EP1507960B1 - Bladed rotor wheel of a turbomachine - Google Patents

Bladed rotor wheel of a turbomachine Download PDF

Info

Publication number
EP1507960B1
EP1507960B1 EP03756014.1A EP03756014A EP1507960B1 EP 1507960 B1 EP1507960 B1 EP 1507960B1 EP 03756014 A EP03756014 A EP 03756014A EP 1507960 B1 EP1507960 B1 EP 1507960B1
Authority
EP
European Patent Office
Prior art keywords
fact
elastic
platforms
wheel
zone
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.)
Expired - Lifetime
Application number
EP03756014.1A
Other languages
German (de)
French (fr)
Other versions
EP1507960A1 (en
Inventor
Chantal Giot
Marc Marchi
Christian Gosselin
Eric Bil
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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1507960A1 publication Critical patent/EP1507960A1/en
Application granted granted Critical
Publication of EP1507960B1 publication Critical patent/EP1507960B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the upper wall 19 of the liner is spread over its greater extent from the lower face of the platform 34, as is visible on the figure 5 , the shirt 10 tilting about an axis intersecting the plane of the figure 5 at the point referenced 44 and located in the vicinity of the downstream flared edge 13.
  • the protrusion 43 of the upstream radial wall 35 makes it possible to limit the sliding of the elastic zone 18, and to retain the liner 10 in the upper zone of the cavity 37.

Description

L'invention concerne la maîtrise des zones de fuite sous les plates-formes des aubes d'une roue aubagée dans une turbomachine.The invention relates to the control of the trailing zones under the platforms of the blades of a bladed wheel in a turbomachine.

Elle concerne plus précisément une roue aubagée de turbomachine comportant un disque présentant à sa périphérie une pluralité d'alvéoles sensiblement axiales, une pluralité d'aubes dont les pieds sont retenus dans lesdites alvéoles et qui présentent des plates-formes destinées à délimiter, du côté radialement intérieur, la veine de flux gazeux et des parois radiales amont et aval qui s'étendent à partir desdites plates-formes vers la périphérie dudit disque, des cavités inter-aubes délimitées par lesdites plates-formes et la périphérie dudit disque, et des dispositifs d'étanchéité des espaces inter-aubes réalisés sous forme de chemises ayant des bords évasés radialement vers l'intérieur et disposées dans lesdites cavités contre les parois des plates-formes de deux aubes voisines.It relates more specifically to a turbomachine bladed wheel having a disc having at its periphery a plurality of substantially axial cells, a plurality of blades whose feet are retained in said cells and which have platforms for delimiting, on the side radially inner, the stream of gas flow and upstream and downstream radial walls extending from said platforms to the periphery of said disk, inter-blade cavities delimited by said platforms and the periphery of said disk, and inter-vane gap sealing devices in the form of jackets having flared edges radially inward and disposed in said cavities against the wall walls of two adjacent blades.

La figure 1 montre en perspective une chemise d'étanchéité 1 selon l'état de la technique qui présente un bord amont 2 et un bord aval 3 évasés radialement vers l'intérieur, ainsi que deux bords évasés longitudinaux incurvés qui épousent les flancs des aubes sous les plates-formes. Les bords amont 2 et aval 3 sont destinés à venir au voisinage immédiat des parois radiales adjacentes amont et aval des deux aubes voisines, afin de limiter les fuites par l'espace séparant les parois latérales voisines. La paroi supérieure 6 de chaque chemise vient appuyer contre les faces inférieures de deux plates-formes voisines sous l'action des forces centrifuges lorsque la roue est en rotation et assure l'étanchéité de l'interstice séparant les plates-formes voisines. Par construction, les bords évasés sont pratiquement indéformables sous l'action des forces centrifuges, et on ne peut garantir que les bords évasés amont 2 et aval 3 soient effectivement appliqués contre les parois radiales amont et aval des aubes. Ainsi que cela est montré sur la figure 2, ces bords peuvent se trouver écartés des parois radiales adjacentes, ce qui entraîne une fuite d'air f entre la cavité sous la plate-forme et la veine de flux gazeux dans ces zones, ce qui est préjudiciable au rendement de la roue. Les documents EP851096 ou US4505642 décrivent roues aubagées connues.The figure 1 shows in perspective a sealing liner 1 according to the state of the art which has an upstream edge 2 and a downstream edge 3 flared radially inward, and two curved longitudinal flared edges which fit the flanks of the blades under the plates Platforms. The upstream and downstream edges 2 and 3 are intended to come in the immediate vicinity of the adjacent upstream and downstream radial walls of the two neighboring blades, in order to limit leakage by the space separating the neighboring sidewalls. The upper wall 6 of each liner presses against the lower faces of two neighboring platforms under the action of centrifugal forces when the wheel is rotating and seals the gap separating the neighboring platforms. By construction, the flared edges are virtually indeformable under the action of centrifugal forces, and it can not be guaranteed that the upstream flared edges 2 and downstream 3 are effectively applied against the upstream and downstream radial walls of the blades. As this is shown on the figure 2 these edges may be spaced apart from the adjacent radial walls, resulting in air leakage f between the cavity under the platform and the flow of gas stream in these areas, which is detrimental to the efficiency of the wheel. The documents EP851096 or US4505642 describe known bladed wheels.

Le but de l'invention est de mieux maîtriser la zone de fuite sous une plate-forme d'aube notamment au niveau des interstices entre les parois radiales sous plates-formes.The object of the invention is to better control the leakage zone under a blade platform especially at the interstices between the radial walls under platforms.

L'invention atteint son but par le fait que chaque chemise présente sur l'un de ses bords évasés, amont ou aval, une zone élastique et les parois radiales adjacentes à ces bords sont raccordées aux plates-formes par des surfaces internes inclinées par rapport à un plan radial, et contre lesquelles ladite zone élastique est en appui, de telle manière que ladite zone élastique peut glisser radialement vers l'intérieur en cas d'arrêt de la rotation de ladite roue, et radialement vers l'extérieur sous l'action des forces centrifuges afin de solliciter ladite chemise à se déplacer axialement vers les parois radiales éloignées de ladite zone élastique pour améliorer l'étanchéité dans cette zone.The invention achieves its object by the fact that each liner has on one of its flared edges, upstream or downstream, an elastic zone and the radial walls adjacent to these edges are connected to the platforms by internal surfaces inclined relative to each other. at a radial plane, and against which said elastic zone bears, so that said elastic zone can slide radially inwards in case of stopping of the rotation of said wheel, and radially outwardly under the action of the centrifugal forces to urge said liner to move axially towards the radial walls remote from said elastic zone to improve the seal in this area.

En cas d'arrêt de la roue aubagée, la zone élastique glisse radialement vers l'intérieur et la chemise se met hors contrainte et s'écarte des parois inférieures des deux plates-formes au moins dans les régions voisines de la zone élastique. Lorsque la roue aubagée est mise en rotation, les forces centrifuges vont appliquer la chemise contre les parois inférieures des plates-formes, et les forces élastiques vont repousser le bord évasé opposé vers les parois latérales opposées du bord élastique, afin d'améliorer l'étanchéité à cet endroit. Les zones élastiques étant toujours en appui sur les parois latérales adjacentes, l'étanchéité est garantie dans cette zone.In case of stopping of the bladed wheel, the elastic zone slides radially inwards and the liner goes out of stress and deviates from the lower walls of the two platforms at least in the regions adjacent to the elastic zone. When the bladed wheel is rotated, the centrifugal forces will apply the liner against the lower walls of the platforms, and the elastic forces will push the opposite flared edge toward the opposite side walls of the elastic edge, to improve the tightness at this place. The elastic zones being always resting on the adjacent side walls, the sealing is guaranteed in this zone.

Avantageusement les parois radiales éloignées des zones élastiques comportent des butées pour limiter le déplacement axial des chemises sous l'action des forces centrifuges.Advantageously, the radial walls remote from the elastic zones comprise stops to limit the axial displacement of the jackets under the action of centrifugal forces.

Les parois latérales adjacentes aux zones élastiques comportent également des butées pour limiter le glissement vers l'intérieur desdites zones élastiques.The side walls adjacent the elastic zones also comprise stops to limit the sliding inward of said elastic zones.

Selon une caractéristique de l'invention les zones élastiques sont délimitées circonférentiellement par deux entailles ménagées dans le bord évasé correspondant des chemises. Cette disposition permet de mettre en oeuvre facilement l'invention sans coût supplémentaire.According to one characteristic of the invention the elastic zones are delimited circumferentially by two notches formed in the corresponding flared edge of the shirts. This arrangement makes it easy to implement the invention without additional cost.

L'invention s'applique notamment aux roues aubagées de turbine.The invention is particularly applicable to bladed turbine wheels.

Dans ce cas particulier, la zone élastique est prévue sur le bord amont, et l'angle de la surface inclinée par rapport au plan radial est supérieur à la pente de la plate-forme par rapport à l'axe de rotation de la turbomachine.In this particular case, the elastic zone is provided on the upstream edge, and the angle of the inclined surface relative to the radial plane is greater than the slope of the platform relative to the axis of rotation of the turbomachine.

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

  • la figure 1 est une vue de dessous et en perspective d'une chemise d'étanchéité selon l'art antérieur ;
  • la figure 2 est une vue latérale en coupe d'un bord de chemise et d'une paroi radiale d'aube selon l'art antérieur ;
  • la figure 3 est une vue de dessus et en perspective d'une chemise d'étanchéité selon l'invention ;
  • la figure 4 est une vue de dessous et en perspective de la chemise d'étanchéité de la figure 3 ;
  • la figure 5 est une coupe selon un plan contenant l'axe de la roue aubagée, qui montre la disposition de la chemise d'étanchéité selon l'invention dans la cavité sous plates-formes, après montage et en l'absence de forces centrifuges ; et
  • la figure 6 est semblable à la figure 5 et montre la position de la chemise d'étanchéité, lorsqu'elle est soumise à des forces centrifuges par suite de la rotation de la roue aubagée.
  • Les figures 1 et 2 montrent l'état de la technique qui a été discuté supra dans le présent mémoire.
  • Les figures 3 et 4 montrent une chemise d'étanchéité 10 selon l'invention qui comporte des bords évasés radialement vers l'intérieur, à savoir un bord amont 12, un bord aval 13, et entre le bord amont 12 et le bord aval 13 deux bords longitudinaux évasés incurvés qui épousent la forme des flancs des deux aubes adjacentes.
Other characteristics and advantages of the invention will emerge on reading the following description, given by way of example and with reference to the appended drawings in which:
  • the figure 1 is a view from below and in perspective of a sealing jacket according to the prior art;
  • the figure 2 is a sectional side view of a liner edge and a radial blade wall according to the prior art;
  • the figure 3 is a view from above and in perspective of a sealing sleeve according to the invention;
  • the figure 4 is a view from below and in perspective of the sealing jacket of the figure 3 ;
  • the figure 5 is a section along a plane containing the axis of the bladed wheel, which shows the arrangement of the sealing liner according to the invention in the cavity under platforms, after assembly and in the absence of centrifugal forces; and
  • the figure 6 is similar to the figure 5 and shows the position of the sealing liner when it is subjected to centrifugal forces as a result of the rotation of the bladed wheel.
  • The Figures 1 and 2 show the state of the art discussed above in this memoir.
  • The Figures 3 and 4 show a sealing liner 10 according to the invention which has flared edges radially inward, namely an upstream edge 12, a downstream edge 13, and between the upstream edge 12 and the downstream edge 13 two curved flared longitudinal edges which follow the shape of the flanks of the two adjacent blades.

Le bord amont 12 présente deux entailles 16 et 17 qui délimitent entre elles une zone élastique 18 qui, au repos, émerge sur l'avant par rapport au bord amont 2 de la chemise 1 selon l'état de la technique montré sur la figure 1. Autrement dit, au repos, la zone élastique 18 se trouve à l'extérieur de la surface imaginaire qui relierait de manière continue et douce les extrémités 12a et 12b du bord amont 12, situées au-delà des entailles 16 et 17, et raccordées respectivement aux bords longitudinaux 14 et 15 par des surfaces convexes.The upstream edge 12 has two notches 16 and 17 which delimit between them an elastic zone 18 which, at rest, emerges on the front with respect to the upstream edge 2 of the liner 1 according to the state of the art shown on FIG. figure 1 . In other words, at rest, the elastic zone 18 is outside the imaginary surface which connect continuously and smoothly the ends 12a and 12b of the upstream edge 12, located beyond the notches 16 and 17, and respectively connected to the longitudinal edges 14 and 15 by convex surfaces.

Les figures 5 et 6 montrent une roue aubagée 30 qui comporte un disque 31 qui présente à sa périphérie une pluralité d'alvéoles 32 sensiblement axiales dans chacun desquelles loge le pied d'une aube 33. Chaque aube 33 présente au-dessus de son pied une plate-forme 34 qui délimite, radialement à l'intérieur, la veine de flux gazeux F traversant la grille d'aubes, cette plate-forme 34 étant raccordée à une paroi radiale amont 35 et à une paroi radiale aval 36 qui s'étendent vers la périphérie du disque 31. Des cavités 37 inter-aubes sont ainsi aménagées à la périphérie du disque 31 sous les plates-formes 34. Si on regarde la grille d'aubes axialement dans le sens du flux gazeux F, chaque aube 33 présente une portion de plate-forme à droite et une portion de plate-forme à gauche. Il en est de même des parois radiales 35 et 36. Chaque cavité sous plates-formes 37 est ainsi délimitée par des portions de plate-forme droite et gauche de deux aubes adjacentes, et par leurs portions de parois latérales amont et aval, droites et gauches. Par construction et pour les besoins de montage, un jeu ou interstice sépare les portions de droite et de gauche qu'il est nécessaire d'étancher par une chemise d'étanchéité.The figures 5 and 6 show a bladed wheel 30 which comprises a disk 31 which has at its periphery a plurality of substantially axial cells 32 in each of which houses the foot of a blade 33. Each blade 33 has a platform 34 above its foot. which delimits, radially on the inside, the stream of gas flow F passing through the blade grid, this platform 34 being connected to an upstream radial wall 35 and a downstream radial wall 36 which extend towards the periphery of the 31. Inter-blade cavities 37 are thus arranged at the periphery of the disk 31 under the platforms 34. If the blade grid is viewed axially in the direction of the gas flow F, each blade 33 has a flat portion. -form to the right and a platform portion to the left. It is the same for the radial walls 35 and 36. Each cavity under platforms 37 is thus delimited by right and left platform portions of two adjacent blades, and their portions of upstream and downstream side walls, straight and lefts. By construction and for assembly purposes, a clearance or gap separates the right and left portions that must be sealed by a sealing jacket.

Ainsi que cela est montré sur les figures 5 et 6, le raccordement 38 entre la paroi radiale amont 35 et la plate-forme 34 présente du côté de la cavité 37 une surface 39 qui fait un angle α avec le plan radial perpendiculaire à l'axe de rotation de la roue aubagée 30. La paroi radiale aval 36 est raccordée à la plate-forme 34 par une zone 40 qui présente du côté de la cavité 37 une surface courbe 41 complémentaire de l'évasement du bord amont 13 de la chemise 10. La paroi radiale aval 36 présente en outre sur sa face interne une excroissance 42 qui sert de butée au rebord aval de la chemise 10. La paroi radiale amont 35 présente également sur sa face située du côté de la cavité 37, une excroissance 43.As this is shown on the figures 5 and 6 , the connection 38 between the upstream radial wall 35 and the platform 34 has on the side of the cavity 37 a surface 39 which makes an angle α with the radial plane perpendicular to the axis of rotation of the bladed wheel 30. The wall radial downstream 36 is connected to the platform 34 by an area 40 which has on the side of the cavity 37 a curved surface 41 complementary to the flare of the upstream edge 13 of the liner 10. The downstream radial wall 36 further has on its inner face a protrusion 42 which serves as a stop at the downstream edge of the liner 10. The upstream radial wall 35 also has on its face located on the side of the cavity 37, an outgrowth 43.

La chemise 10 est montée dans la cavité 37 de telle manière que le bord aval 13 soit positionné au-dessus de l'excroissance 42 et que la zone élastique 18 soit positionnée au-dessus de l'excroissance 43. Dans cette position, la zone élastique 18 de la chemise 10 est en appui sur la surface inclinée 39.The liner 10 is mounted in the cavity 37 so that the downstream edge 13 is positioned above the protrusion 42 and the elastic zone 18 is positioned above the protrusion 43. In this position, the elastic zone 18 of the liner 10 bears on the inclined surface 39.

L'angle α de la surface inclinée 39 est calculé en fonction de la pente de la plate-forme 34 par rapport à l'axe de rotation de la roue et en fonction de l'angle de frottement ϕ de la chemise 10 contre la surface interne de la plate-forme 34, pour que, en l'absence de force centrifuge, c'est-à-dire lorsque la roue aubagée 30 est à l'arrêt, la zone élastique 18 glisse radialement vers l'intérieur sur la surface inclinée 39.The angle α of the inclined surface 39 is calculated as a function of the slope of the platform 34 with respect to the axis of rotation of the wheel and as a function of the friction angle φ of the liner 10 against the surface internal of the platform 34, so that, in the absence of centrifugal force, that is to say when the bladed wheel 30 is stopped, the elastic zone 18 slides radially inwards on the surface inclined 39.

Dans cette position, la paroi supérieure 19 de la chemise est écartée sur sa plus grande étendue de la face inférieure de la plate-forme 34, ainsi que cela est visible sur la figure 5, la chemise 10 basculant autour d'un axe coupant le plan de la figure 5 au point référencé 44 et situé au voisinage du bord évasé aval 13. L'excroissance 43 de la paroi radiale amont 35 permet de limiter le glissement de la zone élastique 18, et de retenir la chemise 10 dans la zone supérieure de la cavité 37.In this position, the upper wall 19 of the liner is spread over its greater extent from the lower face of the platform 34, as is visible on the figure 5 , the shirt 10 tilting about an axis intersecting the plane of the figure 5 at the point referenced 44 and located in the vicinity of the downstream flared edge 13. The protrusion 43 of the upstream radial wall 35 makes it possible to limit the sliding of the elastic zone 18, and to retain the liner 10 in the upper zone of the cavity 37.

La figure 6 montre la position de la chemise 10 lors de la rotation de la roue aubagée 30. Dans cette position, la chemise 10 est soumise à des forces centrifuges qui tendent à la plaquer contre la face interne de la plate-forme 34. La zone élastique 18 est sollicitée radialement vers l'extérieur et elle glisse contre la paroi inclinée 39.The figure 6 shows the position of the liner 10 during the rotation of the bladed wheel 30. In this position, the liner 10 is subjected to centrifugal forces which tend to press against the inner face of the platform 34. The elastic zone 18 is urged radially outwards and slides against the inclined wall 39.

L'angle α est avantageusement supérieur à la pente de la plate-forme 34. Lors du déplacement vers l'extérieur de la zone élastique 18, par basculement de la chemise 10 autour de l'axe de pivotement défini par le point référencé 44, la force élastique exercée par la zone élastique 18 augmente, et cette force tend à déplacer axialement la chemise 10 vers la paroi radiale aval 36 ce qui améliore l'étanchéité au niveau de la zone de raccordement 40. Le déplacement axial de la chemise 10 est limité par l'excroissance 42 qui sert de butée.The angle α is advantageously greater than the slope of the platform 34. During the outward movement of the elastic zone 18, by tilting of the liner 10 around the pivot axis defined by the point referenced 44, the elastic force exerted by the elastic zone 18 increases, and this force tends to axially move the liner 10 towards the downstream radial wall 36 which improves the sealing at the connection zone 40. The axial displacement of the liner 10 is limited by the protrusion 42 which serves as a stop.

Lors de la mise à l'arrêt de la roue aubagée 30, la chemise 10 reprendra la position montrée sur la figure 5, dès que les forces centrifuges seront insuffisantes pour empêcher le glissement de la zone élastique 18 sur la paroi inclinée 39.When stopping the bladed wheel 30, the liner 10 will resume the position shown on the figure 5 as soon as the centrifugal forces are insufficient to prevent the sliding of the elastic zone 18 on the inclined wall 39.

Claims (6)

  1. A turbomachine blade-wheel comprising a disk (31) presenting a plurality of substantially axial slots on its periphery, a plurality of blades (33) having roots that are retained in said slots, and which present platforms (34) for defining, on the radially inner side, the stream of gas (F) and upstream and downstream radial walls (35, 36) which extend from said platforms (34) towards the periphery of said disk, inter-blade cavities (37) defined by said platforms and the periphery of said disk, and sealing devices for sealing the inter-blade spaces, the sealing devices being made in the form of liners (10) having edges (12, 13, 14, 15) that flare radially inwards and that are disposed in said cavities (37) against the walls of the platforms of two adjacent blades, characterized by the fact that each liner (10) presents an elastic zone (18) on one of its upstream and downstream flared edges(12), and the radial walls (35) adjacent to said edge are connected to the platforms (34) by inside surfaces that are inclined (39) relative to a radial plane, and against which edges said elastic zone (18) bears, in such a manner that said elastic zone can slide radially inwards in the event of said wheel ceasing to rotate, and radially outwards under the action of centrifugal forces in order to urge said liner (10) to move axially towards the radial walls (36) distant from said elastic zone (18) so as to improve sealing in said zone,
    characterized by the fact that the elastic zones (18) are circumferentially defined by two notches (16, 17) that are cut in the corresponding flared edges (12) of the liners (10).
  2. A wheel according to claim 1, characterized by the fact that the radial walls (36) that are spaced apart from the elastic zones include abutments (42) to limit the axial movement of the liners (10) under the action of centrifugal forces.
  3. A wheel according to claim 1 or 2, characterized by the fact that the lateral walls (36) that are adjacent to the elastic zones (18) include abutments (42) to limit inward sliding of said elastic zones.
  4. A wheel according to any one of claims 1 to 3, characterized by the fact that the elastic zone (18) is provided on the upstream edge.
  5. A wheel according to claim 4, characterized by the fact that it is a turbine blade-wheel.
  6. A wheel according to claim 5, characterized by the fact that the angle α of the inclined surface (39) is greater than the slope of the platform relative to the axis of rotation of the turbomachine.
EP03756014.1A 2002-05-30 2003-05-28 Bladed rotor wheel of a turbomachine Expired - Lifetime EP1507960B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0206599A FR2840352B1 (en) 2002-05-30 2002-05-30 MASTING THE LEAK AREA UNDER A DAWN PLATFORM
FR0206599 2002-05-30
PCT/FR2003/001611 WO2003102380A1 (en) 2002-05-30 2003-05-28 Control of leak zone under blade platform

Publications (2)

Publication Number Publication Date
EP1507960A1 EP1507960A1 (en) 2005-02-23
EP1507960B1 true EP1507960B1 (en) 2017-03-08

Family

ID=29558830

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03756014.1A Expired - Lifetime EP1507960B1 (en) 2002-05-30 2003-05-28 Bladed rotor wheel of a turbomachine

Country Status (9)

Country Link
US (1) US7214034B2 (en)
EP (1) EP1507960B1 (en)
JP (1) JP2005528550A (en)
AU (1) AU2003249424A1 (en)
CA (1) CA2487471C (en)
FR (1) FR2840352B1 (en)
RU (1) RU2313671C2 (en)
UA (1) UA81764C2 (en)
WO (1) WO2003102380A1 (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2874402B1 (en) * 2004-08-23 2006-09-29 Snecma Moteurs Sa ROTOR BLADE OF A COMPRESSOR OR A GAS TURBINE
GB0804260D0 (en) * 2008-03-07 2008-04-16 Rolls Royce Plc Annulus filler
US8070448B2 (en) * 2008-10-30 2011-12-06 Honeywell International Inc. Spacers and turbines
CA2754795C (en) * 2009-03-09 2016-06-07 Avio S.P.A. Rotor for turbomachines
GB201016597D0 (en) * 2010-10-04 2010-11-17 Rolls Royce Plc Turbine disc cooling arrangement
US9022727B2 (en) 2010-11-15 2015-05-05 Mtu Aero Engines Gmbh Rotor for a turbo machine
ES2710516T3 (en) * 2010-11-17 2019-04-25 MTU Aero Engines AG Rotor for a turbomachine, corresponding turbomachine and manufacturing, repair or overhaul procedure
FR2972482B1 (en) * 2011-03-07 2016-07-29 Snecma TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION
FR2974387B1 (en) 2011-04-19 2015-11-20 Snecma TURBINE WHEEL FOR A TURBOMACHINE
EP2551464A1 (en) * 2011-07-25 2013-01-30 Siemens Aktiengesellschaft Airfoil arrangement comprising a sealing element made of metal foam
FR2981979B1 (en) 2011-10-28 2013-11-29 Snecma TURBINE WHEEL FOR A TURBOMACHINE
FR2986557B1 (en) * 2012-02-02 2015-09-25 Snecma OPTIMIZATION OF THE SUPPORT POINTS OF MOBILE AUBES IN A PROCESS FOR MACHINING THESE AUBES
WO2014051688A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Seal damper with improved retention
US20140271205A1 (en) * 2013-03-12 2014-09-18 Solar Turbines Incorporated Turbine blade pin seal
WO2014160641A1 (en) * 2013-03-25 2014-10-02 United Technologies Corporation Rotor blade with l-shaped feather seal
FR3006364B1 (en) * 2013-05-30 2018-07-13 Safran Aircraft Engines TURBOMACHINE WHEEL, IN PARTICULAR FOR LOW PRESSURE TURBINE
EP2881544A1 (en) 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Airfoil device for a gas turbine and corresponding arrangement
FR3027950B1 (en) * 2014-11-04 2019-10-18 Safran Aircraft Engines TURBINE WHEEL FOR A TURBOMACHINE
FR3027949B1 (en) * 2014-11-04 2019-07-26 Safran Aircraft Engines TURBINE WHEEL FOR A TURBOMACHINE
US10030523B2 (en) * 2015-02-13 2018-07-24 United Technologies Corporation Article having cooling passage with undulating profile
US9822644B2 (en) 2015-02-27 2017-11-21 Pratt & Whitney Canada Corp. Rotor blade vibration damper
EP3438410B1 (en) * 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine
FR3090030B1 (en) 2018-12-12 2020-11-20 Safran Aircraft Engines Retaining device for removing a turbine engine impeller and method using it
FR3092863B1 (en) 2019-02-15 2021-01-22 Safran Aircraft Engines Turbine wheel for aircraft turbomachines comprising sealing members for inter-blade cavities
US11365642B2 (en) * 2020-04-09 2022-06-21 Raytheon Technologies Corporation Vane support system with seal
US11773731B2 (en) * 2022-01-04 2023-10-03 Rtx Corporation Bathtub damper seal arrangement for gas turbine engine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999631A (en) * 1958-09-05 1961-09-12 Gen Electric Dual airfoil
FR2503247B1 (en) * 1981-04-07 1985-06-14 Snecma IMPROVEMENTS ON THE FLOORS OF A GAS TURBINE OF TURBOREACTORS PROVIDED WITH AIR COOLING MEANS OF THE TURBINE WHEEL DISC
US4505642A (en) * 1983-10-24 1985-03-19 United Technologies Corporation Rotor blade interplatform seal
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5228835A (en) * 1992-11-24 1993-07-20 United Technologies Corporation Gas turbine blade seal
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
FR2722240B1 (en) * 1994-07-06 1996-08-14 Snecma METAL LIPSTICK AND TURBOMACHINE EQUIPPED WITH THIS SEAL
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
JP2005528550A (en) 2005-09-22
EP1507960A1 (en) 2005-02-23
FR2840352B1 (en) 2005-12-16
WO2003102380A1 (en) 2003-12-11
CA2487471A1 (en) 2003-12-11
RU2313671C2 (en) 2007-12-27
US20050175463A1 (en) 2005-08-11
AU2003249424A1 (en) 2003-12-19
CA2487471C (en) 2011-07-12
FR2840352A1 (en) 2003-12-05
UA81764C2 (en) 2008-02-11
US7214034B2 (en) 2007-05-08
RU2004138597A (en) 2005-08-10

Similar Documents

Publication Publication Date Title
EP1507960B1 (en) Bladed rotor wheel of a turbomachine
EP2060750B1 (en) Stage of a turbine or compressor, in particular of a turbomachine
EP1760258B1 (en) Locking appartus for an axial retention ring of a blade
EP2780553B1 (en) Impeller for a turbomachine
CA2585875C (en) Rotor blade retention system
CA2647057C (en) Sectorized distributor for a turbine
EP1760259B1 (en) Locking apparatus for an axial retention ring of a blade
EP1895103B1 (en) Rotor vane of a turbomachine
FR2918409A1 (en) Rotating part i.e. fan, for turbine engine of aircraft, has blade with circumferential projection detected in continuity of adjacent platform forming sector, where projection participates in definition of inter-blade surface
EP2366061A1 (en) Turbine wheel with an axial retention system for vanes
WO2011157957A1 (en) Angular stator sector for a turbomachine compressor, turbomachine stator and turbomachine comprising such a sector
EP2060751B1 (en) Turbine or compressor stage of a jet engine
EP1630350B1 (en) Rotor blade of a compressor or a gas turbine
FR3075869A1 (en) MOBILE TURBINE WHEEL FOR AIRCRAFT TURBOMACHINE, COMPRISING A SEAL RING RADIALLY RETAINED BY INCREASES ON THE ECHASSE DES AUBES
FR2993599A1 (en) TURBOMACHINE LABYRINTH DISK
EP3677752B1 (en) Improved seal assembly for an inter-blade platform
WO2019224464A1 (en) Improved turbmachine fan disc
WO2017162975A1 (en) Fan assembly, disk and platform
EP1818507A1 (en) Rotor wheel of a turbomachine
EP3683450A1 (en) Turbine engine rotor assembly
FR3078740A1 (en) DYNAMIC LICENSE SEAL COMPRISING AN ACTIVE PART IN A CIRCONFERENTIALLY LIMITED SIZE
WO2023041868A1 (en) Moving blade for a turbine of a turbine engine, comprising a stilt equipped with projections for radially retaining the blade
FR3127018A1 (en) Moving blade for a turbomachine turbine, having a design improving the sealing of the inter-blade cavities
WO2023247903A1 (en) Bladed assembly for a turbomachine, turbine for a turbomachine, and turbomachine
FR3092861A1 (en) TURBOMACHINE ASSEMBLY WITH A CLAMP ON A SEALING RING

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20041115

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA

RBV Designated contracting states (corrected)

Designated state(s): DE ES FR GB IT SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160909

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAR Information related to intention to grant a patent recorded

Free format text: ORIGINAL CODE: EPIDOSNIGR71

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

INTC Intention to grant announced (deleted)
AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

INTG Intention to grant announced

Effective date: 20170131

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 60349974

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170308

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 60349974

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20171211

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20180130

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20180420

Year of fee payment: 16

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190529

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190528

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20220426

Year of fee payment: 20

Ref country code: FR

Payment date: 20220421

Year of fee payment: 20

Ref country code: DE

Payment date: 20220420

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 60349974

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20230527

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20230527