EP2425100B1 - Fan blade retainer with an elastomer - Google Patents

Fan blade retainer with an elastomer Download PDF

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Publication number
EP2425100B1
EP2425100B1 EP10718553.0A EP10718553A EP2425100B1 EP 2425100 B1 EP2425100 B1 EP 2425100B1 EP 10718553 A EP10718553 A EP 10718553A EP 2425100 B1 EP2425100 B1 EP 2425100B1
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EP
European Patent Office
Prior art keywords
shim
fan
root
fan blade
blade
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Active
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EP10718553.0A
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German (de)
French (fr)
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EP2425100A1 (en
Inventor
Patrick Jean-Louis Reghezza
Julien Tran
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP2425100A1 publication Critical patent/EP2425100A1/en
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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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers

Definitions

  • the present invention relates generally to the field of aircraft turbojet blowers, and more particularly to the shims intended to be interposed between the foot of the fan blades, and the bottom of the cells defined by the fan disk.
  • Such a turbojet fan is shown exploded on the figure 1 . It generally comprises a disk 2 centered on the axis 4 of the blower, disk on the periphery of which are made teeth 6 spaced circumferentially from each other, and each extending substantially longitudinally and radially, namely substantially parallel to the axis 4. Between two teeth 6 directly consecutive in the circumferential direction, they delimit a cell 8 for receiving the foot 12 of a fan blade 10. In known manner, each tooth has an enlarged head so as to to be able to ensure the retention of the blades in the radial direction towards the outside.
  • the cell 8 has a narrowed external radial end allowing the stamina of the blade 10 to pass, with a narrowed section compared to that of its foot 12.
  • the conferred assembly is of the dovetail type, or also called "fir fastener”.
  • the fan 1 comprises a shim 20 interposed between the lower end of the blade root 12, and a bottom 8a of the cell associated with the blade concerned.
  • the wedge 20 makes it possible to block the blade 10 in the radial direction towards the inside, and also contributes to the plating of the bearing surfaces of the foot 12 against the energy end of the teeth 6.
  • the wedge 20 comprises a stop 22 for axial retention of its associated blade, this stop 22 being intended to bear against a retention ring (not shown) carried by the disk 2 and centered on the axis 4.
  • the shim 20 conventionally has a metal frame 24 around which is placed one or more outer elements 26 made of elastomeric material, this element 26 being in contact with the bottom 8a of the cell and the radially inner end of the foot 12 of dawn.
  • each element 26 is made by injection molding on the metal reinforcement, which is preferably made of titanium.
  • the overmoulding process used is such as to cause the outer element 26 of elastomeric material to adhere to a support surface provided on the reinforcement 24.
  • outer member 26 also referred to as a delamination problem. Indeed, this problem arises essentially when the wedge 20 is inserted between the foot 12 and the bottom of the cell 8a during engine assembly and / or during handling operations requiring such a wedge introduction. As has been schematized on the figure 1 it is noted that the introduction of the wedge into its dedicated space is made by sliding it along its longitudinal direction 30, generally slightly curvilinear.
  • the blade retention properties associated with this wedge may no longer be satisfied.
  • the wedge also having a vibration reduction function within the blade, its deterioration leads to lowering the vibration damping level experienced by the fan blade in operation.
  • FR-A-2841609 discloses a shim having a metal frame and having recessed portions filled by overmolding with an elastomeric material.
  • the invention therefore aims to at least partially overcome the disadvantages mentioned above relating to the achievements of the prior art.
  • the invention firstly relates to a shim according to claim 1 or 2.
  • the wedge takes the form of a band extending in a longitudinal direction, said corrugated zone having a plurality of waves succeeding one another in the same direction.
  • the waves thus arranged make it possible to withstand the delamination of the outer element made of elastomer material even more effectively when the wedge is introduced between the blade root and the cell bottom. Indeed, these waves then constitute direct obstacles to the relative displacement between the frame and the outer element of the hold, in the longitudinal direction, which usually corresponds to the direction of introduction of the hold in its dedicated space under the dawn.
  • the outer element of elastomeric material is overmolded on the metal reinforcement, preferably by injection under pressure.
  • the metal reinforcement is made of titanium.
  • the invention also relates to a turbojet fan comprising a plurality of fan blades and a disk defining at its periphery a plurality of cells, the foot of each fan blade being housed in one of the cells, and a shim as described above being interposed between the bottom of the cell and said foot.
  • each shim travels along the foot of its associated fan blade.
  • each shim has an axial retention stop of its associated fan blade.
  • the invention also relates to an aircraft turbojet engine comprising a fan as described above.
  • a shim 120 according to a preferred embodiment of the present invention.
  • This shim whose outer shape is substantially identical or similar to that of the wedge 20 of the prior art described on figures 1 and 2 , also has a general shape of strip extending in a longitudinal direction 130, of substantially curvilinear shape, corresponding to the direction in which also extends the foot 12 of its associated blade and the cell bottom 8a.
  • the shim 120 is intended to be introduced between the blade 10 and the bottom 8a of the cell 8 shown in FIG. figure 1 , always for the purpose of retention of the dawn as well as damping of the vibrations undergone by this one.
  • the metal armature 124 preferably of titanium, is equipped with an outer element of elastomeric material referenced 126, which partially covers the outer surface of this armature.
  • the outer element 126 made by overmolding by pressure injection of elastomeric material on the armature 124, leaves free a portion of the outer surface of this armature.
  • each corrugated zone 136 is in fact formed from a succession of waves 140 between which there are rounded depressions 142.
  • the latter comes into the 142, which has the dual effect of increasing the adhesion surface of the element 126 on the armature 124, and to create a plurality of mechanical engagement of the waves of the armature in the recesses of the outer element, and vice versa.
  • each corrugated zone 136 follow one another in the longitudinal direction 130 in which the wedge 120 is usually moved relative to the disk 2, so as to be interposed between the blade root 12 and the cell bottom 8a.
  • two corrugated zones 136 oriented in opposite directions are provided, one of which may optionally be interrupted, in one or more places, by a portion of the armature 124 intended to constitute a part of the outer surface of the shim finished.
  • the two corrugated zones 136 are interconnected by a radially outer zone 146 and a radially internal zone (not visible on the figure 4 ), these two areas being preferably flat and parallel to the direction 130.
  • they are an integral part of the support surface 134 on which the element of elastomeric material 126 is intended to adhere, once the molding overmolding performed.
  • the shim 120 here also has a stop 122 for axial retention of its associated fan blade, having the same geometry as the abutment 22 shown on the shim 20 of the figure 1 .

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

Description

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention se rapporte de façon générale au domaine des soufflantes de turboréacteur pour aéronef, et plus particulièrement à celui des cales destinées à être interposées entre le pied des aubes de soufflante, et le fond des alvéoles définies par le disque de soufflante.The present invention relates generally to the field of aircraft turbojet blowers, and more particularly to the shims intended to be interposed between the foot of the fan blades, and the bottom of the cells defined by the fan disk.

ÉTAT DE LA TECHNIQUE ANTÉRIEURESTATE OF THE PRIOR ART

Une telle soufflante de turboréacteur est représentée de façon éclatée sur la figure 1. Elle comprend globalement un disque 2 centré sur l'axe 4 de la soufflante, disque à la périphérie duquel sont pratiquées des dents 6 espacées circonférentiellement les unes des autres, et s'étendant chacune sensiblement longitudinalement et radialement, à savoir sensiblement parallèlement à l'axe 4. Entre deux dents 6 directement consécutives dans la direction circonférentielle, celles-ci délimitent une alvéole 8 destinée à recevoir le pied 12 d'une aube de soufflante 10. De façon connue, chaque dent dispose d'une tête élargie de manière à pouvoir assurer la rétention des aubes dans la direction radiale vers l'extérieur. En d'autres termes, l'alvéole 8 présente une extrémité radiale externe rétrécie permettant le passage de l'échasse de l'aube 10, de section rétrécie par rapport à celle de son pied 12. Ainsi, l'assemblage conféré est du type queue d'aronde, ou encore dit « attache sapin ».Such a turbojet fan is shown exploded on the figure 1 . It generally comprises a disk 2 centered on the axis 4 of the blower, disk on the periphery of which are made teeth 6 spaced circumferentially from each other, and each extending substantially longitudinally and radially, namely substantially parallel to the axis 4. Between two teeth 6 directly consecutive in the circumferential direction, they delimit a cell 8 for receiving the foot 12 of a fan blade 10. In known manner, each tooth has an enlarged head so as to to be able to ensure the retention of the blades in the radial direction towards the outside. In other words, the cell 8 has a narrowed external radial end allowing the stamina of the blade 10 to pass, with a narrowed section compared to that of its foot 12. Thus, the conferred assembly is of the dovetail type, or also called "fir fastener".

En outre, associée à chaque aube 10, la soufflante 1 comprend une cale 20 interposée entre l'extrémité inférieure du pied d'aube 12, et un fond 8a de l'alvéole associée à l'aube concernée.In addition, associated with each blade 10, the fan 1 comprises a shim 20 interposed between the lower end of the blade root 12, and a bottom 8a of the cell associated with the blade concerned.

Comme cela est le mieux visible sur la figure 2, la cale 20 permet de bloquer l'aube 10 dans la direction radiale vers l'intérieur, et participe également au plaquage des portées du pied 12 contre l'extrémité énergie des dents 6. En outre, comme visible sur la figure 1, la cale 20 comprend une butée 22 de rétention axiale de son aube associée, cette butée 22 étant destinée à être en appui contre un anneau de rétention (non représenté) porté par le disque 2 et centré sur l'axe 4.As is best seen on the figure 2 the wedge 20 makes it possible to block the blade 10 in the radial direction towards the inside, and also contributes to the plating of the bearing surfaces of the foot 12 against the energy end of the teeth 6. In addition, as visible on FIG. figure 1 the wedge 20 comprises a stop 22 for axial retention of its associated blade, this stop 22 being intended to bear against a retention ring (not shown) carried by the disk 2 and centered on the axis 4.

La cale 20 présente classiquement une armature métallique 24 autour de laquelle est placé un ou plusieurs éléments extérieurs 26 en matériau élastomère, cet élément 26 se trouvant donc au contact du fond 8a de l'alvéole et de l'extrémité radialement interne du pied 12 de l'aube. De façon connue, chaque élément 26 est réalisé par surmoulage par injection sur l'armature métallique, qui est de préférence réalisée en titane. Le procédé de surmoulage mis en oeuvre est tel qu'il engendre une adhésion de l'élément extérieur 26 en matériau élastomère sur une surface de support prévue sur l'armature 24.The shim 20 conventionally has a metal frame 24 around which is placed one or more outer elements 26 made of elastomeric material, this element 26 being in contact with the bottom 8a of the cell and the radially inner end of the foot 12 of dawn. In known manner, each element 26 is made by injection molding on the metal reinforcement, which is preferably made of titanium. The overmoulding process used is such as to cause the outer element 26 of elastomeric material to adhere to a support surface provided on the reinforcement 24.

Bien que cette solution technologique soit très répandue sur les turboréacteurs, elle est susceptible de provoquer des problèmes de décollement de l'élément extérieur 26, également dénommé problème de délaminage. En effet, ce problème se pose essentiellement lorsque la cale 20 est introduite entre le pied 12 et le fond de l'alvéole 8a, durant le montage du moteur et/ou lors des opérations de manutention nécessitant une telle introduction de cale. Comme cela a été schématisé sur la figure 1, il est noté que l'introduction de la cale dans son espace dédié s'effectue en la faisant coulisser le long de sa direction longitudinale 30, généralement légèrement curviligne.Although this technological solution is widespread on turbojet engines, it is likely to cause separation problems. outer member 26, also referred to as a delamination problem. Indeed, this problem arises essentially when the wedge 20 is inserted between the foot 12 and the bottom of the cell 8a during engine assembly and / or during handling operations requiring such a wedge introduction. As has been schematized on the figure 1 it is noted that the introduction of the wedge into its dedicated space is made by sliding it along its longitudinal direction 30, generally slightly curvilinear.

Lorsqu'un tel arrachement se produit, les propriétés de rétention d'aube associées à cette cale peuvent ne plus être satisfaites. En outre, la cale disposant également d'une fonction de réduction des vibrations au sein de l'aube, sa détérioration conduit à baisser le niveau d'amortissement des vibrations subies par cette aube de soufflante en fonctionnement.When such tearing occurs, the blade retention properties associated with this wedge may no longer be satisfied. In addition, the wedge also having a vibration reduction function within the blade, its deterioration leads to lowering the vibration damping level experienced by the fan blade in operation.

FR-A-2841609 divulgue une cale présentant une armature métallique et ayant des parties évidées comblées par surmoulage avec un matériau élastomère. FR-A-2841609 discloses a shim having a metal frame and having recessed portions filled by overmolding with an elastomeric material.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

L'invention a donc pour but de remédier au moins partiellement aux inconvénients mentionnés ci-dessus relatifs aux réalisations de l'art antérieur.The invention therefore aims to at least partially overcome the disadvantages mentioned above relating to the achievements of the prior art.

Pour ce faire, l'invention a tout d'abord pour objet une cale selon la revendication 1 ou 2.To do this, the invention firstly relates to a shim according to claim 1 or 2.

Préférentiellement, la cale prend la forme d'une bande s'étendant selon une direction longitudinale, ladite zone ondulée présentant une pluralité de vagues se succédant cela cette même direction. Les vagues ainsi disposées permettent de résister encore mieux au délaminage de l'élément extérieur en matériau élastomère, lorsque la cale est introduite entre le pied d'aube et le fond d'alvéole. En effet, ces vagues constituent alors des obstacles directs au déplacement relatifs entre l'armature et l'élément extérieur de la cale, selon la direction longitudinale, qui correspond habituellement à la direction d'introduction de la cale dans son espace dédié sous l'aube.Preferably, the wedge takes the form of a band extending in a longitudinal direction, said corrugated zone having a plurality of waves succeeding one another in the same direction. The waves thus arranged make it possible to withstand the delamination of the outer element made of elastomer material even more effectively when the wedge is introduced between the blade root and the cell bottom. Indeed, these waves then constitute direct obstacles to the relative displacement between the frame and the outer element of the hold, in the longitudinal direction, which usually corresponds to the direction of introduction of the hold in its dedicated space under the dawn.

De préférence, l'élément extérieur en matériau élastomère est surmoulé sur l'armature métallique, préférentiellement par injection sous pression.Preferably, the outer element of elastomeric material is overmolded on the metal reinforcement, preferably by injection under pressure.

De préférence, l'armature métallique est réalisée en titane.Preferably, the metal reinforcement is made of titanium.

L'invention a également pour objet une soufflante de turboréacteur comprenant une pluralité d'aubes de soufflante ainsi qu'un disque définissant à sa périphérie une pluralité d'alvéoles, le pied de chaque aube de soufflante étant logé dans l'une des alvéoles, et une cale telle que décrite ci-dessus étant interposée entre le fond de l'alvéole et ledit pied.The invention also relates to a turbojet fan comprising a plurality of fan blades and a disk defining at its periphery a plurality of cells, the foot of each fan blade being housed in one of the cells, and a shim as described above being interposed between the bottom of the cell and said foot.

De préférence, chaque cale chemine le long du pied de son aube de soufflante associée.Preferably, each shim travels along the foot of its associated fan blade.

De préférence, chaque cale présente une butée de rétention axiale de son aube de soufflante associée.Preferably, each shim has an axial retention stop of its associated fan blade.

Enfin, l'invention a également pour objet un turboréacteur d'aéronef comprenant une soufflante telle que décrite ci-dessus.Finally, the invention also relates to an aircraft turbojet engine comprising a fan as described above.

D'autres avantages et caractéristiques de l'invention apparaîtront dans la description détaillée non limitative ci-dessous.Other advantages and features of the invention will become apparent in the detailed non-limiting description below.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

Cette description sera faite au regard des dessins annexés, parmi lesquels ;

  • la figure 1, déjà décrite, représente une vue éclatée en perspective d'une partie d'une soufflante de turboréacteur pour aéronef, de conception connue de l'art antérieur ;
  • La figure 2, également décrite précédemment, représente une vue partielle en section transversale de la soufflante montrée sur la figure 1 ;
  • La figure 3 représente une vue en perspective d'une cale pour soufflante de turboréacteur, selon un mode de réalisation préféré de la présente invention ;
  • la figure 4 représente une vue similaire à celle de la figure 3, sur laquelle l'élément extérieur en matériau élastomère a été retiré afin de montrer uniquement l'armature métallique et sa surface de support de l'élément extérieur ; et
  • la figure 4a représente une vue en coupe prise selon le plan P de la figure 4a, intégrant la direction longitudinale de la cale, et montrant les zones ondulées de la surface de support formée par l'armature métallique.
This description will be made with reference to the appended drawings, among which;
  • the figure 1 , already described, represents an exploded perspective view of a portion of an aircraft jet engine fan, known design of the prior art;
  • The figure 2 , also described above, represents a partial cross-sectional view of the blower shown in FIG. figure 1 ;
  • The figure 3 represents a perspective view of a turbojet fan shim, according to a preferred embodiment of the present invention;
  • the figure 4 represents a view similar to that of the figure 3 on which the outer elastomeric material member has been removed to show only the metal frame and its support surface of the outer member; and
  • the figure 4a represents a sectional view taken along the plane P of the figure 4a , integrating the longitudinal direction of the shim, and showing the corrugated areas of the support surface formed by the metal frame.

EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERSDETAILED PRESENTATION OF PARTICULAR EMBODIMENTS

En référence à la figure 3, on peut donc apercevoir une cale 120 selon un mode de réalisation préféré de la présente invention. Cette cale, dont la forme extérieure est sensiblement identique ou similaire à celle de la cale 20 de l'art antérieur décrite sur les figures 1 et 2, présente également une forme générale de bande s'étendant sur une direction longitudinale 130, de forme sensiblement curviligne, correspondant à la direction selon laquelle s'étend également le pied 12 de son aube associée ainsi que le fond d'alvéole 8a. Ainsi, il est à comprendre que la cale 120 est destinée à être introduite entre l'aube 10 et le fond 8a de l'alvéole 8 montrée sur la figure 1, toujours à des fins de rétention de l'aube ainsi que d'amortissement des vibrations subies par celle-ci.With reference to the figure 3 it is therefore possible to see a shim 120 according to a preferred embodiment of the present invention. This shim, whose outer shape is substantially identical or similar to that of the wedge 20 of the prior art described on figures 1 and 2 , also has a general shape of strip extending in a longitudinal direction 130, of substantially curvilinear shape, corresponding to the direction in which also extends the foot 12 of its associated blade and the cell bottom 8a. Thus, it should be understood that the shim 120 is intended to be introduced between the blade 10 and the bottom 8a of the cell 8 shown in FIG. figure 1 , always for the purpose of retention of the dawn as well as damping of the vibrations undergone by this one.

Sur la figure 3, on peut apercevoir que l'armature métallique 124, de préférence en titane, est équipée d'un élément extérieur en matériau élastomère référencé 126, qui recouvre partiellement la surface extérieure de cette armature. En d'autres termes, l'élément extérieur 126, réalisé par surmoulage par injection sous pression de matériau élastomère sur l'armature 124, laisse libre une partie de la surface extérieure de cette armature.On the figure 3 it can be seen that the metal armature 124, preferably of titanium, is equipped with an outer element of elastomeric material referenced 126, which partially covers the outer surface of this armature. In other words, the outer element 126, made by overmolding by pressure injection of elastomeric material on the armature 124, leaves free a portion of the outer surface of this armature.

Sur la figure 4, il est montré cette même armature 124 dans un état dans lequel elle n'est pas encore recouverte par son élément extérieur 126. Cela permet de faire apparaître la surface de support 134 de cet élément extérieur, qui, comme cela est visible sur les figures 4 et 4a, présente plusieurs zones ondulées 136. Chaque zone ondulée 136 est en fait formée à partir d'une succession de vagues 140 entre lesquelles se présentent des creux arrondis 142. Ainsi, lors du surmoulage par injection du matériau élastomère, ce dernier vient pénétrer dans les creux 142, ce qui a pour double conséquence d'augmenter la surface d'adhésion de l'élément 126 sur l'armature 124, et de créer une pluralité d'engagements mécaniques des vagues de l'armature dans les creux de l'élément extérieur, et inversement.On the figure 4 , it is shown this same armature 124 in a state in which it is not yet covered by its outer element 126. This makes it possible to reveal the support surface 134 of this external element, which, as is visible on the Figures 4 and 4a has a plurality of corrugated zones 136. Each corrugated zone 136 is in fact formed from a succession of waves 140 between which there are rounded depressions 142. Thus, during injection overmoulding of the elastomeric material, the latter comes into the 142, which has the dual effect of increasing the adhesion surface of the element 126 on the armature 124, and to create a plurality of mechanical engagement of the waves of the armature in the recesses of the outer element, and vice versa.

A cet égard, pour diminuer encore davantage les risques de délaminage de l'élément 126, il est prévu que les vagues 140 de chaque zone ondulée 136 se succèdent selon la direction longitudinale 130 dans laquelle la cale 120 est habituellement déplacée relativement par rapport au disque 2, de manière à être interposée entre le pied d'aube 12 et le fond d'alvéole 8a. Comme cela est montré sur la figure 4, il est ici prévu deux zones ondulées 136 orientées dans des directions opposées, l'une d'elle pouvant éventuellement être interrompue, à un ou plusieurs endroits, par une portion de l'armature 124 destinée à constituer une partie de la surface extérieure de la cale finie. Une fois la cale mise en place dans son alvéole, les vagues 140 s'étendent, dans le sens de leur amplitude, selon la direction circonférentielle du disque de soufflante 2.In this regard, to further reduce the risk of delamination of the element 126, it is expected that the waves 140 of each corrugated zone 136 follow one another in the longitudinal direction 130 in which the wedge 120 is usually moved relative to the disk 2, so as to be interposed between the blade root 12 and the cell bottom 8a. As shown on the figure 4 here two corrugated zones 136 oriented in opposite directions are provided, one of which may optionally be interrupted, in one or more places, by a portion of the armature 124 intended to constitute a part of the outer surface of the shim finished. Once the wedge has been placed in its cavity, the waves 140 extend in the direction of their amplitude in the circumferential direction of the fan disk 2.

En outre, les deux zones ondulées 136 sont reliées entre elles par une zone radialement externe 146 et une zone radialement interne (non visible sur la figure 4), ces deux zones étant préférentiellement planes et parallèles à la direction 130. De plus, elles font partie intégrante de la surface de support 134 sur laquelle l'élément en matériau élastomère 126 est destiné à adhérer, une fois le surmoulage par injection réalisé.In addition, the two corrugated zones 136 are interconnected by a radially outer zone 146 and a radially internal zone (not visible on the figure 4 ), these two areas being preferably flat and parallel to the direction 130. In addition, they are an integral part of the support surface 134 on which the element of elastomeric material 126 is intended to adhere, once the molding overmolding performed.

Bien entendu, la cale 120 présente ici également une butée 122 de rétention axiale de son aube de soufflante associée, présentant la même géométrie que la butée 22 montrée sur la cale 20 de la figure 1.Of course, the shim 120 here also has a stop 122 for axial retention of its associated fan blade, having the same geometry as the abutment 22 shown on the shim 20 of the figure 1 .

Claims (9)

  1. Shim (120) designed to be inserted between a root of fan blade (12) of a turbojet and a bottom (8a) of a compartment (8) in which this root is housed, the compartment being delimited by a fan disk (2), said shim having a metal stiffener (124) equipped with at least one external element (126) made of an elastomer material, said stiffener having a support surface (134) of said external element made of an elastomer material,
    characterised in that said support surface (134) comprises at least one corrugated zone (136).
  2. Shim according to claim 1, characterised in that said support surface (134) has two corrugated zones (136) oriented in opposite directions.
  3. Shim according to claim 1 or claim 2, characterised in that the shim is in the form of a strip extending along a longitudinal direction (130), and in that said corrugated zone comprises a plurality of waves (140) succeeding each other along said longitudinal direction (130).
  4. Shim according to any one of the previous claims, characterised in that said external element (126) is insert moulded onto the metal stiffener (124).
  5. Shim according to any one of the previous claims, characterised in that the metal stiffener (124) is made of titanium.
  6. Turbojet fan (1) comprising a plurality of fan blades (10) and a disk (2) defining a plurality of compartments (8) around its periphery, the root (12) of each fan blade (10) being housed in one of the compartments (8) and a shim (120) according to any one of the previous claims being inserted between the bottom (8a) of the compartment and said root (12).
  7. Fan according to claim 6, characterised in that each shim (120) travels along the root (12) of its associated fan blade (10).
  8. Fan according to claim 6 or claim 7, characterised in that each shim (120) has an axial retention stop (122) for its associated fan blade.
  9. Aircraft turbojet comprising a fan (1) according to any one of claims 6 to 8.
EP10718553.0A 2009-04-29 2010-04-28 Fan blade retainer with an elastomer Active EP2425100B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0952812A FR2945074B1 (en) 2009-04-29 2009-04-29 REINFORCED BLOW OF BREATHING BLADE
PCT/EP2010/055689 WO2010125089A1 (en) 2009-04-29 2010-04-28 Strengthened fan-blade block

Publications (2)

Publication Number Publication Date
EP2425100A1 EP2425100A1 (en) 2012-03-07
EP2425100B1 true EP2425100B1 (en) 2015-02-18

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EP10718553.0A Active EP2425100B1 (en) 2009-04-29 2010-04-28 Fan blade retainer with an elastomer

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US (1) US8870545B2 (en)
EP (1) EP2425100B1 (en)
JP (1) JP5699131B2 (en)
CN (1) CN102414397B (en)
BR (1) BRPI1013981B1 (en)
CA (1) CA2760290C (en)
FR (1) FR2945074B1 (en)
RU (1) RU2526607C2 (en)
WO (1) WO2010125089A1 (en)

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CA2760290C (en) 2017-03-07
JP5699131B2 (en) 2015-04-08
US8870545B2 (en) 2014-10-28
BRPI1013981A2 (en) 2016-04-05
WO2010125089A1 (en) 2010-11-04
CA2760290A1 (en) 2010-11-04
RU2526607C2 (en) 2014-08-27
CN102414397B (en) 2015-02-18
JP2012525530A (en) 2012-10-22
FR2945074A1 (en) 2010-11-05
EP2425100A1 (en) 2012-03-07
BRPI1013981B1 (en) 2020-06-23
US20120107125A1 (en) 2012-05-03
RU2011148428A (en) 2013-06-10
FR2945074B1 (en) 2011-06-03
CN102414397A (en) 2012-04-11

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