EP0669451A1 - Seal between the blades and the intermediate platforms - Google Patents

Seal between the blades and the intermediate platforms Download PDF

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Publication number
EP0669451A1
EP0669451A1 EP95400353A EP95400353A EP0669451A1 EP 0669451 A1 EP0669451 A1 EP 0669451A1 EP 95400353 A EP95400353 A EP 95400353A EP 95400353 A EP95400353 A EP 95400353A EP 0669451 A1 EP0669451 A1 EP 0669451A1
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EP
European Patent Office
Prior art keywords
blades
platforms
envelope
vanes
face
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
EP95400353A
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German (de)
French (fr)
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EP0669451B1 (en
Inventor
Jean-Pierre Louis Mareix
Philippe Jean-Pierre Pabion
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0669451A1 publication Critical patent/EP0669451A1/en
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Publication of EP0669451B1 publication Critical patent/EP0669451B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms

Definitions

  • the invention relates to a seal arranged in an assembly of blades on a fan disk and intermediate platforms, thus forming a rotor.
  • a common design is to produce the platform segments of a block with the vanes. It has been exposed in numerous patents and has the advantage that the platform segments join halfway between the blades by straight junctions which it is easy to fill with a gasket. The disadvantage is that the platforms, whose extension is substantially perpendicular to that of the blades, complicate their production.
  • the invention thus applies to constructions where the platforms are produced as separate parts of the blades and each extend between a pair of blades, forming a clearance with each of them, which unfortunately implies that the games are important along the blades because of the complexity of the shape thereof and in particular of their curvature and the need to dismantle the platforms.
  • the platforms are held in position between the blades by two ferrules, one located upstream of the rotor, the other downstream.
  • the invention can also be applied to a rotor, the platforms of which have a foot which is housed in cells machined in the disc.
  • the invention relates to a seal which can be placed in each of these sets and which fills them correctly. More specifically, it relates to an assembly for a rotor, composed of vanes embedded in the rotor and of platforms located between pairs of consecutive vanes, substantially longitudinal clearances remaining between the vanes and the platforms, and this assembly is characterized in that it comprises seals occupying the games and formed of an envelope composed of a face bearing against the sides of the platforms and a flexible face directed towards the surfaces of the blades.
  • the envelope may, in an equivalent manner, be composed of a face bearing against the surfaces of the blades and of a flexible face directed towards the sides of the platforms.
  • the linings are also formed of a solid elongated piece in the envelope, which can be sectored or composed of a plurality of elements.
  • FIG. 1 essentially represents a turbomachine provided as usual with several stages of compressors, turbines, etc., and which opens, on the left in the figure, by an inlet fan S composed of a rotor disk 8 carrying a circular stage of radial vanes 1 which separate platforms 2 delimiting a flow stream.
  • FIG. 3 We now deal with FIG. 3.
  • the cores 4 have external flanks 6 oriented towards the blades 1 and which widen in the radial direction towards the outside.
  • the clearance 7, determined by the mounting method, with the blades 1 is only a few millimeters.
  • the platform parts 2 are made of composite material, which significantly lightens the rotor. We see in Figure 2 that they extend over all the length of the disc 8, and protrude from both sides by an upstream appendage 10 and a downstream appendage 11. An upstream ferrule 12 and a downstream ferrule 13 attached to the lateral faces of the disc 8 and fixed to these faces according to known arrangements respectively cover the appendages 10 and 11 of the platform parts 2 and thus retain these parts against the axial and radial movements. In this embodiment, the platform pieces 2 are held by the ferrules 12 and 13 a few tenths of a millimeter from the surface of the disc 8.
  • the seals which occupy the sets 7 have the general reference 15 in FIG. 3.
  • Each consists of an envelope 16 formed of an internal face 17, an external face 18 and a radially internal heel 19 .
  • the section of the envelope 16 is therefore triangular as shown, at the time of the insertion of the platform parts 2.
  • a long, baguette-shaped part 20 is engaged in the envelope 16 and occupies part of the volume it encompasses.
  • the rod 20 is not necessarily flexible and can be formed from metal or composite material, but whose mass is sufficient for it to move in the envelope 16 under the action of centrifugal forces created during operation.
  • the casing 16 is made of elastomer, its outer face 18 and the heel 19 have the ability to deform, and the rod 20 has the freedom to slide in the casing 16 towards outside to get closer to the place of game 7 and fill it.
  • the rod 20 is advantageously cylindrical with all its sections to facilitate its sliding.
  • the envelope 16 then takes the form of a triangle, the point of which is inwards in the radial direction instead of being outwards.
  • the internal face 17 remains for its part glued to the corresponding flank 6.
  • FIG. 4 illustrates this embodiment of the invention in centripetal view.
  • Each platform piece 2 carries two similar seals 15, even if the respective clearances 7a and 7b which separate the edge of the platform piece 2 from the blades 1 between which it is located may be different: the flexibility of the casing 16 makes it possible to fill wide as well as narrow clearances 7.
  • the sides 6 of the platform parts 2 are substantially parallel to the sides of the blades 1 in front of which they extend, and that the seals 15 are similarly curved.
  • the games 7 are thus filled over their entire length by a substantially uniform movement of translation of the rods 20.
  • FIG. 6 illustrates an embodiment in which the platform parts 2 have, like the blades 1, a foot 5 engaged in a cell of the disc 8 produced by a broaching.
  • the ferrules 12 and 13 can then be omitted.
  • FIG. 7 illustrates another embodiment of the invention, in which the internal face, here 17 ′, of the envelope 16 ′ of the seals 15 is glued to the flank of the blade 1, and the external face 18 ′ and the heel 19 ′ are directed towards the flank 6 of the platform 2. It can be seen that the operation is the same because the centrifugal forces move the rod 20 towards the narrow portion of the game and therefore fill it.

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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)

Abstract

The rotor assembly is composed of radial blades (1) encastred in the rotor disc (8). Composite material platforms (2) composed of a central beam (3) and cores (4) on either side are held in place between consecutive blade pairs. The cores have two external flanks (6) directed towards the blades which widen out radially. Substantial longitudinal play (7) exists between the blades and the platforms. Sealing lagging (15) which occupies the play is made from an envelope (16) formed with an internal face (17), carried against the flanks an external supple face (18) directed towards the blade surfaces and a internal radial heel (19). The lagging is formed from a long heavy beading (20) contained in the envelope.

Description

L'invention concerne une garniture d'étanchéité disposée dans un assemblage d'aubes sur un disque de soufflante et de plates-formes intermédiaires formant ainsi un rotor.The invention relates to a seal arranged in an assembly of blades on a fan disk and intermediate platforms, thus forming a rotor.

La conception la plus classique de rotors aubagés indispensables notamment dans les turboréacteurs consiste à construire séparément le disque du rotor et les aubes, et à assembler celles-ci à celui-là en engageant des pieds d'aubes dans des rainures du disque. En effet, il est souvent avantageux de produire à part les aubes, qui sont des pièces incurvées de forme souvent compliquée à réaliser.The most classic design of bladed rotors essential in particular in turbojets consists in separately constructing the rotor disc and the blades, and in assembling the latter with the latter by engaging the feet of blades in grooves of the disc. Indeed, it is often advantageous to produce apart from the blades, which are curved parts of shape often complicated to realize.

On se heurte alors à la difficulté d'installer des plates-formes entre les aubes pour border le disque par une surface circulaire et lisse dont la fonction est de délimiter la veine d'écoulement des gaz, car ces plates-formes sont parfois des pièces rapportées entre l'extrados et l'intrados d'aubes adjacentes, ce qui laisse subsister des jeux qui détruisent la continuité de la surface de la veine et qu'il faut donc réduire autant qu'on le peut afin de ne pas compromettre la qualité de l'écoulement.We then encounter the difficulty of installing platforms between the blades to border the disc by a circular and smooth surface whose function is to delimit the gas flow stream, because these platforms are sometimes parts reported between the upper surface and the lower surface of adjacent blades, which leaves games which destroy the continuity of the surface of the vein and which must therefore be reduced as much as possible so as not to compromise the quality of the flow.

Une conception courante consiste à produire les segments de plate-forme d'un bloc avec les aubes. Elle est exposée dans de nombreux brevets et présente l'avantage que les segments de plates-formes se joignent à mi-distance des aubes par des jonctions droites qu'il est facile de combler par une garniture d'étanchéité. L'inconvénient est que les plates-formes, dont l'extension est sensiblement perpendiculaire à celle des aubes, compliquent leur réalisation.A common design is to produce the platform segments of a block with the vanes. It has been exposed in numerous patents and has the advantage that the platform segments join halfway between the blades by straight junctions which it is easy to fill with a gasket. The disadvantage is that the platforms, whose extension is substantially perpendicular to that of the blades, complicate their production.

Il est d'ailleurs avantageux d'alléger le rotor en construisant ces pièces moins exposées aux efforts en matériau composite afin de les alléger, ce qui peut concerner les plates-formes et oblige alors à les séparer des aubes.It is moreover advantageous to lighten the rotor by constructing these parts less exposed to the stresses of composite material in order to lighten them, which can concern the platforms and then obliges them to be separated from the blades.

L'invention s'applique ainsi aux constructions où les plates-formes sont réalisées en tant que pièces détachées des aubes et s'étendent chacune entre une paire d'aubes en formant un jeu avec chacune d'elles, ce qui implique malheureusement que les jeux sont importants le long des aubes à cause de la complexité de la forme de celles-ci et notamment de leur courbure et la nécessité du démontage des plates-formes. Dans une série de réalisations, les plates-formes sont maintenues en position entre les aubes par deux viroles, l'une située en amont du rotor, l'autre en aval.The invention thus applies to constructions where the platforms are produced as separate parts of the blades and each extend between a pair of blades, forming a clearance with each of them, which unfortunately implies that the games are important along the blades because of the complexity of the shape thereof and in particular of their curvature and the need to dismantle the platforms. In a series of embodiments, the platforms are held in position between the blades by two ferrules, one located upstream of the rotor, the other downstream.

En variante, l'invention peut également s'appliquer à un rotor dont les plates-formes possèdent un pied qui vient se loger dans des alvéoles usinés dans le disque.As a variant, the invention can also be applied to a rotor, the platforms of which have a foot which is housed in cells machined in the disc.

L'invention est relative à une garniture d'étanchéité qui peut être placée dans chacun de ces jeux et qui les comble correctement. Plus précisément, elle est relative à un assemblage pour rotor, composé d'aubes encastrées dans le rotor et de plates-formes situées entre des paires d'aubes consécutives, des jeux substantiellement longitudinaux subsistant entre les aubes et les plates-formes, et cet assemblage est caractérisé en ce qu'il comprend des garnitures d'étanchéité occupant les jeux et formées d'une enveloppe composée d'une face portant contre les flancs des plates-formes et d'une face souple dirigée vers les surfaces des aubes. L'enveloppe peut, de façon équivalente, être composée d'une face portant contre les surfaces des aubes et d'une face souple dirigée vers les flancs des plates-formes. De plus, les garnitures sont encore formées d'une pièce longiligne massive dans l'enveloppe, qui peut être sectorisée ou composée d'une pluralité d'éléments.The invention relates to a seal which can be placed in each of these sets and which fills them correctly. More specifically, it relates to an assembly for a rotor, composed of vanes embedded in the rotor and of platforms located between pairs of consecutive vanes, substantially longitudinal clearances remaining between the vanes and the platforms, and this assembly is characterized in that it comprises seals occupying the games and formed of an envelope composed of a face bearing against the sides of the platforms and a flexible face directed towards the surfaces of the blades. The envelope may, in an equivalent manner, be composed of a face bearing against the surfaces of the blades and of a flexible face directed towards the sides of the platforms. In addition, the linings are also formed of a solid elongated piece in the envelope, which can be sectored or composed of a plurality of elements.

On va maintenant décrire l'invention plus en détail à l'aide des figures suivantes annexées à titre illustratif et non limitatif :

  • la figure 1 est une vue générale d'une machine où l'invention est utilisée,
  • la figure 2 est une coupe transversale de l'assemblage représentant une plate-forme maintenue en place par des viroles amont et aval,
  • la figure 3 est une coupe dans le sens circonférentiel de l'assemblage de la figure 2,
  • la figure 4 est une vue de dessus partiellement éclatée,
  • la figure 5 est un détail de la figure 3 et qui illustre le comportement de la garniture d'étanchéité lorsque le moteur tourne conformément à l'invention,
  • la figure 6 est une coupe dans le sens circonférentiel d'une variante de l'invention,
  • et la figure 7 est une vue analogue à la figure 5 qui illustre une autre réalisation de l'invention.
The invention will now be described in more detail with the aid of the following figures, which are given by way of illustration and not limitation:
  • FIG. 1 is a general view of a machine where the invention is used,
  • FIG. 2 is a cross section of the assembly representing a platform held in place by upstream and downstream ferrules,
  • FIG. 3 is a section in the circumferential direction of the assembly of FIG. 2,
  • FIG. 4 is a partially exploded top view,
  • FIG. 5 is a detail of FIG. 3 and which illustrates the behavior of the seal when the engine is running in accordance with the invention,
  • FIG. 6 is a section in the circumferential direction of a variant of the invention,
  • and Figure 7 is a view similar to Figure 5 which illustrates another embodiment of the invention.

On se reporte tout d'abord aux figures 1 à 3. La figure 1 représente essentiellement une turbomachine pourvue comme d'habitude de plusieurs étages de compresseurs, de turbines, etc., et qui s'ouvre, à gauche sur la figure, par une soufflante d'entrée S composée d'un disque 8 de rotor portant un étage circulaire d'aubes 1 radiales qui séparent des plates-formes 2 délimitant une veine d'écoulement. On aborde maintenant la figure 3. On y voit deux aubes 1 adjacentes et une plate-forme 2 intermédiaire, composée d'un longeron central 3 et de noyaux 4 de part et d'autre du longeron 3. Les noyaux 4 présentent des flancs 6 externes orientés vers les aubes 1 et qui s'évasent en direction radiale vers l'extérieur. Le jeu 7, déterminé par le mode de montage, avec les aubes 1 n'est que de quelques millimètres.Reference is first made to FIGS. 1 to 3. FIG. 1 essentially represents a turbomachine provided as usual with several stages of compressors, turbines, etc., and which opens, on the left in the figure, by an inlet fan S composed of a rotor disk 8 carrying a circular stage of radial vanes 1 which separate platforms 2 delimiting a flow stream. We now deal with FIG. 3. We see two adjacent blades 1 and an intermediate platform 2, composed of a central spar 3 and cores 4 on both sides and on the other side of the spar 3. The cores 4 have external flanks 6 oriented towards the blades 1 and which widen in the radial direction towards the outside. The clearance 7, determined by the mounting method, with the blades 1 is only a few millimeters.

Les pièces de plate-forme 2 sont en matériau composite, ce qui allège sensiblement le rotor. On voit sur la figure 2 qu'elles s'étendent sur toutes la longueur du disque 8, et en dépassent des deux côtés par un appendice amont 10 et un appendice aval 11. Une virole amont 12 et une virole aval 13 accolées aux faces latérales du disque 8 et fixées à ces faces selon des dispositions connues coiffent respectivement les appendices 10 et 11 des pièces de plate-forme 2 et retiennent ainsi ces pièces contre les mouvements axiaux et radiaux. Dans cette réalisation, les pièces de plate-forme 2 sont maintenues par les viroles 12 et 13 à quelques dixièmes de millimètre de la surface du disque 8.The platform parts 2 are made of composite material, which significantly lightens the rotor. We see in Figure 2 that they extend over all the length of the disc 8, and protrude from both sides by an upstream appendage 10 and a downstream appendage 11. An upstream ferrule 12 and a downstream ferrule 13 attached to the lateral faces of the disc 8 and fixed to these faces according to known arrangements respectively cover the appendages 10 and 11 of the platform parts 2 and thus retain these parts against the axial and radial movements. In this embodiment, the platform pieces 2 are held by the ferrules 12 and 13 a few tenths of a millimeter from the surface of the disc 8.

Les garnitures d'étanchéité qui occupent les jeux 7 portent la référence générale 15 sur la figure 3. Chacune est composée d'une enveloppe 16 formée d'une face interne 17, d'une face externe 18 et d'un talon 19 radialement interne. La section de l'enveloppe 16 est donc triangulaire telle qu'elle est représentée, au moment de l'insertion des pièces de plate-forme 2. Une pièce longiligne en forme de baguette 20 est engagée dans l'enveloppe 16 et occupe une partie du volume qu'elle englobe. La baguette 20 n'est pas forcément souple et peut être formée de métal ou de matériau composite, mais dont la masse est suffisante pour qu'elle se déplace dans l'enveloppe 16 sous l'action des forces centrifuges créées au fonctionnement.The seals which occupy the sets 7 have the general reference 15 in FIG. 3. Each consists of an envelope 16 formed of an internal face 17, an external face 18 and a radially internal heel 19 . The section of the envelope 16 is therefore triangular as shown, at the time of the insertion of the platform parts 2. A long, baguette-shaped part 20 is engaged in the envelope 16 and occupies part of the volume it encompasses. The rod 20 is not necessarily flexible and can be formed from metal or composite material, but whose mass is sufficient for it to move in the envelope 16 under the action of centrifugal forces created during operation.

En effet, comme on le représente à la figure 5, l'enveloppe 16 est en élastomère, sa face externe 18 et le talon 19 ont la faculté de se déformer, et la baguette 20 a la liberté de glisser dans l'enveloppe 16 vers l'extérieur pour se rapprocher de l'endroit du jeu 7 et le combler. La baguette 20 est avantageusement cylindrique à toutes ses sections pour faciliter son glissement. L'enveloppe 16 prend alors la forme d'un triangle dont la pointe est vers l'intérieur en direction radiale au lieu d'être vers l'extérieur. La face interne 17 reste pour sa part collée au flanc 6 correspondant.Indeed, as shown in Figure 5, the casing 16 is made of elastomer, its outer face 18 and the heel 19 have the ability to deform, and the rod 20 has the freedom to slide in the casing 16 towards outside to get closer to the place of game 7 and fill it. The rod 20 is advantageously cylindrical with all its sections to facilitate its sliding. The envelope 16 then takes the form of a triangle, the point of which is inwards in the radial direction instead of being outwards. The internal face 17 remains for its part glued to the corresponding flank 6.

La figure 4 illustre cette réalisation de l'invention en vue centripète. Chaque pièce de plate-forme 2 porte deux garnitures d'étanchéité 15 semblables, même si les jeux respectifs 7a et 7b qui séparent le bord de la pièce de plate-forme 2 des aubes 1 entre lesquelles elle est située peuvent être différents : la souplesse de l'enveloppe 16 permet de combler des jeux 7 larges aussi bien qu'étroits. On remarque aussi que les flancs 6 des pièces de plate-forme 2 sont sensiblement parallèles aux flancs des aubes 1 devant lesquels ils s'étendent, et que les garnitures d'étanchéité 15 sont courbées de façon semblable. Les jeux 7 sont ainsi comblés sur toute leur longueur par un mouvement sensiblement uniforme de translation des baguettes 20.Figure 4 illustrates this embodiment of the invention in centripetal view. Each platform piece 2 carries two similar seals 15, even if the respective clearances 7a and 7b which separate the edge of the platform piece 2 from the blades 1 between which it is located may be different: the flexibility of the casing 16 makes it possible to fill wide as well as narrow clearances 7. It is also noted that the sides 6 of the platform parts 2 are substantially parallel to the sides of the blades 1 in front of which they extend, and that the seals 15 are similarly curved. The games 7 are thus filled over their entire length by a substantially uniform movement of translation of the rods 20.

La figure 6 illustre une réalisation dans laquelle les pièces de plate-forme 2 possèdent comme les aubes 1 un pied 5 engagé dans un alvéole du disque 8 réalisé par un brochage. Les viroles 12 et 13 peuvent alors être omises.FIG. 6 illustrates an embodiment in which the platform parts 2 have, like the blades 1, a foot 5 engaged in a cell of the disc 8 produced by a broaching. The ferrules 12 and 13 can then be omitted.

La figure 7 illustre une autre réalisation de l'invention, dans laquelle la face interne, ici 17', de l'enveloppe 16' des garnitures d'étanchéité 15 est collée au flanc de l'aube 1, et la face externe 18' et le talon 19' sont dirigés vers le flanc 6 de la plate-forme 2. On s'aperçoit que le fonctionnement est le même car les forces centrifuges déplacent la baguette 20 vers la portion étroite du jeu et le comblent donc.FIG. 7 illustrates another embodiment of the invention, in which the internal face, here 17 ′, of the envelope 16 ′ of the seals 15 is glued to the flank of the blade 1, and the external face 18 ′ and the heel 19 ′ are directed towards the flank 6 of the platform 2. It can be seen that the operation is the same because the centrifugal forces move the rod 20 towards the narrow portion of the game and therefore fill it.

Claims (3)

Assemblage pour rotor, composé d'aubes (1) encastrées dans le rotor, de plates-formes (2) situées et maintenues en place entre des paires d'aubes (1) consécutives, des jeux (7) substantiellement longitudinaux subsistant entre les aubes (1) et les plates-formes (2), caractérisé en ce qu'il comprend des garnitures d'étanchéité (15) occupant en fonctionnement les jeux (7) et formées d'une enveloppe (16) composée d'une face (17) portant contre des flancs (6) des plates-formes (2) et d'une face souple (18, 19) dirigée vers les surfaces des aubes, les garnitures (15) étant encore formées d'une pièce longiligne massive (20) dans l'enveloppe (16).Rotor assembly, comprising vanes (1) embedded in the rotor, platforms (2) located and held in place between pairs of consecutive vanes (1), substantially longitudinal clearances (7) remaining between the vanes (1) and the platforms (2), characterized in that it comprises seals (15) occupying the games (7) in operation and formed of an envelope (16) composed of a face ( 17) bearing against the sides (6) of the platforms (2) and of a flexible face (18, 19) directed towards the surfaces of the blades, the linings (15) still being formed from a solid elongated part (20 ) in the envelope (16). Assemblage pour rotor, composé d'aubes (1) encastrées dans le rotor, de plates-formes (2) situées et maintenues en place entre des paires d'aubes (1) consécutives, des jeux (7) substantiellement longitudinaux subsistant entre les aubes (1) et les plates-formes (2), caractérisé en ce qu'il comprend des garnitures d'étanchéité (15) occupant en fonctionnement les jeux (7) et formées d'une enveloppe (16') composée d'une face (17') portant contre des flancs des aubes et d'une face souple (18', 19') dirigée vers les surfaces des plate-formes, les garnitures (15) étant encore formées d'une pièce longiligne massive (20) dans l'enveloppe (16).Rotor assembly, comprising vanes (1) embedded in the rotor, platforms (2) located and held in place between pairs of consecutive vanes (1), substantially longitudinal clearances (7) remaining between the vanes (1) and platforms (2), characterized in that it comprises seals (15) occupying the games (7) in operation and formed of an envelope (16 ') composed of one face (17 ') bearing against the flanks of the blades and a flexible face (18', 19 ') directed towards the surfaces of the platforms, the linings (15) still being formed from a solid elongated part (20) in the envelope (16). Assemblage pour rotor selon la revendication 1 ou 2, caractérisé en ce que l'enveloppe (16) a une section substantiellement triangulaire s'amincissant radialement vers l'extérieur.Rotor assembly according to claim 1 or 2, characterized in that the casing (16) has a substantially triangular section tapering radially outwards.
EP95400353A 1994-02-23 1995-02-21 Seal between the blades and the intermediate platforms Expired - Lifetime EP0669451B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9402025 1994-02-23
FR9402025A FR2716502B1 (en) 1994-02-23 1994-02-23 Sealing between vanes and intermediate platforms.

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EP0669451A1 true EP0669451A1 (en) 1995-08-30
EP0669451B1 EP0669451B1 (en) 1998-04-08

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EP (1) EP0669451B1 (en)
DE (1) DE69501973T2 (en)
FR (1) FR2716502B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0787890A3 (en) * 1996-02-02 1999-04-28 ROLLS-ROYCE plc Rotors for gas turbine engines

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2739135B1 (en) * 1995-09-21 1997-10-31 Snecma SHOCK ABSORBER ARRANGEMENT BETWEEN ROTOR BLADES
DE19654471B4 (en) * 1996-12-27 2006-05-24 Alstom Rotor of a turbomachine
EP1124038A1 (en) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbine blading
US6916154B2 (en) * 2003-04-29 2005-07-12 Pratt & Whitney Canada Corp. Diametrically energized piston ring
CN100430606C (en) * 2004-01-05 2008-11-05 财团法人工业技术研究院 High-speed cantilever centrifugal compressor rotor mechanism
EP1925781A1 (en) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Blade arrangement
US7762781B1 (en) 2007-03-06 2010-07-27 Florida Turbine Technologies, Inc. Composite blade and platform assembly
GB0806171D0 (en) * 2008-04-07 2008-05-14 Rolls Royce Plc Aeroengine fan assembly
US8827651B2 (en) 2010-11-01 2014-09-09 Rolls-Royce Plc Annulus filler
FR3003294B1 (en) * 2013-03-15 2018-03-30 Safran Aircraft Engines MULTI-FLOW TURBOMOTEUR BLOWER, AND TURBOMOTEUR EQUIPPED WITH SUCH BLOWER
US9926798B2 (en) 2014-08-13 2018-03-27 Rolls-Royce Corporation Method for manufacturing composite fan annulus filler having nano-coating

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1331209A (en) * 1969-10-28 1973-09-26 Secr Defence Bladed rotors for fluid flow machines
EP0081416A1 (en) * 1981-12-03 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping device for the blades of a turbo machine fan
FR2619158A1 (en) * 1987-08-05 1989-02-10 Gen Electric DEVICE FOR SEALING AND DAMPING THE VIBRATIONS OF THE PLATFORM OF A TURBINE BLADE
EP0488874A1 (en) * 1990-11-28 1992-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fan rotor with blades without platforms and fillers reconstructing the streamline profile
WO1993022539A1 (en) * 1992-05-07 1993-11-11 Rolls-Royce Plc Rotors for gas turbine engines
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4111603A (en) * 1976-05-17 1978-09-05 Westinghouse Electric Corp. Ceramic rotor blade assembly for a gas turbine engine
US4784573A (en) * 1987-08-17 1988-11-15 United Technologies Corporation Turbine blade attachment
US5222865A (en) * 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
FR2706528B1 (en) * 1993-06-10 1995-09-01 Snecma Separate inter-blade platform of turbine engine rotor blade disc.
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1331209A (en) * 1969-10-28 1973-09-26 Secr Defence Bladed rotors for fluid flow machines
EP0081416A1 (en) * 1981-12-03 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping device for the blades of a turbo machine fan
FR2619158A1 (en) * 1987-08-05 1989-02-10 Gen Electric DEVICE FOR SEALING AND DAMPING THE VIBRATIONS OF THE PLATFORM OF A TURBINE BLADE
EP0488874A1 (en) * 1990-11-28 1992-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fan rotor with blades without platforms and fillers reconstructing the streamline profile
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
WO1993022539A1 (en) * 1992-05-07 1993-11-11 Rolls-Royce Plc Rotors for gas turbine engines

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0787890A3 (en) * 1996-02-02 1999-04-28 ROLLS-ROYCE plc Rotors for gas turbine engines

Also Published As

Publication number Publication date
FR2716502A1 (en) 1995-08-25
US5520514A (en) 1996-05-28
EP0669451B1 (en) 1998-04-08
DE69501973D1 (en) 1998-05-14
DE69501973T2 (en) 1998-08-20
FR2716502B1 (en) 1996-04-05

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