuxième face latérale et apte à venir se loger dans une encoche ménagée dans une lèvre de la rainure, lorsque le verrou passe dans sa position verrouillée.Advantageously, the lock has on its second side face a pin or other means for preventing the circumferential movement of the latch when the latter is in its locked position. This stud is protruding from the second side face and adapted to be housed in a notch formed in a lip of the groove, when the lock goes into its locked position.

Avantageusement encore, le verrou présente sur sa deuxième face latérale une portée radiale ou tout autre moyen permettant d'empêcher le déplacement radial du verrou, lorsque celui-ci est dans sa position verrouillée. Cette portée est en saillie par rapport à la deuxième face latérale et est apte à venir en butée contre une lèvre de la rainure, lorsque le verrou passe dans sa position verrouillée. Dans la présente demande, la direction radiale est définie par rapport à l'axe de rotation du disque (une droite radiale est perpendiculaire à l'axe de rotation et coupe cet axe).Advantageously, the lock has on its second side face a radial bearing or other means for preventing the radial displacement of the latch, when the latter is in its locked position. This scope is projecting relative to the second side face and is adapted to abut against a lip of the groove, when the lock passes into its locked position. In the present application, the radial direction is defined with respect to the axis of rotation of the disk (a radial line is perpendicular to the axis of rotation and intersects this axis).

L'invention a également pour objet un disque de turbomachine présentant une rainure circonférentielle dans laquelle des aubes sont susceptibles d'être retenues par leur pied, cette rainure étant délimitée, dans sa partie supérieure, par des première et deuxième lèvres, le disque comprenant un dispositif de blocage, tel que précédemment décrit, permettant de bloquer les aubes dans la direction circonférentielle du disque.The invention also relates to a turbomachine disk having a circumferential groove in which blades are capable of being retained by their feet, this groove being delimited, in its upper part, by first and second lips, the disk comprising a blocking device, as previously described, for blocking the blades in the circumferential direction of the disk.

Selon un mode de réalisation, le disque présente un logement, entre le bord supérieur de la première lèvre et le fond de la rainure, apte à recevoir la surface d'appui en rotation du verrou et dont la forme est sensiblement complémentaire de celle de la surface d'appui. Ceci permet d'améliorer le guidage en rotation du verrou. Lorsque la surface d'appui est formée par la première face latérale du verrou, l'ensemble de cette face latérale se situe sous le bord supérieur de la première lèvre de la rainure et la partie supérieure de la première face latérale est en butée contre cette première lèvre, au moins lorsque le verrou est en position verrouillée.According to one embodiment, the disc has a housing, between the upper edge of the first lip and the bottom of the groove, adapted to receive the bearing surface in rotation of the latch and whose shape is substantially complementary to that of the bearing surface. This improves the rotation guidance of the lock. When the bearing surface is formed by the first lateral face of the latch, the whole of this lateral face is located under the upper edge of the first lip of the groove and the upper part of the first lateral face abuts against this first lip, at least when the lock is in the locked position.

L'invention a également pour objet un tambour de rotor de turbomachine et, plus généralement, une turbomachine comprenant un disque du type précité.The subject of the invention is also a turbomachine rotor drum and, more generally, a turbomachine comprising a disc of the aforementioned type.

L'invention et ses avantages seront mieux compris à la lecture de la description détaillée qui suit, donnée à titre illustratif et non limitatif. Cette description fait référence aux figures annexées sur lesquelles :

  • la figure 1 est une vue de détail en coupe radiale d'un disque de turbomachine équipé d'un dispositif de blocage de type connu ;
  • la figure 2 est une vue de détail en perspective d'une partie du tambour du rotor d'une turbomachine;
  • la figure 3 est une vue de détail en coupe radiale montrant un exemple de dispositif de blocage selon l'invention et une aube voisine, montés sur un disque de turbomachine, le dispositif étant en position verrouillée ;
  • la figure 4 est une vue de détail en coupe radiale montrant l'exemple de dispositif de blocage de la figure 3, monté sur un disque de turbomachine, en position déverrouillée ;
  • la figure 5 est une vue de dessus selon la flèche V du verrou du dispositif des figures 3 et 4.
The invention and its advantages will be better understood on reading the detailed description which follows, given by way of illustration and not limitation. This description refers to the appended figures in which:
  • Figure 1 is a detail view in radial section of a turbomachine disk equipped with a known type of locking device;
  • Figure 2 is a detail view in perspective of a portion of the rotor drum of a turbomachine;
  • Figure 3 is a detail view in radial section showing an example of a locking device according to the invention and a neighboring blade, mounted on a turbomachine disk, the device being in the locked position;
  • Figure 4 is a detail view in radial section showing the example of the locking device of Figure 3, mounted on a turbomachine disk, in the unlocked position;
  • Figure 5 is a top view along the arrow V of the lock of the device of Figures 3 and 4.

L'invention se destine à tout type de turbomachine : turboréacteur, turbopropulseur, turbine à gaz terrestre... Dans l'exemple qui suit, on s'intéresse à un turboréacteur d'avion et, plus particulièrement, au rotor du compresseur basse pression de ce turboréacteur. Un tel rotor est constitué d'un tambour formé d'un empilement de disques à la périphérie desquels sont fixées des aubes, dont la tête reste libre.The invention is intended for any type of turbomachine: turbojet, turboprop, land gas turbine ... In the following example, we are interested in an aircraft turbojet and, more particularly, the rotor of the low pressure compressor of this turbojet. Such a rotor consists of a drum formed of a stack of disks on the periphery of which are fixed blades, whose head remains free.

Sur les dessins, on a représenté (voir figure 2) un disque 7 porteur d'aubes 13 faisant partie du tambour d'un tel rotor. Ce tambour est constitué par plusieurs disques 7 de ce type et chaque disque porte à sa périphérie une pluralité d'aubes 13 (voir figure 3).In the drawings, there is shown (see Figure 2) a disc 7 carrying vanes 13 forming part of the drum of such a rotor. This drum is constituted by several disks 7 of this type and each disk carries at its periphery a plurality of vanes 13 (see FIG. 3).

Les aubes 13 sont retenues dans une rainure 6, s'étendant circonférentiellement à la surface externe du disque 7. Une aube 13 comporte à sa base une plateforme 16 et un pied d'aube 18, dit à "attache marteau", qui s'étend sous ladite plateforme 16 sur une partie de la largeur de celle-ci. Le pied d'aube 18 est engagé et retenu dans ladite rainure 6 du disque 7. Sur la figure 3, la position du pied d'aube 18 dans la rainure 6 apparaît en pointillé.The blades 13 are retained in a groove 6, extending circumferentially to the outer surface of the disk 7. A blade 13 comprises at its base a platform 16 and a blade root 18, said to "hammer clip", which is extends under said platform 16 over part of the width thereof. The blade root 18 is engaged and retained in said groove 6 of the disk 7. In FIG. 3, the position of the blade root 18 in the groove 6 appears in phantom.

La rainure 6 est délimitée dans sa partie supérieure, par une première lèvre, ou lèvre amont 9, et par une deuxième lèvre, ou lèvre aval 11. Dans la présente demande, l'amont et l'aval sont définis par rapport au sens normal de la circulation des gaz à travers la turbomachine.The groove 6 is delimited in its upper part, by a first lip, or upstream lip 9, and by a second lip, or downstream lip 11. In the present application, the upstream and downstream are defined relative to the normal direction the circulation of gases through the turbomachine.

La plateforme 16 d'une aube 13 vient recouvrir un secteur de la rainure 6. Une fois toutes les aubes 13 mises en place, les plateformes 16, côte à côte, reconstituent une surface annulaire qui délimite extérieurement une partie de la veine conique du compresseur à l'intérieur de laquelle circule les gaz.The platform 16 of a blade 13 comes to cover a sector of the groove 6. Once all the blades 13 are in place, the platforms 16, side by side, reconstruct an annular surface which externally delimits a portion of the conical flow of the compressor. inside which the gases circulate.

Le montage des aubes 13 impose de réaliser au moins une encoche d'introduction 30 sur l'une des lèvres annulaire 9, 11 de la rainure 6, ici les deux lèvres présentent une encoche d'introduction 30. Cette encoche 30 permet d'engager les pieds d'aube 18 les uns après les autres dans la rainure 6. Une fois qu'un pied d'aube 18 est engagé dans cette rainure 6, on fait coulisser l'aube 13 correspondante, circonférentiellement le long de la rainure jusqu'à sa position finale.The mounting of the blades 13 requires at least one insertion slot 30 to be made on one of the annular lips 9, 11 of the groove 6, in this case the two lips have an insertion notch 30. This notch 30 makes it possible to engage the dawning feet 18 one after the other in the groove 6. Once a blade root 18 is engaged in this groove 6, the corresponding blade 13 is slid circumferentially along the groove until at its final position.

Pour éviter que les aubes 13 puissent ultérieurement se déplacer circonférentiellement (sinon le pied d'une des aube 13 risquerait de d'échapper de l'encoche 30 ce qui provoquerait l'échappement de cette aube), on prévoit de monter des dispositifs de blocage 1 selon l'invention dans la rainure 6, ces dispositifs 1 étant immobilisés dans la rainure 6, entre deux aubes 13, et repartis circonférentiellement dans la rainure 6, à des emplacements choisis.To prevent the blades 13 can subsequently move circumferentially (otherwise the foot of one blade 13 might escape from the notch 30 which would cause the escape of the blade), it is expected to mount blocking devices 1 according to the invention in the groove 6, these devices 1 being immobilized in the groove 6, between two blades 13, and distributed circumferentially in the groove 6 at selected locations.

Chaque dispositif de blocage 1 comprend un verrou 5 traversé par une vis 3. Le verrou présente deux faces latérales amont 19 et aval 21 opposées. Une fois le verrou 5 dans la rainure 6, les faces latérales amont 19 et aval 21 font respectivement face aux lèvres amont 9 et aval 11 de cette rainure.Each locking device 1 comprises a latch 5 traversed by a screw 3. The latch has two opposite upstream side faces 21 and downstream 21 opposite. Once the lock 5 in the groove 6, the upstream side faces 19 and downstream 21 respectively face the upstream lips 9 and downstream 11 of this groove.

Sur la face latérale aval 21, font saillie un tenon 15 et, sous ce tenon, une portée radiale 17 (voir figure 5). La portée radiale 17 s'étend sensiblement sur toute la largeur de la face latérale 21, tandis que le tenon 15 s'étend sur une partie seulement de cette largeur. Le tenon 15 est destiné à se loger dans une encoche 23 ménagé dans la lèvre aval 11 de la rainure 6 et la portée radiale 17 est destinée à venir en butée contre la lèvre aval 11 lorsque le verrou 5 est en position verrouillée (voir figure 3).On the downstream side face 21, project a stud 15 and, under this pin, a radial bearing 17 (see Figure 5). The radial span 17 extends substantially over the entire width of the side face 21, while the pin 15 extends over only a portion of this width. The pin 15 is intended to be housed in a notch 23 formed in the downstream lip 11 of the groove 6 and the radial bearing 17 is intended to abut against the downstream lip 11 when the latch 5 is in the locked position (see FIG. ).

La face latérale amont 19 du verrou est dépourvue de tenon ou de portée radiale. Cette face 19 est courbe et constitue une surface d'appui en rotation autour de laquelle le verrou 5 pivote pour passer de sa position déverrouillée à sa position verrouillée (ou inversement). Le changement de position se fait lors du vissage (ou du dévissage) de la vis 3. La face latérale amont 19 du verrou 5 est logée entre le bord supérieur de la lèvre amont 9 de la rainure 6 et le fond 8 de cette rainure. La paroi du logement recevant la face latérale amont du verrou 5, est également courbe. La forme de cette paroi et celle de la face latérale amont 19 correspondent de manière à favoriser le guidage du verrou 5 lors de son pivotement.The upstream side face 19 of the lock is devoid of tenon or radial bearing. This face 19 is curved and constitutes a rotating bearing surface around which the latch 5 pivots to move from its unlocked position to its locked position (or vice versa). The change of position is made during the screwing (or unscrewing) of the screw 3. The upstream side face 19 of the lock 5 is housed between the upper edge of the upstream lip 9 of the groove 6 and the bottom 8 of this groove. The wall of the housing receiving the upstream side face of the latch 5, is also curved. The shape of this wall and that of the upstream side face 19 correspond to promote the guiding of the latch 5 during its pivoting.

De manière à garantir un jeu d'assemblage constant entre le verrou 5 et le disque 7, la face latérale aval 21 du verrou 5 présente, dans les régions ou il n'y a ni le tenon 15 ni la portée radiale 17, une courbure telle que le jeu J entre la face 21 et la lèvre aval 11 de la rainure reste sensiblement constant lors de la rotation du verrou. Un exemple de face 21 de ce type est représenté sur les figures 3 et 4. En coupe radiale (voir figure 4), la face 21 s'inscrit dans un arc de cercle C de diamètre approprié, centré au point O qui appartient à la surface d'appui en rotation formée par la face latérale 19. On notera qu'un point situé sur la face 21 décrit, sensiblement, une partie de l'arc de cercle C lorsque le verrou 5 pivote.In order to guarantee a constant assembly clearance between the lock 5 and the disc 7, the downstream lateral face 21 of the lock 5 has, in regions where there is neither the tenon nor the radial bearing surface 17, a curvature such that the clearance J between the face 21 and the downstream lip 11 of the groove remains substantially constant during the rotation of the latch. An example of a face 21 of this type is shown in FIGS. 3 and 4. In radial section (see FIG. 4), the face 21 is part of an arc of circle C of appropriate diameter, centered at the point O which belongs to the rotating support surface formed by the side face 19. Note that a point on the face 21 substantially describes part of the arc C when the latch 5 pivots.

Selon une alternative, non représentée, la face latérale aval 21 est sensiblement plane. Ceci permet de simplifier l'usinage du verrou, mais le jeu d'assemblage entre le verrou 5 et le disque 7 varie lors de la rotation du verrou (il faut donc veiller à ce que ce jeu ne soit pas trop élevé).According to an alternative, not shown, the downstream side face 21 is substantially flat. This simplifies the machining of the lock, but the assembly clearance between the lock 5 and the disc 7 varies during the rotation of the lock (so be careful that this game is not too high).

Comme évoqué précédemment, le dispositif de blocage selon l'invention se révèle intéressant lorsque les lèvres 9 et 11 de la rainure 6 sont décalées, c'est-à-dire situées à des distances différentes, D et d, de l'axe de rotation A du disque (voir figure 3).As mentioned above, the locking device according to the invention is interesting when the lips 9 and 11 of the groove 6 are offset, that is to say located at different distances, D and d, of the axis of A rotation of the disc (see Figure 3).

Sur la figure 3, on a représenté le plan moyen P passant par les faces inférieures des lèvres 9, 11 contre lesquelles la partie supérieure de la face latérale amont 19 et la porté radiale 17 viennent respectivement en butée, dans la position verrouillée du verrou 5. Lorsque les lèvres 9 et 11 sont décalées, le plan P est incliné d'un angle a par rapport à l'axe A de rotation du disque, qui correspond également à l'axe de la turbomachine. Lorsque l'angle a est supérieur ou égal à 25°, il est préférable d'utiliser un dispositif de blocage selon l'invention car l'utilisation des dispositifs connus, dans lesquels le verrou monte en translation suivant l'axe de la vis, donne de très mauvais résultats en terme de verrouillage.FIG. 3 shows the average plane P passing through the lower faces of the lips 9, 11 against which the upper part of the upstream lateral face 19 and the radial bearing 17 respectively abut in the locked position of the lock 5. When the lips 9 and 11 are offset, the plane P is inclined at an angle with respect to the axis A of rotation of the disk, which also corresponds to the axis of the turbomachine. When the angle a is greater than or equal to 25 °, it is preferable to use a locking device according to the invention because the use of known devices, in which the lock is mounted in translation along the axis of the screw, gives very poor results in terms of locking.

Claims (11)

Dispositif pour bloquer les aubes (13) d'un disque (7) de turbomachine dans la direction circonférentielle du disque, ces aubes étant retenues par leur pied (18) dans une rainure circonférentielle (6) du disque, le dispositif étant destiné à être introduit dans ladite rainure (6) et comprenant un verrou (5) passant d'une position déverrouillée à une position verrouillée sous l'action de moyens de poussée (3) en appui sur le fond de la rainure (6), ce verrou présentant une première et une deuxième faces latérales opposées (9, 11), caractérisé en ce que la première face latérale (19) du verrou présente une surface d'appui en rotation, et en ce que ledit verrou (5) est apte à se déplacer en rotation, autour de ladite surface d'appui, dans un plan perpendiculaire à la direction circonférentielle, pour passer de sa position déverrouillée à sa position verrouillée.Device for locking the vanes (13) of a turbomachine disk (7) in the circumferential direction of the disk, said blades being held by their foot (18) in a circumferential groove (6) of the disk, the device being intended to be introduced into said groove (6) and comprising a latch (5) passing from an unlocked position to a locked position under the action of pushing means (3) resting on the bottom of the groove (6), this lock presenting first and second opposite lateral faces (9, 11), characterized in that the first lateral face (19) of the latch has a bearing surface in rotation, and in that said latch (5) is able to move in rotation, around said bearing surface, in a plane perpendicular to the circumferential direction, to move from its unlocked position to its locked position. Dispositif selon la revendication 1, caractérisé en ce que la première face latérale (19) du verrou est courbe et constitue ladite surface d'appui en rotation.Device according to claim 1, characterized in that the first lateral face (19) of the latch is curved and constitutes said bearing surface in rotation. Dispositif selon la revendication 1 ou 2, caractérisé en ce que lesdits moyens de poussée comprennent une vis (3) coopérant avec un trou fileté traversant le verrou (5).Device according to claim 1 or 2, characterized in that said thrust means comprise a screw (3) cooperating with a threaded hole passing through the lock (5). Dispositif selon l'une quelconque des revendications 1 à 3, caractérisé en ce qu'un tenon (15) fait saillie sur la deuxième face latérale (21) du verrou, ce tenon permettant d'empêcher le déplacement circonférentiel du verrou lorsque celui-ci est dans sa position verrouillée.Device according to any one of claims 1 to 3, characterized in that a tenon (15) projects on the second lateral face (21) of the lock, this tenon to prevent the circumferential movement of the lock when the latter is in its locked position. Dispositif selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'une portée radiale (17) fait saillie sur la deuxième face latérale (21) du verrou, en dessous du tenon (15), cette portée permettant d'empêcher le déplacement radial du verrou (5) lorsque celui-ci est dans sa position verrouillée.Device according to any one of claims 1 to 4, characterized in that a radial bearing (17) projects from the second lateral face (21) of the lock, below the tenon (15), this bearing being used to prevent the radial displacement of the latch (5) when it is in its locked position. Disque de turbomachine présentant une rainure circonférentielle (6) dans laquelle des aubes (13) sont susceptibles d'être retenues par leur pied (18), cette rainure étant délimitée, dans sa partie supérieure, par des première et deuxième lèvres (9, 11), le disque comprenant un dispositif (1) selon l'une quelconque des revendications 1 à 5 permettant de bloquer les aubes (13) dans la direction circonférentielle du disque.A turbomachine disc having a circumferential groove (6) in which blades (13) are capable of being retained by their feet (18), this groove being delimited, in its upper part, by first and second lips (9, 11 ), the disk comprising a device (1) according to any one of claims 1 to 5 for blocking the vanes (13) in the circumferential direction of the disk. Disque de turbomachine selon la revendication 6, caractérisé en ce qu'il présente, entre le bord supérieur de la première lèvre (9) et le fond (8) de la rainure (6), un logement pour recevoir ladite surface d'appui en rotation, dont la forme est sensiblement complémentaire de celle de la surface d'appui.Turbomachine disc according to Claim 6, characterized in that it has, between the upper edge of the first lip (9) and the bottom (8) of the groove (6), a housing for receiving said bearing surface in rotation, whose shape is substantially complementary to that of the bearing surface. Disque de turbomachine selon la revendication 6 ou 7, caractérisé en ce que la deuxième face latérale (21) du verrou est courbe avec une courbure telle que le jeu (J) entre cette deuxième face (21) et la deuxième lèvre (11) de la rainure (6) reste sensiblement constant lors de la rotation du verrou.Turbomachine disk according to claim 6 or 7, characterized in that the second lateral face (21) of the latch is curved with a curvature such that the clearance (J) between this second face (21) and the second lip (11) of the groove (6) remains substantially constant during the rotation of the latch. Disque de turbomachine selon l'une quelconque des revendications 6 à 8, caractérisé en ce que la première et la deuxième lèvre (9, 11) de ladite rainure sont situées à des distances différentes de l'axe de rotation (A) du disque.Turbomachine disk according to any one of claims 6 to 8, characterized in that the first and the second lip (9, 11) of said groove are located at different distances from the axis of rotation (A) of the disk. Tambour de rotor de turbomachine, caractérisé en ce qu'il comprend un disque (7) selon l'une quelconque des revendications 6 à 9.Turbomachine rotor drum, characterized in that it comprises a disc (7) according to any one of claims 6 to 9. Turbomachine comprenant un disque (7) selon l'une quelconque des revendications 6 à 9.Turbomachine comprising a disk (7) according to any one of Claims 6 to 9.
EP05292779.5A 2005-12-23 2005-12-23 Device for locking the blades of a turbomachine disk Active EP1801355B1 (en)

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2971542A1 (en) * 2011-02-16 2012-08-17 Snecma AUTON CIRCONFERENTIAL BLOCKING DEVICE FOR TURBOMACHINE, WITH RADIAL DEPLOYMENT BY ROTATION MOTION OF AN ORGAN OF THE DEVICE
EP2719866A1 (en) 2012-10-12 2014-04-16 Techspace Aero S.A. Lock for drum blades in a circumferential rotor groove
EP2333243A3 (en) * 2009-11-19 2014-06-18 United Technologies Corporation Rotor with circumferencial slot, corresponding lock, disk and assembly method
EP2873808A1 (en) 2013-11-19 2015-05-20 MTU Aero Engines GmbH Rotor-blade group, method and flow engine
EP2602435A3 (en) * 2011-12-07 2017-04-05 United Technologies Corporation Turbomachine rotor and corresponding assembly method

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
US3721506A (en) * 1971-05-25 1973-03-20 Gen Electric Split-nut blade locking assembly
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
USH1258H (en) * 1992-09-16 1993-12-07 The United States Of America As Represented By The Secretary Of The Air Force Blade lock screw
US5584658A (en) * 1994-08-03 1996-12-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbocompressor disk provided with an asymmetrical circular groove
US20030123986A1 (en) * 2001-11-22 2003-07-03 Snecma Moteurs Device for immobilizing blades in a slot of a disk

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2097480B (en) * 1981-04-29 1984-06-06 Rolls Royce Rotor blade fixing in circumferential slot
FR2810366B1 (en) * 2000-06-15 2002-10-11 Snecma Moteurs DEVICE FOR LOCKING BLADES WITH HAMMER FASTENERS ON A DISC
FR2857405B1 (en) * 2003-07-07 2005-09-30 Snecma Moteurs IMPROVING THE RETENTION CAPACITY OF A DISSYMMETRIC HAMMER BLADE
FR2886336B1 (en) * 2005-05-26 2007-08-24 Snecma Moteurs Sa IMPROVEMENT TO A ROTOR AUBAGEE WHEEL TO ENHANCE THE LOCKING OF AUBES

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
US3721506A (en) * 1971-05-25 1973-03-20 Gen Electric Split-nut blade locking assembly
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
USH1258H (en) * 1992-09-16 1993-12-07 The United States Of America As Represented By The Secretary Of The Air Force Blade lock screw
US5584658A (en) * 1994-08-03 1996-12-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbocompressor disk provided with an asymmetrical circular groove
US20030123986A1 (en) * 2001-11-22 2003-07-03 Snecma Moteurs Device for immobilizing blades in a slot of a disk

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2333243A3 (en) * 2009-11-19 2014-06-18 United Technologies Corporation Rotor with circumferencial slot, corresponding lock, disk and assembly method
FR2971542A1 (en) * 2011-02-16 2012-08-17 Snecma AUTON CIRCONFERENTIAL BLOCKING DEVICE FOR TURBOMACHINE, WITH RADIAL DEPLOYMENT BY ROTATION MOTION OF AN ORGAN OF THE DEVICE
WO2012110735A1 (en) * 2011-02-16 2012-08-23 Snecma Device for blocking vanes around a periphery, for a turbomachine, to be deployed radially by a rotational movement of a member of the device
EP2602435A3 (en) * 2011-12-07 2017-04-05 United Technologies Corporation Turbomachine rotor and corresponding assembly method
US10107114B2 (en) 2011-12-07 2018-10-23 United Technologies Corporation Rotor with relief features and one-sided load slots
US10704401B2 (en) 2011-12-07 2020-07-07 Raytheon Technologies Corporation Rotor with relief features and one-sided load slots
EP2719866A1 (en) 2012-10-12 2014-04-16 Techspace Aero S.A. Lock for drum blades in a circumferential rotor groove
US10066487B2 (en) 2012-10-12 2018-09-04 Safran Aero Boosters Sa Drum blade lock in a circumferential rotor groove
EP2873808A1 (en) 2013-11-19 2015-05-20 MTU Aero Engines GmbH Rotor-blade group, method and flow engine
DE102013223583A1 (en) 2013-11-19 2015-05-21 MTU Aero Engines AG Shovel-disc composite, method and turbomachine
US10041363B2 (en) 2013-11-19 2018-08-07 MTU Aero Engines AG Blade-disk assembly, method and turbomachine

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