EP1764480A1 - Shim for a turbine engine blade - Google Patents

Shim for a turbine engine blade Download PDF

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Publication number
EP1764480A1
EP1764480A1 EP06120645A EP06120645A EP1764480A1 EP 1764480 A1 EP1764480 A1 EP 1764480A1 EP 06120645 A EP06120645 A EP 06120645A EP 06120645 A EP06120645 A EP 06120645A EP 1764480 A1 EP1764480 A1 EP 1764480A1
Authority
EP
European Patent Office
Prior art keywords
foil
connecting piece
tabs
blade
branches
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
EP06120645A
Other languages
German (de)
French (fr)
Other versions
EP1764480B1 (en
Inventor
Jean-Bernard Forgue
Jack-Pierre Lauvergnat
Thierry Nitre
Patrick Reghezza
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1764480A1 publication Critical patent/EP1764480A1/en
Application granted granted Critical
Publication of EP1764480B1 publication Critical patent/EP1764480B1/en
Active legal-status Critical Current
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Classifications

    • 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
    • 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 invention relates to a foil for turbomachine blade comprising two branches adapted to come wrap the sides of the foot of the blade.
  • the invention may relate to a foil for a turbojet fan blade.
  • the foil and the root of the blade are intended to be positioned inside a housing formed by an axial groove formed in the fan disk.
  • This housing is open upstream but delimited downstream by a wall.
  • This wall is formed by the upstream face of the drum of the low pressure compressor of the turbojet engine. It should be noted that this drum is generally of relatively low thickness at this point.
  • an axial direction is defined as being a direction parallel to the axis of rotation of the fan.
  • upstream and downstream of a part are defined with respect to the normal direction of flow of the gases inside the turbojet engine.
  • the invention aims to avoid this last problem by proposing a foil for turbomachine blade comprising two branches adapted to come wrap the flanks of the foot of the blade, and two legs extending respectively from one end of the two branches, these two tabs being folded towards each other, characterized in that said tabs are interconnected so as not to unfold.
  • said tabs are long enough to be folded over one another and be directly connected to each other.
  • they can be connected by welding, riveting, bolting or by interlocking into one another.
  • the foil comprises a connecting piece connecting said tabs so as to prevent them from unfolding.
  • This second embodiment makes it possible to produce shorter tabs and, generally, of less complex shape than those of the first embodiment.
  • the connecting piece used may have different shapes. Furthermore, the connecting piece can be fixed to the legs, that is to say be assembled with the legs so as to prevent relative movement between it and the legs or, conversely, be assembled with the legs with some relative freedom of movement.
  • the blade root can move inside the foil in directions other than the axial direction.
  • the connecting piece is assembled to the legs so as to allow the spacing of the branches of the foil (which amounts to allow the spacing of said legs) and therefore the "lateral" movements of the foot of dawn inside the foil.
  • the connecting piece may be a slide receiving said tabs inside its two ends.
  • the two tabs are assembled at the ends of the slideway so as to remain both free in translation in the direction of spacing of the branches of the foil, or one of these tabs is fixed to the slide, for example by welding, while the other remains free in translation.
  • FIGS. 1 to 3 show: a fan disc 2 having at its periphery numerous axial grooves 4 defining with the upstream face 8 of the low-pressure compressor drum 6 a housing 10 capable of receiving a shim 12, a foil 20 and the foot 16 of a blade 14. It will be noted that there are similar assemblies without wedge 12.
  • the foil 20 comprises two lateral branches 21A and 21B and is suitable for wrapping the blade root 16. As shown in FIG. 2, the foil 20 rests on the shim 12.
  • the blade root 16, the shim 12, the drum 6 and the fan disk 2 are made, for example, of titanium alloy.
  • the foil 20, meanwhile, is a wear part made of a harder alloy such as the alloy known under the brand Inconel 718, and has the function of limiting the wear of the blade root 16 and the disc of 2. Since the foil 20 is made of a material harder than that of the drum 6, repeated shocks between these two elements would damage the drum.
  • the foil 20 has two lugs 22 which extend from its upstream end, on each side of the blade root and which are folded towards each other. These tabs 22 are connected by a connecting piece 24 which prevents them from unfolding.
  • the upstream and downstream of the foil and the other parts are defined with respect to the normal flow direction of the gases inside the turbojet, represented by the arrow F in FIG.
  • the lugs 22 are fixed by welding, riveting, bolting, or any other suitable fastening means, at the ends of the connecting piece 24.
  • a welding spot 26 is made between each leg 22 and the part 24.
  • the connecting piece 24 is able to stretch in the direction of separation of the branches 21A and 21B, that is to say in a direction parallel to the transverse axis A shown in FIG.
  • the connecting piece 24 may be a flexible blade of which at least a portion is curved or bent.
  • the connecting piece 24 is a flexible blade having several folds 28 in its median part, so that the piece 24 is convex downstream, that is to say towards the When the branches 21A, 21B and their respective tabs 22 seek to deviate along the axis A, the curved portion of the piece 24 flattens out so that the piece 24 stretches and allows the blade to be extended. spacing branches 21A and 21B.
  • the piece 24 is curved towards the blade root 16 housed inside the foil 20, that is to say here downstream, helps cushion the shocks between the foil 20 and the foot dawn 16 because the curved portion 25 deforms (it flattens) when it abuts against the blade root 16.
  • the curved portion maintains the welds 26 and the tabs 22 away from the foot of the d dawn 16 and thus preserves these parts of the shocks.
  • the connecting piece 124 may be curved upstream.
  • the curved portion 125 does not come into contact with the blade root 16 (it has no damping function) but it still allows the piece 124 to stretch.
  • the curved portion 25, 125 may have folds and / or at least one curved portion.
  • the curved portion 125 is formed by a curved portion while in Figure 5 the curved portion 25 has five planar sides separated by four folds. Note that the more the curved portion 25 has folds, the more easily it deforms, which promotes the stretching of the piece 24 and the damping of the foil 22 on the blade root 16.
  • said connecting piece is a slide 224 receiving said tabs 22 within its two ends.
  • This slide 224 can be made, for example, by folding on itself a plate.
  • one of the tabs 22 is attached to one end of the part of the link 224 while the other leg 22 is assembled at the other end of the connecting piece 224 so as to remain free in translation in the direction of separation of the branches, that is to say parallel to the transverse axis A '.
  • Fixing at least one of the tabs 22 to the connecting piece 24 allows to have a single set to handle. In addition, it avoids any risk of detachment of the connecting part in operation.
  • the two legs 22 of the foil 20 overlap and are fixed to one another. They can be fastened together, for example, by a weld point 26.
  • a weld point 26 To allow the foil to stretch in the direction A "spacing branches 21A, 21B, at least one of said legs is a flexible blade of which a portion At least one is bent or folded
  • the two lugs 22 have a domed portion 325 facing downstream and formed by a curved portion, alternatively, this convex portion 325 could have folds.
  • the two lugs 22 of the foil 20 overlap and are nested so as to remain free in translation in the direction of separation of the branches.
  • one of the tabs 22 has two upper and lower wings 23 folded so as to form a slide inside which the other leg 22 can slide.
  • one of the tabs 22 has an oblong opening inside which slides a nipple. Either this stud is fixed on the other tab 22, or it also slides inside an oblong opening formed on this other tab 22.
  • turbojet fan blade foil examples have been described above. These foils could nonetheless be used for other types of turbomachine blades such as, for example, a turbojet low pressure compressor blade.
  • the part of the turbojet engine to be protected that is to say the drum of the low pressure compressor 6, is located downstream of the foil. Consequently, the tabs 22 extend from the upstream end of the foil 20.
  • the tabs 22 extend from the downstream end of the foil 20.

Abstract

The liner (20) for the root of a turbine blade (14), having two branches (21A, 21B) that cover the side of the root (16) and lugs (22) that fold over its edges, has the lugs joined by a connecting piece (24) to prevent them from unfolding and allowing the edges of the liner to move apart. The connecting piece can be in the form of a slideway that receives the ends of the two lugs, or a supple plate with at least one section that can be curved or folded.

Description

L'invention a pour objet un clinquant pour aube de turbomachine comprenant deux branches aptes à venir envelopper les flancs du pied de l'aube.The invention relates to a foil for turbomachine blade comprising two branches adapted to come wrap the sides of the foot of the blade.

Plus particulièrement, l'invention peut concerner un clinquant pour aube de soufflante de turboréacteur. Le clinquant et le pied de l'aube sont destinés à être positionnés à l'intérieur d'un logement formé par une rainure axiale ménagée dans le disque de soufflante. Ce logement est ouvert en amont mais délimité en aval par une paroi. Cette paroi est formée par la face amont du tambour du compresseur basse pression du turboréacteur. On notera que ce tambour est généralement d'épaisseur relativement faible à cet endroit.More particularly, the invention may relate to a foil for a turbojet fan blade. The foil and the root of the blade are intended to be positioned inside a housing formed by an axial groove formed in the fan disk. This housing is open upstream but delimited downstream by a wall. This wall is formed by the upstream face of the drum of the low pressure compressor of the turbojet engine. It should be noted that this drum is generally of relatively low thickness at this point.

Dans la présente demande, une direction axiale est définie comme étant une direction parallèle à l'axe de rotation de la soufflante. En outre, l'amont et l'aval d'une pièce sont définis par rapport au sens normal d'écoulement des gaz à l'intérieur du turboréacteur.In the present application, an axial direction is defined as being a direction parallel to the axis of rotation of the fan. In addition, upstream and downstream of a part are defined with respect to the normal direction of flow of the gases inside the turbojet engine.

On rencontre avec les clinquants classiques l'inconvénient suivant : lors de la rotation de la soufflante, le clinquant se déplace suivant un mouvement axial de va et vient à l'intérieur de son logement et percute répétitivement le tambour du compresseur basse pression. Les percussions répétées du clinquant contre le tambour endommagent ce dernier et diminuent sa durée de vie. On constate généralement la formation sur le tambour, d'une empreinte qui constitue une zone de départ de fissure. Ce phénomène est d'autant plus gênant que le tambour est une pièce relativement coûteuse.The following disadvantage is encountered with conventional foils: during the rotation of the fan, the foil moves in an axial movement back and forth inside its housing and repeatedly hits the drum of the low pressure compressor. Repeated percussion of the foil against the drum damages the drum and reduces its life. The formation on the drum is generally noted, of an imprint which constitutes a starting zone of crack. This phenomenon is all the more troublesome as the drum is a relatively expensive piece.

Pour éviter un tel inconvénient, il est connu de prévoir sur le clinquant deux pattes s'étendant respectivement à partir de l'extrémité amont des branches de celui-ci, ces pattes étant repliées l'une vers l'autre. Ces pattes viennent en butée contre la face avant du pied d'aube lorsque le clinquant se déplace vers l'aval. Elles retiennent ainsi le clinquant avant qu'il ne vienne percuter le tambour.To avoid such a disadvantage, it is known to provide on the foil two tabs respectively extending from the upstream end of the branches thereof, these lugs being folded towards one another. These tabs abut against the front face of the blade root when the foil moves downstream. They thus retain the foil before it hits the drum.

Toutefois, ces pattes ont tendance à se déplier sous l'effet des forces de poussée qu'exerce sur elles le pied d'aube. Une fois dépliées, ces pattes ne jouent plus leur rôle de butée, de sorte que le clinquant n'est plus retenu et percute le tambour.However, these legs tend to unfold under the effect of thrust forces exerted on them the blade root. Once unfolded, these tabs do not play their role of abutment, so that the foil is no longer held and hit the drum.

L'invention vise à éviter ce dernier problème en proposant un clinquant pour aube de turbomachine comprenant deux branches aptes à venir envelopper les flancs du pied de l'aube, et deux pattes s'étendant respectivement à partir d'une extrémité des deux branches, ces deux pattes étant repliées l'une vers l'autre, caractérisé en ce lesdites pattes sont reliées entre elles de manière à ne pas pouvoir se déplier.The invention aims to avoid this last problem by proposing a foil for turbomachine blade comprising two branches adapted to come wrap the flanks of the foot of the blade, and two legs extending respectively from one end of the two branches, these two tabs being folded towards each other, characterized in that said tabs are interconnected so as not to unfold.

Selon un premier mode de réalisation, lesdites pattes sont suffisamment longues pour être repliées l'une sur l'autre et être reliées directement entre elles. Par exemple, elles peuvent être reliées par soudage, rivetage, boulonnage ou encore par emboîtement l'une dans l'autre.According to a first embodiment, said tabs are long enough to be folded over one another and be directly connected to each other. For example, they can be connected by welding, riveting, bolting or by interlocking into one another.

Selon un deuxième mode de réalisation le clinquant comprend une pièce de liaison reliant lesdites pattes de manière à les empêcher de se déplier. Ce deuxième mode de réalisation permet de réaliser des pattes plus courtes et, généralement, de forme moins complexe que celles du premier mode de réalisation.According to a second embodiment, the foil comprises a connecting piece connecting said tabs so as to prevent them from unfolding. This second embodiment makes it possible to produce shorter tabs and, generally, of less complex shape than those of the first embodiment.

La pièce de liaison utilisée peut avoir différentes formes. Par ailleurs, la pièce de liaison peut être fixée aux pattes, c'est-à-dire être assemblée avec les pattes de manière à empêcher tout mouvement relatif entre elle et les pattes ou, au contraire, être assemblée avec les pattes avec une certaine liberté de mouvement relatif.The connecting piece used may have different shapes. Furthermore, the connecting piece can be fixed to the legs, that is to say be assembled with the legs so as to prevent relative movement between it and the legs or, conversely, be assembled with the legs with some relative freedom of movement.

On a pu constater lors des recherches ayant conduit à l'invention que pour limiter l'usure du disque de soufflante et/ou du pied d'aube, il était préférable que le pied d'aube puisse se mouvoir à l'intérieur du clinquant dans des directions autres que la direction axiale.It has been found during research that led to the invention that to limit the wear of the fan disk and / or the blade root, it was preferable that the blade root can move inside the foil in directions other than the axial direction.

Ainsi, selon un mode de réalisation avantageux, la pièce de liaison est assemblée aux pattes de manière à autoriser l'écartement des branches du clinquant (ce qui revient à autoriser l'écartement desdites pattes) et donc les mouvements "latéraux" du pied d'aube à l'intérieur du clinquant.Thus, according to an advantageous embodiment, the connecting piece is assembled to the legs so as to allow the spacing of the branches of the foil (which amounts to allow the spacing of said legs) and therefore the "lateral" movements of the foot of dawn inside the foil.

Ainsi, à titre d'exemple, la pièce de liaison peut être une glissière recevant lesdites pattes à l'intérieur de ses deux extrémités.Thus, for example, the connecting piece may be a slide receiving said tabs inside its two ends.

Pour autoriser l'écartement desdites pattes, soit les deux pattes sont assemblées aux extrémités de la glissière de manière à rester toutes deux libres en translation suivant la direction d'écartement des branches du clinquant, soit l'une de ces pattes est fixée à la glissière, par exemple par soudage, tandis que l'autre reste libre en translation.To allow the spacing of said tabs, the two tabs are assembled at the ends of the slideway so as to remain both free in translation in the direction of spacing of the branches of the foil, or one of these tabs is fixed to the slide, for example by welding, while the other remains free in translation.

L'invention et ses avantages seront mieux compris à la lecture de la description qui suit. Cette description fait référence aux figures annexées sur lesquelles :

  • la figure 1 représente de manière schématique un ensemble non assemblé comprenant une partie de disque de soufflante, une cale, un exemple de clinquant selon l'invention, et un pied d'aube de soufflante ;
  • la figure 2 est une vue de face selon la flèche II de l'ensemble de la figure 1, une fois celui-ci assemblé ;
  • la figure 3 est une coupe axiale selon III-III de l'ensemble de la figure 2 ;
  • la figure 4 est une vue de détail en perspective, selon la flèche IV, de la pièce de liaison du clinquant des figures 1 à 3 ;
  • la figure 5 est une coupe selon le plan V-V, de la pièce de liaison de la figure 4 ;
  • la figure 6 est une coupe analogue à celle de la figure 5 montrant un autre type de pièce de liaison ;
  • la figure 7 est une vue de détail en perspective montrant un exemple de clinquant selon l'invention équipé d'un autre type de pièce de liaison;
  • la figure 8 est une vue de détail en perspective montrant un exemple de clinquant selon l'invention dépourvu de pièce de liaison; et
  • la figure 9 est une vue de détail en perspective montrant un autre exemple de clinquant selon l'invention dépourvu de pièce de liaison.
The invention and its advantages will be better understood on reading the description which follows. This description refers to the appended figures in which:
  • Figure 1 schematically shows a non-assembled assembly comprising a portion of a fan disk, a shim, an example foil according to the invention, and a fan blade root;
  • Figure 2 is a front view along the arrow II of the assembly of Figure 1, once it assembled;
  • Figure 3 is an axial section along III-III of the assembly of Figure 2;
  • Figure 4 is a detail view in perspective, according to the arrow IV, the connecting part of the foil of Figures 1 to 3;
  • Figure 5 is a section along the plane VV of the connecting piece of Figure 4;
  • Figure 6 is a section similar to that of Figure 5 showing another type of connecting piece;
  • Figure 7 is a detail view in perspective showing an example of foil according to the invention equipped with another type of connecting piece;
  • Figure 8 is a detail view in perspective showing an example of foil according to the invention without connecting piece; and
  • Figure 9 is a detail view in perspective showing another example of foil according to the invention without connecting piece.

Sur les figures 1 à 3, sont représentés : un disque de soufflante 2 présentant à sa périphérie de nombreuses rainures axiales 4 définissant avec la face amont 8 du tambour de compresseur basse pression 6 un logement 10 susceptible de recevoir une cale 12, un clinquant 20 et le pied 16 d'une aube 14. On notera qu'il existe des montages analogues dépourvus de cale 12.FIGS. 1 to 3 show: a fan disc 2 having at its periphery numerous axial grooves 4 defining with the upstream face 8 of the low-pressure compressor drum 6 a housing 10 capable of receiving a shim 12, a foil 20 and the foot 16 of a blade 14. It will be noted that there are similar assemblies without wedge 12.

Le clinquant 20 comprend deux branches latérales 21A et 21B et est apte à envelopper le pied d'aube 16. Comme représenté sur la figure 2, le clinquant 20 repose sur la cale 12. Le pied d'aube 16, la cale 12, le tambour 6 et le disque de soufflante 2 sont réalisés, par exemple, en alliage de titane. Le clinquant 20, quant à lui, est une pièce d'usure réalisée en un alliage plus dur comme l'alliage connu sous la marque Inconel 718, et a pour fonction de limiter l'usure du pied d'aube 16 et du disque de soufflante 2. Le clinquant 20 étant en un matériau plus dur que celui du tambour 6, des chocs répétés entre ces deux éléments endommageraient le tambour.The foil 20 comprises two lateral branches 21A and 21B and is suitable for wrapping the blade root 16. As shown in FIG. 2, the foil 20 rests on the shim 12. The blade root 16, the shim 12, the drum 6 and the fan disk 2 are made, for example, of titanium alloy. The foil 20, meanwhile, is a wear part made of a harder alloy such as the alloy known under the brand Inconel 718, and has the function of limiting the wear of the blade root 16 and the disc of 2. Since the foil 20 is made of a material harder than that of the drum 6, repeated shocks between these two elements would damage the drum.

Pour éviter de tels chocs, le clinquant 20 présente deux pattes 22 qui s'étendent à partir de son extrémité amont, de chaque côté du pied d'aube et qui sont repliées l'une vers l'autre. Ces pattes 22 sont reliées par une pièce de liaison 24 qui les empêche de se déplier. L'amont et l'aval du clinquant et des autres pièces sont définis par rapport au sens d'écoulement normal des gaz à l'intérieur du turboréacteur, représenté par la flèche F sur la figure 3.To avoid such shocks, the foil 20 has two lugs 22 which extend from its upstream end, on each side of the blade root and which are folded towards each other. These tabs 22 are connected by a connecting piece 24 which prevents them from unfolding. The upstream and downstream of the foil and the other parts are defined with respect to the normal flow direction of the gases inside the turbojet, represented by the arrow F in FIG.

Selon un mode de réalisation, les pattes 22 sont fixées par soudage, rivetage, boulonnage, ou tout autre moyen de fixation approprié, aux extrémités de la pièce de liaison 24. Dans l'exemple des figures 4 et 5, un point de soudure 26 est réalisé entre chaque patte 22 et la pièce 24. Par ailleurs, la pièce de liaison 24 est apte à s'étirer suivant la direction d'écartement des branches 21A et 21B, c'est-à-dire suivant une direction parallèle à l'axe transversal A représenté sur la figure 4.According to one embodiment, the lugs 22 are fixed by welding, riveting, bolting, or any other suitable fastening means, at the ends of the connecting piece 24. In the example of FIGS. 4 and 5, a welding spot 26 is made between each leg 22 and the part 24. Furthermore, the connecting piece 24 is able to stretch in the direction of separation of the branches 21A and 21B, that is to say in a direction parallel to the transverse axis A shown in FIG.

Pour permettre cet étirement, la pièce de liaison 24 peut être une lame souple dont une partie au moins est courbée ou pliée. Dans l'exemple des figures 4 et 5, la pièce de liaison 24 est une lame souple présentant plusieurs plis 28 dans sa partie médiane, de sorte que la pièce 24 est bombée vers l'aval, c'est-à-dire vers le pied d'aube 16. Lorsque les branches 21A, 21B et leurs pattes respectives 22 cherchent à s'écarter suivant l'axe A, la partie bombée de la pièce 24 s'aplatit de sorte que la pièce 24 s'étire et permet l'écartement des branches 21A et 21B.To allow this stretching, the connecting piece 24 may be a flexible blade of which at least a portion is curved or bent. In the example of FIGS. 4 and 5, the connecting piece 24 is a flexible blade having several folds 28 in its median part, so that the piece 24 is convex downstream, that is to say towards the When the branches 21A, 21B and their respective tabs 22 seek to deviate along the axis A, the curved portion of the piece 24 flattens out so that the piece 24 stretches and allows the blade to be extended. spacing branches 21A and 21B.

Le fait que la pièce 24 soit bombée vers le pied d'aube 16 logé à l'intérieur du clinquant 20, c'est-à-dire ici vers l'aval, permet d'amortir les chocs entre le clinquant 20 et le pied d'aube 16 car la partie bombée 25 se déforme (elle s'aplatit) lorsqu'elle vient en butée contre le pied d'aube 16. En outre, la partie bombée maintient les soudures 26 et les pattes 22 à distance du pied d'aube 16 et préserve donc ces parties des chocs.The fact that the piece 24 is curved towards the blade root 16 housed inside the foil 20, that is to say here downstream, helps cushion the shocks between the foil 20 and the foot dawn 16 because the curved portion 25 deforms (it flattens) when it abuts against the blade root 16. In addition, the curved portion maintains the welds 26 and the tabs 22 away from the foot of the d dawn 16 and thus preserves these parts of the shocks.

Selon un autre exemple représenté sur la figure 6, la pièce de liaison 124 peut être bombée vers l'amont. Dans ce cas, la partie bombée 125 n'entre pas au contact du pied d'aube 16 (elle n'a pas de fonction d'amortissement) mais elle permet toujours à la pièce 124 de s'étirer.According to another example shown in Figure 6, the connecting piece 124 may be curved upstream. In this case, the curved portion 125 does not come into contact with the blade root 16 (it has no damping function) but it still allows the piece 124 to stretch.

Concernant la section de la partie bombée 25, 125, celle-ci peut présenter des plis et/ou au moins une portion courbe. Sur la figure 6, la partie bombée 125 est formée par une portion courbe tandis que sur la figure 5 la partie bombée 25 présente cinq côtés plans séparés par quatre plis. On notera que plus la partie bombée 25 présente de plis, plus elle se déforme facilement, ce qui favorise l'étirement de la pièce 24 et l'amortissement du clinquant 22 sur le pied d'aube 16.Concerning the section of the curved portion 25, 125, it may have folds and / or at least one curved portion. In Figure 6, the curved portion 125 is formed by a curved portion while in Figure 5 the curved portion 25 has five planar sides separated by four folds. Note that the more the curved portion 25 has folds, the more easily it deforms, which promotes the stretching of the piece 24 and the damping of the foil 22 on the blade root 16.

Selon un autre mode de réalisation, représenté sur la figure 7, ladite pièce de liaison est une glissière 224 recevant lesdites pattes 22 à l'intérieur de ses deux extrémités. Cette glissière 224 peut être réalisée, par exemple, en repliant sur elle-même une plaque. Dans l'exemple de la figure 7, l'une des pattes 22 est fixée à l'une des extrémités de la pièce de la liaison 224 tandis que l'autre patte 22 est assemblée à l'autre extrémité de la pièce de liaison 224 de manière à rester libre en translation suivant la direction d'écartement des branches, c'est-à-dire parallèlement à l'axe transversal A'.In another embodiment, shown in Figure 7, said connecting piece is a slide 224 receiving said tabs 22 within its two ends. This slide 224 can be made, for example, by folding on itself a plate. In the example of Figure 7, one of the tabs 22 is attached to one end of the part of the link 224 while the other leg 22 is assembled at the other end of the connecting piece 224 so as to remain free in translation in the direction of separation of the branches, that is to say parallel to the transverse axis A '.

Pour faciliter l'insertion de la patte 22 libre en translation, à l'intérieur de la glissière 224, l'extrémité correspondante de cette glissière est biseautée.To facilitate the insertion of the free tab 22 in translation, inside the slide 224, the corresponding end of this slide is tapered.

Le fait de fixer au moins une des pattes 22 à la pièce de liaison 24 permet d'avoir un unique ensemble à manipuler. De plus, on évite tout risque de détachement de la pièce de liaison en fonctionnement.Fixing at least one of the tabs 22 to the connecting piece 24 allows to have a single set to handle. In addition, it avoids any risk of detachment of the connecting part in operation.

En référence aux figures 8 et 9, nous allons maintenant décrire deux exemples de clinquants dépourvus de pièce de liaison.Referring to Figures 8 and 9, we will now describe two examples of foils without connecting part.

Dans l'exemple de la figure 8, les deux pattes 22 du clinquant 20 se recouvrent et sont fixées l'une à l'autre. Elles peuvent être fixées ensemble, par exemple, par un point de soudure 26. Pour permettre au clinquant de s'étirer suivant la direction A" d'écartement des branches 21A, 21B, au moins une desdites pattes est une lame souple dont une partie au moins est courbée ou pliée. Dans l'exemple, pour ne pas créer de déséquilibre, les deux pattes 22 présentent une partie bombée 325 tournée vers l'aval et formée par une portion courbe. Alternativement, cette partie bombée 325 pourrait présenter des plis et/ou être tournée vers l'amont. Le fait que la partie bombée 325 soit tournée vers l'intérieur du cliquant 20, c'est-à-dire vers le pied d'aube 16, permet d'amortir les chocs entre le clinquant 20 et le pied d'aube 16 car la partie bombée 325 se déforme lorsqu'elle vient en butée contre le pied d'aube 16.In the example of Figure 8, the two legs 22 of the foil 20 overlap and are fixed to one another. They can be fastened together, for example, by a weld point 26. To allow the foil to stretch in the direction A "spacing branches 21A, 21B, at least one of said legs is a flexible blade of which a portion At least one is bent or folded In the example, in order not to create an imbalance, the two lugs 22 have a domed portion 325 facing downstream and formed by a curved portion, alternatively, this convex portion 325 could have folds. and / or be turned upstream.The fact that the convex portion 325 is turned towards the inside of the click 20, that is to say towards the blade root 16, makes it possible to dampen the shocks between the foil 20 and the blade root 16 because the convex portion 325 deforms when it abuts against the blade root 16.

Dans l'exemple de la figure 9, les deux pattes 22 du clinquant 20 se recouvrent et sont emboîtées de manière à rester libre en translation suivant la direction d'écartement des branches. Dans cet exemple, l'une des pattes 22 présente deux ailes 23 supérieure et inférieure repliées de manière à former une glissière à l'intérieur de laquelle l'autre patte 22 peut coulisser.In the example of Figure 9, the two lugs 22 of the foil 20 overlap and are nested so as to remain free in translation in the direction of separation of the branches. In this example, one of the tabs 22 has two upper and lower wings 23 folded so as to form a slide inside which the other leg 22 can slide.

Selon un autre exemple, non représenté, l'une des pattes 22 présente une ouverture oblongue à l'intérieur de laquelle coulisse un téton. Soit ce téton est fixé sur l'autre patte 22, soit il coulisse également à l'intérieur d'une ouverture oblongue ménagée sur cette autre patte 22.According to another example, not shown, one of the tabs 22 has an oblong opening inside which slides a nipple. Either this stud is fixed on the other tab 22, or it also slides inside an oblong opening formed on this other tab 22.

On a décrit ci-dessus des exemples de clinquant pour aubes de soufflante de turboréacteur. Ces clinquants pourraient néanmoins être utilisés pour d'autres types d'aube de turbomachine comme, par exemple, une aube de compresseur basse pression de turboréacteur.Examples of turbojet fan blade foil have been described above. These foils could nonetheless be used for other types of turbomachine blades such as, for example, a turbojet low pressure compressor blade.

Par ailleurs, dans ces exemples, la partie du turboréacteur à protéger, c'est-à-dire le tambour du compresseur basse pression 6, est située en aval du clinquant. Par conséquent, les pattes 22 s'étendent à partir de l'extrémité amont du clinquant 20. On pourrait toutefois imaginer des cas où la partie du turboréacteur à protéger serait en amont du clinquant. Dans ce cas, les pattes 22 s'étendraient à partir de l'extrémité aval du clinquant 20.Furthermore, in these examples, the part of the turbojet engine to be protected, that is to say the drum of the low pressure compressor 6, is located downstream of the foil. Consequently, the tabs 22 extend from the upstream end of the foil 20. However, one could imagine cases where the part of the turbojet to be protected is upstream of the foil. In this case, the tabs 22 extend from the downstream end of the foil 20.

Claims (12)

Clinquant (20) pour aube (14) de turbomachine comprenant deux branches (21A, 21B) aptes à venir envelopper les flancs du pied (16) de l'aube, et deux pattes (22) s'étendant respectivement à partir d'une extrémité des deux branches, caractérisé en ce que ces deux pattes sont reliées entre elles de manière à ne pas pouvoir se déplier.Blade (20) for blade (14) turbomachine comprising two branches (21A, 21B) adapted to wrap the flanks of the foot (16) of the blade, and two tabs (22) extending respectively from a end of the two branches, characterized in that these two tabs are interconnected so as not to unfold. Clinquant pour aube de turbomachine selon la revendication 1, caractérisé en ce qu'il comprend une pièce de liaison (24, 124, 224) reliant lesdites pattes de manière à les empêcher de se déplier.A turbomachine blade foil according to claim 1, characterized in that it comprises a connecting piece (24, 124, 224) connecting said tabs so as to prevent them from unfolding. Clinquant selon la revendication 2, caractérisé en ce que ladite pièce de liaison (24, 124, 224) est assemblée auxdites pattes (22) de manière à autoriser l'écartement des branches (21A, 21B) du clinquant.A foil according to claim 2, characterized in that said connecting piece (24, 124, 224) is assembled to said lugs (22) so as to allow the spacing of the branches (21A, 21B) of the foil. Clinquant selon la revendication 2 ou 3, caractérisé en ce que ladite pièce de liaison (224) est une glissière recevant lesdites pattes (22) à l'intérieur de ses deux extrémités.A foil according to claim 2 or 3, characterized in that said connecting piece (224) is a slide receiving said tabs (22) inside its two ends. Clinquant selon l'une quelconque des revendications 2 à 4, caractérisé en ce que l'une desdites pattes (22) est fixée à l'une des extrémités de la pièce de liaison (224) tandis que l'autre patte (22) est assemblée à l'autre extrémité de la pièce de liaison (224) de manière à rester libre en translation suivant la direction d'écartement des branches (21A, 21B).A foil according to any of claims 2 to 4, characterized in that one of said lugs (22) is attached to one end of the connecting piece (224) while the other lug (22) is assembled at the other end of the connecting piece (224) so as to remain free in translation in the direction of separation of the branches (21A, 21B). Clinquant selon la revendication 2 ou 3, caractérisé en ce que les deux pattes (22) sont fixées aux extrémités de la pièce de liaison (24, 124) et en ce que ladite pièce de liaison est apte à s'étirer suivant la direction d'écartement des branches (21A, 21B).A foil according to claim 2 or 3, characterized in that the two lugs (22) are attached to the ends of the connecting piece (24, 124) and in that said connecting piece is able to stretch in the direction of spacing of the branches (21A, 21B). Clinquant selon l'une quelconque des revendications 2, 3 et 6, caractérisé en ce que ladite pièce de liaison (24, 124) est une lame souple dont au moins une partie (25, 125) est courbée ou pliée.A foil according to any one of claims 2, 3 and 6, characterized in that said connecting piece (24, 124) is a flexible blade of which at least a portion (25, 125) is curved or folded. Clinquant selon la revendication 1, caractérisé en ce lesdites pattes (22) se recouvrent et sont fixées l'une à l'autre et en ce qu'au moins une desdites pattes (22) est une lame souple dont au moins une partie (325) est courbée ou pliée.A foil according to claim 1, characterized in that said tabs (22) overlap and are fixed to each other and in that at least one of said tabs (22) is a flexible blade of which at least a portion (325 ) is curved or folded. Clinquant selon la revendication 1, caractérisé en ce que lesdites pattes (22) sont emboîtées de manière à rester libres en translation suivant la direction d'écartement des branches (21A, 21B).A foil according to claim 1, characterized in that said lugs (22) are nested so as to remain free in translation in the direction of separation of the branches (21A, 21B). Clinquant selon la revendication 7 ou 8, caractérisé en ce que ladite partie courbée ou pliée (25, 125, 325) de ladite pièce de liaison (24, 124) ou de ladite patte (22), est bombée vers l'intérieur du cliquant (20).A foil according to claim 7 or 8, characterized in that said curved or folded portion (25, 125, 325) of said connecting piece (24, 124) or said tab (22) is curved towards the inside of the clicking (20). Aube (14) de soufflante dont le pied (16) est enveloppé par un clinquant (20) selon l'une quelconque des revendications 1 à 10.Fan blade (14) whose foot (16) is surrounded by a foil (20) according to any one of claims 1 to 10. Turboréacteur caractérisé en ce qu'il comprend une aube (14) de soufflante dont le pied (16) est enveloppé par un clinquant (20) selon l'une quelconque des revendications 1 à 10.Turbojet characterized in that it comprises a fan blade (14) whose foot (16) is enveloped by a foil (20) according to any one of claims 1 to 10.
EP06120645A 2005-09-15 2006-09-14 Shim for a turbine engine blade Active EP1764480B1 (en)

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FR0509420A FR2890684B1 (en) 2005-09-15 2005-09-15 CLINKING FOR TURBOREACTOR BLADE

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JP5068049B2 (en) 2012-11-07
CN1932251B (en) 2010-09-29
ES2317437T3 (en) 2009-04-16
RU2413072C2 (en) 2011-02-27
FR2890684A1 (en) 2007-03-16
US7938626B2 (en) 2011-05-10
CA2558759C (en) 2013-03-05
CN1932251A (en) 2007-03-21
DE602006003493D1 (en) 2008-12-18
US20100226777A1 (en) 2010-09-09
CA2558759A1 (en) 2007-03-15
JP2007077993A (en) 2007-03-29
FR2890684B1 (en) 2007-12-07
RU2006133128A (en) 2008-03-20
EP1764480B1 (en) 2008-11-05

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