EP1489266B1 - Retention of a blade with an asymmetric hammerhead foot using platform stiffeners - Google Patents

Retention of a blade with an asymmetric hammerhead foot using platform stiffeners Download PDF

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Publication number
EP1489266B1
EP1489266B1 EP04291450A EP04291450A EP1489266B1 EP 1489266 B1 EP1489266 B1 EP 1489266B1 EP 04291450 A EP04291450 A EP 04291450A EP 04291450 A EP04291450 A EP 04291450A EP 1489266 B1 EP1489266 B1 EP 1489266B1
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EP
European Patent Office
Prior art keywords
disk
upstream
downstream
blade
rib
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Expired - Lifetime
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EP04291450A
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German (de)
French (fr)
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EP1489266A1 (en
Inventor
Claude Lejars
Patrick Reghezza
Jérôme Mace
Christophe Follonier
Bruce Pontoizeau
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • 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
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a turbomachine blade which extends in a conical vein and which is retained in a peripheral groove of said disk by hammer-type fasteners, each of said blades further comprising a platform whose radially outer face delimits the vein of the gas flow and whose radially inner face has an upstream rib and a downstream rib disposed in planes perpendicular to the axis of rotation of said disk and respectively adjoining an upstream ring and a downstream ring formed at the periphery of said disk from and other of said groove to ensure sealing in these areas.
  • the radius of the vein of the primary flow decreases from upstream to downstream in the low pressure compressor.
  • the conicity of this vein is very high in the last stages of this compressor.
  • the blades of these stages extend obliquely in the vein relative to the plane perpendicular to the axis of rotation of the compressor, that is to say, obliquely with respect to the radial direction of the centrifugal forces.
  • the invention relates more specifically to the bladed discs of this type, in which the blades are retained by a hammer-type fastener in a peripheral groove of the disc, this groove being delimited by an upstream lip and a downstream lip, whose surfaces connected to the bottom of the groove form spans on which the flanks of the blade roots are supported during the operation of the turbomachine, these bearing surfaces supporting reaction forces whose resultant is preferably in the plane of the centrifugal forces to which the blades are subjected .
  • EP 0 695 856 proposed an asymmetrical hammer clip, that is to say that the angle of the range of the upstream lip, which has the largest diameter, with respect to a plane perpendicular to the axis of rotation, is greater than 1 angel formed between the scope of the downstream lip and said plane.
  • FIG. 4B of this document shows the blade-disk connection in the case where the blade, subjected to a large axial stress, as a result of an impact of a debris ingested by the turbomachine, tends to pivot around a center of rotation C located at the upstream end of the range of the downstream lip. Because of the conformation of the throat and the blade root, dawn can be released in case of significant shock.
  • US 5,271,718 discloses symmetrical hammer-blade type blades having platforms having on their radially inner face circumferentially and axially extending ribs which are intended to avoid vibratory resonances, two of these circumferential ribs cooperating with rings formed at the periphery of the disc to seal in these areas.
  • the axial thickness of these ribs is substantially equal to the thickness of the rings.
  • the downstream rib supports a large part of the forces generated and can skip axially on the downstream ring, which can cause the release of the blade.
  • the ends of these ribs can slip on the rings which, failing to cause the release of the blade, may cause an overlap of the adjacent edges of two neighboring blades.
  • the object of the invention is to provide a modified blade that overcomes these disadvantages.
  • This arrangement makes it possible to provide a plane and homogeneous contact surface between the rib and the ring of the disc which optionally has a groove for receiving a sealing ring.
  • the thickness of the upstream rib in the axial direction is greater than the thickness of the upstream ring.
  • the height of said ribs is large enough to limit the possibility of overlapping platforms.
  • FIG. 1 shows a blade 1 whose dovetail shaped foot 2 comprises an upstream flank 3a and a downstream flank 3b whose surfaces bear on bearing surfaces 4a, 4b of the internal faces of an upstream lip 5 and of a downstream lip 6 which delimit a groove 7 formed at the periphery of a disc 12 and whose bottom 8 is connected to the bearing surfaces 4a and 4b by rounded surfaces 9a and 9b respectively.
  • the blade 1 extends in a strongly conical vein, that is to say that the upstream lip 5 has a greater diameter than the downstream lip 6, and the bearings 4a and 4b are, with the plane perpendicular to the axis of rotation of the disc 2, different angles.
  • the disc 12 has upstream a first radial extension 20, called upstream ring in the present memory, of small axial thickness, and downstream a second radial extension 21, called downstream ring, which has a groove 22 for receiving a rod of sealing not shown in the drawings for the sake of clarity.
  • the upstream and downstream rings 21 have cylindrical peripheral surfaces 20a and 21a, of revolution about the axis of rotation of the disc 12.
  • the blade 2 has between the foot 2 and the aerodynamic portion a platform 30 whose radially outer face 30a delimits the conical vein, and whose radially inner face 30b has an upstream rib 32 and a downstream groove 33 which extend circumferentially in the immediate vicinity of the peripheral surfaces 20a and 21a of the upstream and downstream rings 20 and 21.
  • These ribs 32 and 33 have in particular cylindrical surface portions, respectively 32a and 32b, of revolution about the axis of rotation of the disc 1 which cover the peripheral surfaces 20a and 21a of the upstream and downstream rings 21 and 22, and whose width in the axial direction is greater than the width of the peripheral surfaces 20a and 21a.
  • the width of the surfaces 32a and 33a is calculated so as to always provide sufficient seating on the rings 20 and 21 in all ranges of movement of the blade 1 in operation.
  • the height of the ribs 32 and 33 is calculated such that, regardless of the displacement of the adjacent blades, as a result of a tangential stress, the adjacent edges of the platforms 30 of two consecutive blades 1a and 1b can not overlap as shown in Figure 2.
  • FIG. 2 shows blades 1a and 1b which furthermore have other stiffening ribs, arranged between the upstream rib 32 and the downstream rib 33.
  • This blade could also include ribs directed axially without departing from the scope of the invention.

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

Description

L'invention concerne un disque aubagé de turbomachine qui s'étend dans une veine conique et qui est retenu dans une gorge périphérique dudit disque par des attaches du type marteau, chacune desdites aubes comportant en outre une plate-forme dont la face radialement extérieure délimite la veine du flux gazeux et dont la face radialement intérieure présente une nervure amont et une nervure aval disposées dans des plans perpendiculaires à l'axe de rotation dudit disque et jouxtant respectivement un anneau amont et un anneau aval formés à la périphérie dudit disque de part et d'autre de ladite gorge afin d'assurer l'étanchéité dans ces zones.The invention relates to a turbomachine blade which extends in a conical vein and which is retained in a peripheral groove of said disk by hammer-type fasteners, each of said blades further comprising a platform whose radially outer face delimits the vein of the gas flow and whose radially inner face has an upstream rib and a downstream rib disposed in planes perpendicular to the axis of rotation of said disk and respectively adjoining an upstream ring and a downstream ring formed at the periphery of said disk from and other of said groove to ensure sealing in these areas.

Dans les turboréacteurs à grand taux de dilution, le rayon de la veine du flux primaire diminue de l'amont vers l'aval dans le compresseur basse pression. La conicité de cette veine est très élevée au niveau des derniers étages de ce compresseur. Les aubes de ces étages s'étendent obliquement dans la veine par rapport au plan perpendiculaire à l'axe de rotation du compresseur, c'est-à-dire obliquement par rapport à la direction radiale des forces centrifuges.In turbojets with a high dilution ratio, the radius of the vein of the primary flow decreases from upstream to downstream in the low pressure compressor. The conicity of this vein is very high in the last stages of this compressor. The blades of these stages extend obliquely in the vein relative to the plane perpendicular to the axis of rotation of the compressor, that is to say, obliquely with respect to the radial direction of the centrifugal forces.

L'invention concerne plus précisément les disques aubagés de ce type, dans lesquels les aubes sont retenues par une attache de type marteau dans une gorge périphérique du disque, cette gorge étant délimitée par une lèvre amont et une lèvre aval, dont les surfaces raccordées au fond de la gorge forment des portées sur lesquelles les flancs des pieds d'aube sont en appui lors du fonctionnement de la turbomachine, ces portées supportant des efforts de réaction dont la résultante est de préférence dans le plan des forces centrifuges auxquelles les aubes sont soumises.The invention relates more specifically to the bladed discs of this type, in which the blades are retained by a hammer-type fastener in a peripheral groove of the disc, this groove being delimited by an upstream lip and a downstream lip, whose surfaces connected to the bottom of the groove form spans on which the flanks of the blade roots are supported during the operation of the turbomachine, these bearing surfaces supporting reaction forces whose resultant is preferably in the plane of the centrifugal forces to which the blades are subjected .

Pour obtenir ce résultat, EP 0 695 856 a proposé une attache marteau asymétrique, c'est-à-dire que l'angle de la portée de la lèvre amont, qui a le plus grand diamètre, par rapport à un plan perpendiculaire à l'axe de rotation, est supérieure à l'ange formé entre la portée de la lèvre aval et ledit plan. La figure 4B de ce document montre la liaison aube-disque dans le cas où l'aube, soumise à une sollicitation axiale importante, par suite d'un choc d'un débris ingéré par la turbomachine, a tendance à pivoter autour d'un centre de rotation C situé à l'extrémité amont de la portée de la lèvre aval. Du fait de la conformation de la gorge et du pied d'aube, l'aube peut se dégager en cas de choc important.To obtain this result, EP 0 695 856 proposed an asymmetrical hammer clip, that is to say that the angle of the range of the upstream lip, which has the largest diameter, with respect to a plane perpendicular to the axis of rotation, is greater than 1 angel formed between the scope of the downstream lip and said plane. FIG. 4B of this document shows the blade-disk connection in the case where the blade, subjected to a large axial stress, as a result of an impact of a debris ingested by the turbomachine, tends to pivot around a center of rotation C located at the upstream end of the range of the downstream lip. Because of the conformation of the throat and the blade root, dawn can be released in case of significant shock.

US 5 271 718 décrit des aubes de type attache marteau symétrique qui présentent des plates-formes ayant sur leur face radialement intérieure des nervures qui s'étendent dans le sens circonférentiel et dans le sens axial et qui sont destinées à éviter les résonances vibratoires, deux de ces nervures circonférentielles coopérant avec des anneaux formés à la périphérie du disque pour assurer l'étanchéité dans ces zones. L'épaisseur axiale de ces nervures est sensiblement égale à l'épaisseur des anneaux. Ce document montre que les nervures axiales formées sur la face radialement intérieure des plates-formes ont une hauteur inférieure à celle des nervures coopérant avec les anneaux. En cas de sollicitation axiale importante, la nervure située en aval supporte une grande partie des efforts générés et peut riper axialement sur l'anneau aval, ce qui peut provoquer le dégagement de l'aube.
En outre, en cas de sollicitation tangentielle, les extrémités de ces nervures peuvent riper sur les anneaux ce qui, à défaut d'entraîner le dégagement de l'aube, peut entraîner un chevauchement des bords adjacents de deux aubes voisines. US 5,271,718 discloses symmetrical hammer-blade type blades having platforms having on their radially inner face circumferentially and axially extending ribs which are intended to avoid vibratory resonances, two of these circumferential ribs cooperating with rings formed at the periphery of the disc to seal in these areas. The axial thickness of these ribs is substantially equal to the thickness of the rings. This document shows that the axial ribs formed on the radially inner face of the platforms have a height less than that of the ribs cooperating with the rings. In case of significant axial stress, the downstream rib supports a large part of the forces generated and can skip axially on the downstream ring, which can cause the release of the blade.
In addition, in case of tangential stress, the ends of these ribs can slip on the rings which, failing to cause the release of the blade, may cause an overlap of the adjacent edges of two neighboring blades.

Ces désordres peuvent se produire notamment dans un disque aubagé du type mentionné dans l'introduction du présent mémoire, dans lequel les aubes s'étendent dans une veine fortement conique.
Le but de l'invention est de proposer une aube modifiée qui permette de pallier ces inconvénients.These disorders can occur in particular in a blisk of the type mentioned in the introduction of this memo, wherein the blades extend in a strongly conical vein.
The object of the invention is to provide a modified blade that overcomes these disadvantages.

Ce but est atteint selon l'invention telle que définie par la revendication 1 par le fait que l'épaisseur de la nervure aval, dans la direction axiale, est supérieure à l'épaisseur de l'anneau aval.This object is achieved according to the invention as defined by claim 1 in that the thickness of the downstream rib in the axial direction is greater than the thickness of the downstream ring.

Cette disposition permet d'offrir une surface de contact plane et homogène entre la nervure et l'anneau du disque qui présente éventuellement une gorge pour recevoir un jonc d'étanchéité.This arrangement makes it possible to provide a plane and homogeneous contact surface between the rib and the ring of the disc which optionally has a groove for receiving a sealing ring.

Selon une autre caractéristique avantageuse, l'épaisseur de la nervure amont dans la direction axiale est supérieure à l'épaisseur de l'anneau amont.According to another advantageous characteristic, the thickness of the upstream rib in the axial direction is greater than the thickness of the upstream ring.

De préférence, la hauteur desdites nervures est suffisamment grande pour limiter la possibilité de chevauchement des plates-formes.Preferably, the height of said ribs is large enough to limit the possibility of overlapping platforms.

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

  • la figure 1 est une vue en coupe, selon un plan contenant l'axe de rotation, d'une liaison aube/disque selon l'invention, l'aube s'étendant dans une veine fortement conique, et l'attache étant du type marteau asymétrique, et
  • la figure 2 est une vue en perspective et de dessous de deux aubes adjacentes 1a et 1b.
Other features and advantages of the invention will emerge on reading the following description given by way of example and with reference to the appended drawings in which:
  • FIG. 1 is a sectional view, along a plane containing the axis of rotation, of a blade / disk connection according to the invention, the blade extending in a strongly conical vein, and the fastener being of the type asymmetrical hammer, and
  • Figure 2 is a perspective view from below of two adjacent blades 1a and 1b.

La figure 1 montre une aube 1 dont le pied 2 en forme de queue d'aronde comporte un flanc amont 3a et un flanc aval 3b dont les surfaces sont en appui sur des portées 4a, 4b des faces internes d'une lèvre amont 5 et d'une lèvre aval 6 qui délimitent une gorge 7 formée à la périphérie d'un disque 12 et dont le fond 8 se raccorde aux portées 4a et 4b par des surfaces arrondies respectivement 9a et 9b.FIG. 1 shows a blade 1 whose dovetail shaped foot 2 comprises an upstream flank 3a and a downstream flank 3b whose surfaces bear on bearing surfaces 4a, 4b of the internal faces of an upstream lip 5 and of a downstream lip 6 which delimit a groove 7 formed at the periphery of a disc 12 and whose bottom 8 is connected to the bearing surfaces 4a and 4b by rounded surfaces 9a and 9b respectively.

En cas de sollicitations axiales importantes par suite d'un choc d'un débris sur la partie aérodynamique de l'aube 1, celle-ci a tendance à pivoter autour de l'extrémité amont C de la portée 4b de la lèvre aval 6. L'extrémité 10 du talon 11 du pied de l'aube 1, la plus éloignée du centre de rotation C, est sollicitée à décrire un cercle géométrique C.In the event of significant axial stresses due to a shock of debris on the aerodynamic part of the blade 1, the latter tends to pivot around the upstream end C of the bearing surface 4b of the downstream lip 6. The end 10 of the heel 11 of the root of the blade 1, the furthest away from the center of rotation C, is urged to describe a geometric circle C.

Il est à noter que l'aube 1 s'étend dans une veine fortement conique, c'est-à-dire que la lèvre amont 5 a un diamètre plus grand que la lèvre aval 6, et les portées 4a et 4b font, avec le plan perpendiculaire à l'axe de rotation du disque 2, des angles différents.It should be noted that the blade 1 extends in a strongly conical vein, that is to say that the upstream lip 5 has a greater diameter than the downstream lip 6, and the bearings 4a and 4b are, with the plane perpendicular to the axis of rotation of the disc 2, different angles.

Le disque 12 présente en amont une première extension radiale 20, appelé anneau amont dans le présent mémoire, de faible épaisseur axiale, et en aval une deuxième extension radiale 21, appelé anneau aval, qui comporte une gorge 22 destinée à recevoir un jonc d'étanchéité non montré sur le dessins par souci de clarté.The disc 12 has upstream a first radial extension 20, called upstream ring in the present memory, of small axial thickness, and downstream a second radial extension 21, called downstream ring, which has a groove 22 for receiving a rod of sealing not shown in the drawings for the sake of clarity.

Les anneaux amont 20 et aval 21 présentent des surfaces périphériques 20a et 21a cylindriques, de révolution autour de l'axe de rotation du disque 12.The upstream and downstream rings 21 have cylindrical peripheral surfaces 20a and 21a, of revolution about the axis of rotation of the disc 12.

L'aube 2 présente entre le pied 2 et la partie aérodynamique une plate-forme 30 dont la face radialement extérieure 30a délimite la veine conique, et dont la face radialement intérieure 30b comporte une nervure amont 32 et une rainure aval 33 qui s'étendent circonférentiellement au voisinage immédiat des surfaces périphériques 20a et 21a des anneaux amont 20 et aval 21.The blade 2 has between the foot 2 and the aerodynamic portion a platform 30 whose radially outer face 30a delimits the conical vein, and whose radially inner face 30b has an upstream rib 32 and a downstream groove 33 which extend circumferentially in the immediate vicinity of the peripheral surfaces 20a and 21a of the upstream and downstream rings 20 and 21.

Ces nervures 32 et 33 présentent notamment des portions de surface cylindriques, respectivement 32a et 32b, de révolution autour de l'axe de rotation du disque 1 qui recouvrent les surfaces périphériques 20a et 21a des anneaux amont 21 et aval 22, et dont la largeur dans le sens axial est supérieure à la largeur des surfaces périphériques 20a et 21a.These ribs 32 and 33 have in particular cylindrical surface portions, respectively 32a and 32b, of revolution about the axis of rotation of the disc 1 which cover the peripheral surfaces 20a and 21a of the upstream and downstream rings 21 and 22, and whose width in the axial direction is greater than the width of the peripheral surfaces 20a and 21a.

En cas d'une sollicitation axiale de l'aube 1 par suite du choc d'un débris, l'aube 1 a tendance à pivoter autour du point C. Cette sollicitation entraîne un appui positif de la nervure aval 33 sur l'anneau aval 21.In the case of an axial biasing of the blade 1 as a result of the shock of a debris, the blade 1 tends to pivot around the point C. This bias causes a positive support of the downstream rib 33 on the downstream ring 21.

Du fait que la surface 32b est cylindrique et large dans le sens axial, cette surface ne peut pas riper sur la surface périphérique 21a de l'anneau 21. Cette disposition empêche le pied d'aube 2 de s'échapper de la gorge 7 car elle limite le débattement de l'aube 1.Because the surface 32b is cylindrical and broad in the axial direction, this surface can not slip on the peripheral surface 21a of the ring 21. This arrangement prevents the blade root 2 from escaping the groove 7 because it limits the deflection of the dawn 1.

En cas d'une sollicitation tangentielle importante, les extrémités des deux nervures 32 et 33 sont en appui positif sur les surfaces périphériques 20a et 21a des anneaux amont 20 et aval 21.In the event of substantial tangential stress, the ends of the two ribs 32 and 33 bear positively on the peripheral surfaces 20a and 21a of the upstream and downstream rings 20 and 21.

La largeur des surfaces 32a et 33a est calculée de manière à toujours offrir une assise suffisante sur les anneaux 20 et 21 dans toutes les plages de déplacement de l'aube 1 en fonctionnement.The width of the surfaces 32a and 33a is calculated so as to always provide sufficient seating on the rings 20 and 21 in all ranges of movement of the blade 1 in operation.

La hauteur des nervures 32 et 33 est calculée de telle manière que, quel que soit le déplacement des aubes adjacentes, par suite d'une sollicitation tangentielle, les bords adjacents des plates-formes 30 de deux aubes consécutives 1a et 1b ne puissent se chevaucher, ainsi que cela est montré sur la figure 2.The height of the ribs 32 and 33 is calculated such that, regardless of the displacement of the adjacent blades, as a result of a tangential stress, the adjacent edges of the platforms 30 of two consecutive blades 1a and 1b can not overlap as shown in Figure 2.

Cette figure 2 montre des aubes 1a et 1b qui présentent en outre d'autres nervures de rigidification, disposées entre la nervure amont 32 et la nervure aval 33.This FIG. 2 shows blades 1a and 1b which furthermore have other stiffening ribs, arranged between the upstream rib 32 and the downstream rib 33.

Cette aube pourrait également comporter des nervures dirigées axialement sans sortir du cadre de l'invention.This blade could also include ribs directed axially without departing from the scope of the invention.

Claims (3)

  1. A bladed disk for a turbomachine, the disk including blades (1) which extend into a conical stream and which are held in a peripheral groove (7) of said disk (12) by hammerhead type fasteners, each of said blades further including a platform (30) whose radially-outer face (30a) defines the boundary of the gas flow stream and whose radially-inner face (30b) presents an upstream rib (32) and a downstream rib (33) disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring (20) and a downstream ring (21) formed at the periphery of said disk (12) on either side of said groove (7) in order to provide leaktightness in these zones, the disk being characterized by the fact that the thickness of the downstream rib (33) in the axial direction is greater than the thickness of the upstream ring (21).
  2. A disk according to claim 1, characterized by the fact that the thickness of the upstream rib (32) in the axial direction is greater than the thickness of the upstream ring (20).
  3. A disk according to claim 1 or claim 2, characterized by the fact that the height of the ribs is great enough to limit any possibility of platforms overlapping.
EP04291450A 2003-06-16 2004-06-10 Retention of a blade with an asymmetric hammerhead foot using platform stiffeners Expired - Lifetime EP1489266B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0307214 2003-06-16
FR0307214A FR2856105B1 (en) 2003-06-16 2003-06-16 IMPROVING THE RETENTION CAPACITY OF A DISSYMMETRIC HAMMER ATTACHED BLADE USING PLATFORM STIFFENERS

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EP1489266A1 EP1489266A1 (en) 2004-12-22
EP1489266B1 true EP1489266B1 (en) 2007-08-15

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EP (1) EP1489266B1 (en)
JP (1) JP4227077B2 (en)
CA (1) CA2470073C (en)
DE (1) DE602004008153T2 (en)
ES (1) ES2291833T3 (en)
FR (1) FR2856105B1 (en)
RU (1) RU2333366C2 (en)
UA (1) UA81901C2 (en)

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GB2332024B (en) 1997-12-03 2000-12-13 Rolls Royce Plc Rotary assembly
FR2812906B1 (en) 2000-08-10 2002-09-20 Snecma Moteurs AXIAL RETAINER RING OF A FLANGE ON A DISC

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RU2333366C2 (en) 2008-09-10
UA81901C2 (en) 2008-02-25
US7080974B2 (en) 2006-07-25
FR2856105B1 (en) 2007-05-25
DE602004008153D1 (en) 2007-09-27
ES2291833T3 (en) 2008-03-01
CA2470073A1 (en) 2004-12-16
RU2004118078A (en) 2006-01-10
DE602004008153T2 (en) 2008-05-15
US20040253113A1 (en) 2004-12-16
EP1489266A1 (en) 2004-12-22
JP4227077B2 (en) 2009-02-18
FR2856105A1 (en) 2004-12-17
JP2005009492A (en) 2005-01-13
CA2470073C (en) 2011-08-16

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