EP2060743B1 - Sealing of a stator guide vane ring in a turbine stage - Google Patents

Sealing of a stator guide vane ring in a turbine stage Download PDF

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Publication number
EP2060743B1
EP2060743B1 EP08163591A EP08163591A EP2060743B1 EP 2060743 B1 EP2060743 B1 EP 2060743B1 EP 08163591 A EP08163591 A EP 08163591A EP 08163591 A EP08163591 A EP 08163591A EP 2060743 B1 EP2060743 B1 EP 2060743B1
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EP
European Patent Office
Prior art keywords
sheet
ring
nozzle
annular
outer rim
Prior art date
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Application number
EP08163591A
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German (de)
French (fr)
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EP2060743A1 (en
Inventor
Philippe Gérard Marie Hazevis
Xavier Firmin Camille Jean Lescure
Aurélien René-Pierre Massot
Jean-Luc Soupizon
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP2060743A1 publication Critical patent/EP2060743A1/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
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to the sealing of a rotor ring in a turbine stage of a turbomachine such as an airplane turbojet or turboprop engine as described in US Pat. EP 1538306A .
  • a turbomachine turbine comprises at least one stage comprising a distributor formed of an annular row of fixed vanes and followed by a rotor wheel mounted inside a sectorized ring.
  • the distributor comprises at its downstream end an annular flange which extends radially outwards and which carries attachment means on a casing of the turbine.
  • the downstream sectorized ring comprises an upstream cylindrical rim which is held radially on a rail of the turbine casing by means of an annular locking member with a C-shaped or U-shaped section axially engaged on the casing rail and on the cylindrical rim of the ring.
  • the cylindrical rim of the ring and the casing rail are generally thermally protected by an annular plate which is mounted between the outer rim of the distributor and the upstream end of the ring to limit the passage of gas from the vein of the ring.
  • turbine radially outwardly in the annular housing space of the rim of the ring and crankcase rail.
  • the seal is not perfect and hot gas leaks from the vein of the turbine can increase the temperature of the crankcase hooks and cause the formation of cracks or cracks may destroy the hooks.
  • vanes of the distributor generally comprise cooling air flow channels taken upstream on the compressor of the turbomachine.
  • the object of the invention is in particular to provide a simple, effective and economical answer to these problems of the prior art.
  • It relates to a turbine stage comprising sealing means between the distributor and the ring sectorized which are simple and effective to prevent the passage of gas in a radial direction between the outer rim of the distributor and the upstream end of the ring.
  • a turbine stage of a turbomachine comprising a rotor wheel mounted inside a sectorized ring carried by a turbine casing, a distributor located upstream of the wheel and formed of a row.
  • annular fixed vanes this distributor comprising at its downstream end an outer annular flange having fastening means on the turbine housing, sealing means being provided between the outer rim of the distributor and the upstream end of the ring for limiting the passage of gas radially between the outer rim of the distributor and the ring, characterized in that the sealing means comprise an annular plate which extends substantially radially between the outer rim of the distributor and the end upstream of the ring and which comprises, at its inner periphery and at its outer periphery, axial support means against a downstream face of the external rim of the distributor, the annular part e median of this sheet being axially spaced from the outer rim of the distributor and being in axial bearing against the upstream end of the ring, the sheet being resiliently biased in the
  • the sealing plate according to the invention bears axially in the direction of the upstream, at its inner periphery and at its outer periphery, on the rim of the distributor, and its median annular portion bears elastically on the upstream end. of the ring.
  • the three annular support areas of the sheet on the rim of the distributor and on the ring ensure a good seal between these elements, and thus prevent the passage of gas from the turbine duct outwards, in the annular space housing the rim of the ring and the crankcase rail, and the air leaks from this space inwards into the turbine duct.
  • the ring is in abutment at its upstream end on the middle part of the sheet, itself bearing on the rim of the distributor, which can result in a slight elastic deformation in bending of the sheet. This deformation is allowed by the axial space provided between the outer rim of the distributor and the sealing plate at the middle annular portion of this sheet.
  • This axial prestress is determined to make up the manufacturing tolerances of the various parts and, in operation, to maintain the three aforementioned supports, despite differential thermal expansions of the different parts.
  • the bending deformation of the sheet may therefore be more or less important during the different operating speeds of the turbine.
  • the sheet is fixed, by means of rivets for example, on the outer rim of the distributor.
  • the sheet is for example fixed by its inner periphery on a radially inner end portion of the outer rim of the distributor.
  • the sheet is substantially flat and is, in the mounting position, plated on the downstream face of the outer rim of the distributor, covering an annular groove of the downstream face.
  • the annular groove of the downstream face of the outer rim of the distributor makes it possible to define an axial annular space between the rim of the distributor and the median annular portion of the sheet, thus allowing the bending elastic deformation of the sheet.
  • This groove is sectorized as the distributor and can be substantially continuous 360 ° around the axis of the turbine and is closed by the sheet bearing on the outer rim of the distributor, radially inside and outside of this throat.
  • the annular plate is not flat, but curved with a concavity facing upstream. It comprises, for example, an annular portion having a U-shaped or V-shaped section whose opening is oriented upstream, this annular portion being in axial abutment against the upstream end of the ring and defining an annular space with the downstream face of the outer rim of the distributor.
  • the sealing plate is sectorized as the distributor and can extend over 360 ° around the axis of the turbine. It is preferably metallic.
  • the invention also relates to a turbomachine turbine, characterized in that it comprises at least one stage as described above.
  • the invention also relates to a turbomachine, such as an airplane turbojet or turboprop, characterized in that it comprises at least one turbine stage of the aforementioned type.
  • FIG. 1 represents a turbomachine low-pressure turbine 10 comprising four stages each comprising a distributor 12 formed of an annular row of fixed vanes 14 carried by an outer casing 16 of the turbine, and a wheel 18 located downstream of the distributor 12.
  • the wheels 18 comprise disks 20 assembled axially to each other by annular flanges 22 and carrying radial vanes 24. These wheels 18 are connected to a turbine shaft (not shown) via a drive cone 26 fixed on annular flanges 22 discs.
  • Each wheel 18 is surrounded externally with a small clearance by a ring 28 formed by sectors fixed circumferentially on the casing 16 of the turbine through locking members, as will be described in more detail in the following.
  • the distributors 12 comprise walls 30 of internal and external revolution 32, respectively, which delimit between them the annular flow vein of the gases in the turbine and between which radially extend the vanes 14.
  • the outer wall 32 of the distributor 16 of the upstream stage comprises radially outer annular rims upstream 34 and downstream 36 having axial annular tabs 38 hooking, oriented upstream and intended to be engaged in corresponding axial annular grooves 40 of the casing 16 of the turbine.
  • the vanes 14 of this distributor 12 comprise cooling air circulation channels 42 coming from a supply enclosure 44 (arrows 46) located radially outside the wall 32 of the distributor. This air is partly discharged in the vein of flow of the turbine gases through orifices (not shown) formed near the trailing edge of the vanes 14 and opening into their channels 42, and partly discharged into a chamber 52 located radially inside the wall 30 of the dispenser (arrows 54). The cooling air is taken upstream on a compressor of the turbomachine and brought into the supply chamber 44 by appropriate means.
  • the ring 28 located downstream of the distributor 12 of the upstream stage comprises at its upstream end an annular hook 56 which is applied to a corresponding cylindrical rail 58 of the casing 16, and which is held radially on this rail by an annular member 60 with a C-shaped or U-shaped section which is axially engaged from upstream on the hook 56 and the rail 5 ( figure 3 ).
  • the member 60, the hook 56 and the rail 58 are housed in an annular space 62 which extends around the ring 28 between the housing 16 and the distributor 12.
  • the member 60 bears at its upstream end on a downstream face 64 of the downstream annular rim 36 of the distributor.
  • the member 60, the housing rail 58 and the hook 56 of the ring are thermally protected by an annular plate 66 which is mounted between the upstream end of the ring 28 and the downstream face 64 of the annular flange 36 of the distributor. , to limit the passage of gas from the vein of the turbine radially outwards in the annular space 62.
  • the housing rail 58 and the hook 56 of the ring are in operation subjected to high temperatures which can cause the formation of cracks or fissures likely to destroy them.
  • ducts 68 and 70 are respectively formed in the outer wall 32 and in the outer rim 36 of the distributor, to connect the Channels 42 of the vanes to the annular space 62.
  • the ducts 68 formed in the outer wall 32 of the distributor communicate at one of their ends with a channel 42 of a blade and at the other of their ends with an annular passage 72 located radially outside the wall 32 of the distributor and defined axially by the outer annular flanges 34, 36 of the distributor.
  • the ducts 70 formed in the outer rim 36 of the distributor 12 are oblique with respect to the axis of the turbine and oriented downstream towards the outside. They open at their upstream ends in the annular passage 72, and at their downstream ends on the downstream face 64 of the outer rim 36 of the distributor.
  • annular plate 66 alone does not provide a sufficient seal between the distributor 12 and the ring 28, which results in leaks of the air injected into the annular space 62 radially inwards in the vein of the turbine.
  • the invention makes it possible to provide a simple solution to this problem by means of new sealing means.
  • the sealing means according to the invention comprise an annular plate 80 which extends radially between the outer rim 36 of the distributor and the upstream end of the ring 28 and which is axially prestressed by bearing on the upstream side, by its periphery. internal and its outer periphery, on the downstream face 64 of the flange 36 and by pressing the downstream side, at its median annular portion on the upstream end of the ring 28.
  • the annular sealing plate 80 is substantially flat and is fixed by rivets 82 on the outer flange 36 of the distributor.
  • the rivets are substantially parallel to the axis of the turbine and pass through orifices 84 formed in a radially inner end portion of the sheet 80 and corresponding orifices 86 formed in a radially inner end portion of the rim 36 of the distributor.
  • the sheet 80 completely covers an annular groove 88 of the downstream face 64 of the flange 36.
  • This groove 88 has a small axial depth, for example substantially equal to the thickness of the sheet, and has a radial dimension which is slightly smaller than that of the sheet. of the sheet 80. It is formed in the distributor areas over the entire angular extent of these sectors and can extend over 360 ° around the axis of the turbine.
  • the sheet is formed of angular sectors each fixed on a distributor sector and can extend over 360 ° around the axis of the turbine.
  • the inner periphery of the sheet 80 extends over a circumference located radially inside the groove 88 and this inner periphery bears axially against a radially inner portion of the downstream face 64 of the flange 36.
  • the outer periphery of the sheet extends over a circumference located radially outside the groove and this periphery bears axially on a radially outer portion of the downstream face 64 of the flange 36.
  • the orifices 84 and 86 for mounting the rivets 82 open at one of their ends into the annular groove 88 in the vicinity of its inner periphery, and are located radially inside the ring 28. upstream end of the ring 28 is in axial abutment on the sheet 80 in an area between the rivets and the outer periphery of the groove 88.
  • the sheet 80 is elastically prestressed by the ring which exerts a sufficient force in the axial direction upstream on the sheet so that it undergoes a slight elastic deformation in bending.
  • the axial prestressing of the sheet 80 is determined on the one hand to make up the manufacturing tolerances of the different parts, and to preserve the three annular sealing zones on the distributor flange and on the ring, despite the differential thermal expansions. parts in operation.
  • the deformation of the sheet 80 may therefore vary during an operating cycle of the turbomachine.
  • the three bearing zones provide a good seal between the turbine duct and the annular space 62 for housing the upstream flange 56 of the ring and the casing rail 58.
  • the ducts 70 of the figure 3 which provide the fluidic communication between the annular passage 72 and the annular space 62 are here replaced by axial holes 90 formed in the flange 36 of the distributor and axial grooves 92 formed in the annular tabs 38 of this flange.
  • the holes 90 open at their downstream ends radially outside the sheet 80.
  • the flange 36 of the dispenser may comprise ducts 70 similar to those of FIG. figure 3 these ducts opening at their ends downstream radially outside the sheet.
  • the plate 80 Before mounting the ring 28 on the turbine casing 16, the plate 80 can already be plated by means of the rivets on the downstream face 64 of the distributor flange. The ring 28 is then mounted on the housing rail 58 and abuts on the sheet 80 to preload axially.
  • the sheet 80 is held by the rivets and extends from upstream to downstream to the outside so that only its inner periphery is in contact with the downstream face of the flange 36 Fixing the ring on the casing then makes it possible to press the outer periphery of the sheet onto the external rim of the distributor.
  • the annular plate 80 ' is not flat but curved with a concavity oriented axially upstream.
  • the sheet 80 ' comprises in the vicinity of its outer periphery a curved annular portion V-shaped section or U whose opening is oriented upstream.
  • This sheet 80 ' is mounted in the same manner as the sheet 80 described above, and its curved portion delimits an annular space 94 with the downstream face 64 of the outer flange 36 of the distributor. It is therefore not necessary to provide an annular groove on this face 64, as is the case in the embodiment of the figure 3 .
  • the sealing plate 80, 80 ' is made of metal alloy, and has a relatively small thickness of about one to a few millimeters.
  • the sheet 80, 80 'according to the invention is associated in the example shown with a distributor whose outer rim 36 comprises means for fluid communication between the annular passage 72 and the annular space 62, this sheet could be associated to a distributor without such means.
  • the sheet could also be fixed on the distributor by other fastening means than the rivets 82. It could possibly be fixed on the upstream end of the ring 28.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Description

La présente invention concerne l'étanchéité d'un anneau de rotor dans un étage de turbine d'une turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion comme décrit dans EP 15 38 306 A .The present invention relates to the sealing of a rotor ring in a turbine stage of a turbomachine such as an airplane turbojet or turboprop engine as described in US Pat. EP 1538306A .

Typiquement, une turbine de turbomachine comprend au moins un étage comportant un distributeur formé d'une rangée annulaire d'aubes fixes et suivi d'une roue de rotor montée à l'intérieur d'un anneau sectorisé. Le distributeur comprend à son extrémité aval un rebord annulaire qui s'étend radialement vers l'extérieur et qui porte des moyens d'accrochage sur un carter de la turbine. L'anneau sectorisé situé en aval comprend un rebord cylindrique amont qui est maintenu radialement sur un rail du carter de turbine par l'intermédiaire d'un organe annulaire de verrouillage à section en forme de C ou de U engagé axialement sur le rail de carter et sur le rebord cylindrique de l'anneau.Typically, a turbomachine turbine comprises at least one stage comprising a distributor formed of an annular row of fixed vanes and followed by a rotor wheel mounted inside a sectorized ring. The distributor comprises at its downstream end an annular flange which extends radially outwards and which carries attachment means on a casing of the turbine. The downstream sectorized ring comprises an upstream cylindrical rim which is held radially on a rail of the turbine casing by means of an annular locking member with a C-shaped or U-shaped section axially engaged on the casing rail and on the cylindrical rim of the ring.

Le rebord cylindrique de l'anneau et le rail de carter sont en général protégés thermiquement par une tôle annulaire qui est montée entre le rebord externe du distributeur et l'extrémité amont de l'anneau pour limiter le passage de gaz depuis la veine de la turbine radialement vers l'extérieur dans l'espace annulaire de logement du rebord de l'anneau et du rail de carter.The cylindrical rim of the ring and the casing rail are generally thermally protected by an annular plate which is mounted between the outer rim of the distributor and the upstream end of the ring to limit the passage of gas from the vein of the ring. turbine radially outwardly in the annular housing space of the rim of the ring and crankcase rail.

Toutefois, l'étanchéité n'est pas parfaite et les fuites de gaz chauds venant de la veine de la turbine peuvent faire monter la température des crochets de carter et provoquer la formation de criques ou fissures susceptibles de détruire les crochets.However, the seal is not perfect and hot gas leaks from the vein of the turbine can increase the temperature of the crankcase hooks and cause the formation of cracks or cracks may destroy the hooks.

Par ailleurs, les aubes du distributeur comprennent en général des canaux d'écoulement d'air de refroidissement prélevé en amont sur le compresseur de la turbomachine.Moreover, the vanes of the distributor generally comprise cooling air flow channels taken upstream on the compressor of the turbomachine.

Il est connu de prélever une partie de l'air circulant dans les canaux de ces aubes et de réinjecter cet air dans l'espace annulaire de logement du rebord amont de l'anneau et du rail de carter pour réduire leur température. L'injection d'air dans cet espace permet également de maintenir cet espace à une pression supérieure à celle des gaz de combustion passant dans la turbine, ce qui limite l'introduction de ces gaz dans l'espace annulaire.It is known to take a portion of the air circulating in the channels of these vanes and reinject this air into the annular housing space of the upstream edge of the ring and the casing rail to reduce their temperature. The injection of air into this space also makes it possible to maintain this space at a pressure greater than that of the combustion gases passing through the turbine, which limits the introduction of these gases into the annular space.

Cependant, lorsque l'étanchéité entre le rebord externe du distributeur et l'extrémité amont de l'anneau n'est pas suffisante, l'air de refroidissement injecté dans l'espace annulaire de logement du rebord de l'anneau et du rail de carter, a tendance à passer radialement de l'extérieur vers l'intérieur dans la veine de turbine et ne participe donc pas au refroidissement du carter et de l'anneau.However, when the seal between the outer rim of the distributor and the upstream end of the ring is not sufficient, the cooling air injected into the annular housing space of the rim of the ring and the rail of casing, tends to pass radially from outside to inside in the turbine duct and therefore does not participate in the cooling of the housing and the ring.

L'invention a notamment pour but de répondre de manière simple, efficace et économique à ces problèmes de la technique antérieure.The object of the invention is in particular to provide a simple, effective and economical answer to these problems of the prior art.

Elle a pour objet un étage de turbine comportant des moyens d'étanchéité entre le distributeur et l'anneau sectorisé qui soient simples et efficaces pour empêcher le passage de gaz en direction radiale entre le rebord externe du distributeur et l'extrémité amont de l'anneau.It relates to a turbine stage comprising sealing means between the distributor and the ring sectorized which are simple and effective to prevent the passage of gas in a radial direction between the outer rim of the distributor and the upstream end of the ring.

Elle propose à cet effet un étage de turbine d'une turbomachine, comprenant une roue de rotor montée à l'intérieur d'un anneau sectorisé porté par un carter de turbine, un distributeur situé en amont de la roue et formé d'une rangée annulaire d'aubes fixes, ce distributeur comprenant à son extrémité aval un rebord annulaire externe comportant des moyens d'accrochage sur le carter de turbine, des moyens d'étanchéité étant prévus entre le rebord externe du distributeur et l'extrémité amont de l'anneau pour limiter le passage de gaz en direction radiale entre le rebord externe du distributeur et l'anneau, caractérisé en ce que les moyens d'étanchéité comprennent une tôle annulaire qui s'étend sensiblement radialement entre le rebord externe du distributeur et l'extrémité amont de l'anneau et qui comprend, à sa périphérie interne et à sa périphérie externe, des moyens d'appui axial contre une face aval du rebord externe du distributeur, la partie annulaire médiane de cette tôle étant espacée axialement du rebord externe du distributeur et étant en appui axial contre l'extrémité amont de l'anneau, la tôle étant précontrainte élastiquement en direction axiale par l'extrémité amont de l'anneau.It proposes for this purpose a turbine stage of a turbomachine, comprising a rotor wheel mounted inside a sectorized ring carried by a turbine casing, a distributor located upstream of the wheel and formed of a row. annular fixed vanes, this distributor comprising at its downstream end an outer annular flange having fastening means on the turbine housing, sealing means being provided between the outer rim of the distributor and the upstream end of the ring for limiting the passage of gas radially between the outer rim of the distributor and the ring, characterized in that the sealing means comprise an annular plate which extends substantially radially between the outer rim of the distributor and the end upstream of the ring and which comprises, at its inner periphery and at its outer periphery, axial support means against a downstream face of the external rim of the distributor, the annular part e median of this sheet being axially spaced from the outer rim of the distributor and being in axial bearing against the upstream end of the ring, the sheet being resiliently biased in the axial direction by the upstream end of the ring.

La tôle d'étanchéité selon l'invention est en appui axial en direction de l'amont, à sa périphérie interne et à sa périphérie externe, sur le rebord du distributeur, et sa partie annulaire médiane est en appui élastique sur l'extrémité amont de l'anneau. Les trois zones annulaires d'appui de la tôle sur le rebord du distributeur et sur l'anneau assurent une bonne étanchéité entre ces éléments, et empêchent donc le passage de gaz depuis la veine de turbine vers l'extérieur, dans l'espace annulaire de logement du rebord de l'anneau et du rail de carter, et les fuites d'air depuis cet espace vers l'intérieur, dans la veine de turbine.The sealing plate according to the invention bears axially in the direction of the upstream, at its inner periphery and at its outer periphery, on the rim of the distributor, and its median annular portion bears elastically on the upstream end. of the ring. The three annular support areas of the sheet on the rim of the distributor and on the ring ensure a good seal between these elements, and thus prevent the passage of gas from the turbine duct outwards, in the annular space housing the rim of the ring and the crankcase rail, and the air leaks from this space inwards into the turbine duct.

L'anneau est en butée à son extrémité amont sur la partie médiane de la tôle, elle-même en appui sur le rebord du distributeur, ce qui peut se traduire par une légère déformation élastique en flexion de la tôle. Cette déformation est autorisée par l'espace axial prévu entre le rebord externe du distributeur et la tôle d'étanchéité, au niveau de la partie annulaire médiane de cette tôle.The ring is in abutment at its upstream end on the middle part of the sheet, itself bearing on the rim of the distributor, which can result in a slight elastic deformation in bending of the sheet. This deformation is allowed by the axial space provided between the outer rim of the distributor and the sealing plate at the middle annular portion of this sheet.

Cette précontrainte axiale est déterminée pour rattraper les tolérances de fabrication des différentes pièces et pour, en fonctionnement, conserver les trois appuis précités, en dépit des dilatations thermiques différentielles des différentes pièces. La déformation en flexion de la tôle peut donc être plus ou moins importante pendant les différents régimes de fonctionnement de la turbine.This axial prestress is determined to make up the manufacturing tolerances of the various parts and, in operation, to maintain the three aforementioned supports, despite differential thermal expansions of the different parts. The bending deformation of the sheet may therefore be more or less important during the different operating speeds of the turbine.

Préférentiellement, la tôle est fixée, par l'intermédiaire de rivets par exemple, sur le rebord externe du distributeur. La tôle est par exemple fixée par sa périphérie interne sur une partie d'extrémité radialement interne du rebord externe du distributeur.Preferably, the sheet is fixed, by means of rivets for example, on the outer rim of the distributor. The sheet is for example fixed by its inner periphery on a radially inner end portion of the outer rim of the distributor.

Dans un mode de réalisation de l'invention, la tôle est sensiblement plane et est, en position de montage, plaquée sur la face aval du rebord externe du distributeur, en recouvrant une gorge annulaire de cette face aval.In one embodiment of the invention, the sheet is substantially flat and is, in the mounting position, plated on the downstream face of the outer rim of the distributor, covering an annular groove of the downstream face.

La gorge annulaire de la face aval du rebord externe du distributeur permet de définir un espace annulaire axial entre le rebord du distributeur et la partie annulaire médiane de la tôle, autorisant ainsi la déformation élastique en flexion de la tôle. Cette gorge est sectorisée comme le distributeur et peut être sensiblement continue sur 360° autour de l'axe de la turbine et elle est obturée par la tôle prenant appui sur le rebord externe du distributeur, radialement à l'intérieur et à l'extérieur de cette gorge.The annular groove of the downstream face of the outer rim of the distributor makes it possible to define an axial annular space between the rim of the distributor and the median annular portion of the sheet, thus allowing the bending elastic deformation of the sheet. This groove is sectorized as the distributor and can be substantially continuous 360 ° around the axis of the turbine and is closed by the sheet bearing on the outer rim of the distributor, radially inside and outside of this throat.

Selon un autre mode de réalisation de l'invention, la tôle annulaire n'est pas plane, mais incurvée avec une concavité tournée vers l'amont. Elle comprend par exemple une partie annulaire ayant en section une forme en U ou en V dont l'ouverture est orientée vers l'amont, cette partie annulaire étant en appui axial contre l'extrémité amont de l'anneau et définissant un espace annulaire avec la face aval du rebord externe du distributeur.According to another embodiment of the invention, the annular plate is not flat, but curved with a concavity facing upstream. It comprises, for example, an annular portion having a U-shaped or V-shaped section whose opening is oriented upstream, this annular portion being in axial abutment against the upstream end of the ring and defining an annular space with the downstream face of the outer rim of the distributor.

La tôle d'étanchéité est sectorisée comme le distributeur et peut s'étendre sur 360° autour de l'axe de la turbine. Elle est de préférence métallique.The sealing plate is sectorized as the distributor and can extend over 360 ° around the axis of the turbine. It is preferably metallic.

L'invention concerne également une turbine de turbomachine, caractérisée en ce qu'elle comprend au moins un étage tel que décrit ci-dessus.The invention also relates to a turbomachine turbine, characterized in that it comprises at least one stage as described above.

L'invention concerne encore une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend au moins un étage de turbine du type précité.The invention also relates to a turbomachine, such as an airplane turbojet or turboprop, characterized in that it comprises at least one turbine stage of the aforementioned type.

L'invention sera mieux comprise et d'autres caractéristiques, détails et avantages de celle-ci apparaîtront plus clairement à la lecture de la description qui suit, faite à titre d'exemple non limitatif en référence aux dessins annexés dans lesquels :

  • la figure 1 est une demi-vue schématique partielle en coupe axiale d'une turbine de turbomachine ;
  • la figure 2 est une vue à plus grande échelle d'une partie de la figure 1, et représente un étage de turbine selon la technique antérieure ;
  • la figure 3 est une vue agrandie du détail I3 de la figure 2 ;
  • la figure 4 est une vue schématique partielle en coupe axiale d'un étage de turbine selon l'invention ;
  • la figure 5 est une vue correspondant à la figure 4 et représentant une variante de réalisation de l'invention.
The invention will be better understood and other characteristics, details and advantages thereof will appear more clearly on reading the description which follows, given by way of non-limiting example with reference to the accompanying drawings in which:
  • the figure 1 is a partial schematic half-view in axial section of a turbomachine turbine;
  • the figure 2 is a larger-scale view of some of the figure 1 , and represents a turbine stage according to the prior art;
  • the figure 3 is an enlarged view of detail I 3 of the figure 2 ;
  • the figure 4 is a partial schematic view in axial section of a turbine stage according to the invention;
  • the figure 5 is a view corresponding to the figure 4 and representing an alternative embodiment of the invention.

On se réfère d'abord à la figure 1 qui représente une turbine basse-pression 10 de turbomachine comprenant quatre étages comportant chacun un distributeur 12 formé d'une rangée annulaire d'aubes fixes 14 portées par un carter externe 16 de la turbine, et une roue 18 située en aval du distributeur 12.We first refer to the figure 1 which represents a turbomachine low-pressure turbine 10 comprising four stages each comprising a distributor 12 formed of an annular row of fixed vanes 14 carried by an outer casing 16 of the turbine, and a wheel 18 located downstream of the distributor 12.

Les roues 18 comprennent des disques 20 assemblés axialement les uns aux autres par des brides annulaires 22 et portant des aubes radiales 24. Ces roues 18 sont reliées à un arbre de turbine (non représenté) par l'intermédiaire d'un cône d'entraînement 26 fixé sur des brides annulaires 22 des disques.The wheels 18 comprise disks 20 assembled axially to each other by annular flanges 22 and carrying radial vanes 24. These wheels 18 are connected to a turbine shaft (not shown) via a drive cone 26 fixed on annular flanges 22 discs.

Chaque roue 18 est entourée extérieurement avec un faible jeu par un anneau 28 formé par des secteurs fixés circonférentiellement sur le carter 16 de la turbine par l'intermédiaire d'organes de verrouillage, comme cela sera décrit plus en détail dans ce qui suit.Each wheel 18 is surrounded externally with a small clearance by a ring 28 formed by sectors fixed circumferentially on the casing 16 of the turbine through locking members, as will be described in more detail in the following.

Les distributeurs 12 comprennent des parois de révolution interne 30 et externe 32, respectivement, qui délimitent entre elles la veine annulaire d'écoulement des gaz dans la turbine et entre lesquelles s'étendent radialement les aubes 14.The distributors 12 comprise walls 30 of internal and external revolution 32, respectively, which delimit between them the annular flow vein of the gases in the turbine and between which radially extend the vanes 14.

La paroi externe 32 du distributeur 16 de l'étage amont, mieux visible en figure 2, comprend des rebords annulaires radialement externes amont 34 et aval 36 comportant des pattes annulaires axiales 38 d'accrochage, orientées vers l'amont et destinées à être engagées dans des gorges annulaires axiales 40 correspondantes du carter 16 de la turbine.The outer wall 32 of the distributor 16 of the upstream stage, better visible in figure 2 , comprises radially outer annular rims upstream 34 and downstream 36 having axial annular tabs 38 hooking, oriented upstream and intended to be engaged in corresponding axial annular grooves 40 of the casing 16 of the turbine.

Les aubes 14 de ce distributeur 12 comprennent des canaux 42 de circulation d'air de refroidissement provenant d'une enceinte d'alimentation 44 (flèches 46), située radialement à l'extérieur de la paroi 32 du distributeur. Cet air est en partie évacué dans la veine d'écoulement des gaz de la turbine par des orifices (non représentés) formés à proximité du bord de fuite des aubes 14 et débouchant dans leurs canaux 42, et en partie évacué dans une enceinte 52 situé radialement à l'intérieur de la paroi 30 du distributeur (flèches 54). L'air de refroidissement est prélevé en amont sur un compresseur de la turbomachine et amené dans l'enceinte d'alimentation 44 par des moyens appropriés.The vanes 14 of this distributor 12 comprise cooling air circulation channels 42 coming from a supply enclosure 44 (arrows 46) located radially outside the wall 32 of the distributor. This air is partly discharged in the vein of flow of the turbine gases through orifices (not shown) formed near the trailing edge of the vanes 14 and opening into their channels 42, and partly discharged into a chamber 52 located radially inside the wall 30 of the dispenser (arrows 54). The cooling air is taken upstream on a compressor of the turbomachine and brought into the supply chamber 44 by appropriate means.

L'anneau 28 situé en aval du distributeur 12 de l'étage amont comprend à son extrémité amont un crochet annulaire 56 qui est appliqué sur un rail cylindrique 58 correspondant du carter 16, et qui est maintenu radialement sur ce rail par un organe annulaire 60 de verrouillage à section en forme de C ou de U qui est engagé axialement depuis l'amont sur le crochet 56 et le rail 5 (figure 3).The ring 28 located downstream of the distributor 12 of the upstream stage comprises at its upstream end an annular hook 56 which is applied to a corresponding cylindrical rail 58 of the casing 16, and which is held radially on this rail by an annular member 60 with a C-shaped or U-shaped section which is axially engaged from upstream on the hook 56 and the rail 5 ( figure 3 ).

L'organe 60, le crochet 56 et le rail 58 sont logés dans un espace annulaire 62 qui s'étend autour de l'anneau 28 entre le carter 16 et le distributeur 12. L'organe 60 prend appui à son extrémité amont sur une face aval 64 du rebord annulaire aval 36 du distributeur.The member 60, the hook 56 and the rail 58 are housed in an annular space 62 which extends around the ring 28 between the housing 16 and the distributor 12. The member 60 bears at its upstream end on a downstream face 64 of the downstream annular rim 36 of the distributor.

L'organe 60, le rail de carter 58 et le crochet 56 de l'anneau sont protégés thermiquement par une tôle annulaire 66 qui est montée entre l'extrémité amont de l'anneau 28 et la face aval 64 du rebord annulaire 36 du distributeur, pour limiter le passage de gaz depuis la veine de la turbine radialement vers l'extérieur dans l'espace annulaire 62.The member 60, the housing rail 58 and the hook 56 of the ring are thermally protected by an annular plate 66 which is mounted between the upstream end of the ring 28 and the downstream face 64 of the annular flange 36 of the distributor. , to limit the passage of gas from the vein of the turbine radially outwards in the annular space 62.

Le rail de carter 58 et le crochet 56 de l'anneau sont en fonctionnement soumis à des températures importantes qui peuvent provoquer la formation de criques ou fissures susceptibles de les détruire.The housing rail 58 and the hook 56 of the ring are in operation subjected to high temperatures which can cause the formation of cracks or fissures likely to destroy them.

Pour remédier à ces problèmes, on a déjà proposé de prélever une partie de l'air relativement frais circulant dans les canaux 42 des aubes du distributeur, et d'amener cet air dans l'espace annulaire 62 pour réduire la température à l'intérieur de cet espace.To remedy these problems, it has already been proposed to take a portion of the relatively cool air circulating in the channels 42 of the vanes of the distributor, and to bring this air into the annular space 62 to reduce the temperature inside. of this space.

Pour cela, des conduits 68 et 70 sont formés respectivement dans la paroi externe 32 et dans le rebord externe 36 du distributeur, pour relier les canaux 42 des aubes à l'espace annulaire 62. Les conduits 68 formés dans la paroi externe 32 du distributeur communiquent à une de leurs extrémités avec un canal 42 d'une aube et à l'autre de leurs extrémités avec un passage annulaire 72 situé radialement à l'extérieur de la paroi 32 du distributeur et délimité axialement par les rebords annulaires externes 34, 36 du distributeur. Les conduits 70 formés dans le rebord externe 36 du distributeur 12 sont obliques par rapport à l'axe de la turbine et orientés en aval vers l'extérieur. Ils débouchent à leurs extrémités amont dans le passage annulaire 72, et à leurs extrémités aval sur la face aval 64 du rebord externe 36 du distributeur.For this, ducts 68 and 70 are respectively formed in the outer wall 32 and in the outer rim 36 of the distributor, to connect the Channels 42 of the vanes to the annular space 62. The ducts 68 formed in the outer wall 32 of the distributor communicate at one of their ends with a channel 42 of a blade and at the other of their ends with an annular passage 72 located radially outside the wall 32 of the distributor and defined axially by the outer annular flanges 34, 36 of the distributor. The ducts 70 formed in the outer rim 36 of the distributor 12 are oblique with respect to the axis of the turbine and oriented downstream towards the outside. They open at their upstream ends in the annular passage 72, and at their downstream ends on the downstream face 64 of the outer rim 36 of the distributor.

Cependant, la tôle annulaire 66 n'assure pas à elle seule une étanchéité suffisante entre le distributeur 12 et l'anneau 28, ce qui se traduit par des fuites de l'air injecté dans l'espace annulaire 62 radialement vers l'intérieur dans la veine de la turbine.However, the annular plate 66 alone does not provide a sufficient seal between the distributor 12 and the ring 28, which results in leaks of the air injected into the annular space 62 radially inwards in the vein of the turbine.

L'invention permet d'apporter une solution simple à ce problème grâce à des nouveaux moyens d'étanchéité.The invention makes it possible to provide a simple solution to this problem by means of new sealing means.

Les moyens d'étanchéité selon l'invention comprennent une tôle annulaire 80 qui s'étend radialement entre le rebord externe 36 du distributeur et l'extrémité amont de l'anneau 28 et qui est précontrainte axialement par appui du côté amont, par sa périphérie interne et sa périphérie externe, sur la face aval 64 du rebord 36 et par appui du côté aval, au niveau de sa partie annulaire médiane sur l'extrémité amont de l'anneau 28.The sealing means according to the invention comprise an annular plate 80 which extends radially between the outer rim 36 of the distributor and the upstream end of the ring 28 and which is axially prestressed by bearing on the upstream side, by its periphery. internal and its outer periphery, on the downstream face 64 of the flange 36 and by pressing the downstream side, at its median annular portion on the upstream end of the ring 28.

Dans l'exemple représenté en figure 4, la tôle annulaire 80 d'étanchéité est sensiblement plane et est fixée par des rivets 82 sur le rebord externe 36 du distributeur. Les rivets sont sensiblement parallèles à l'axe de la turbine et passent à travers des orifices 84 formés dans une partie d'extrémité radialement interne de la tôle 80 et des orifices 86 correspondants formés dans une partie d'extrémité radialement interne du rebord 36 du distributeur.In the example shown in figure 4 , the annular sealing plate 80 is substantially flat and is fixed by rivets 82 on the outer flange 36 of the distributor. The rivets are substantially parallel to the axis of the turbine and pass through orifices 84 formed in a radially inner end portion of the sheet 80 and corresponding orifices 86 formed in a radially inner end portion of the rim 36 of the distributor.

La tôle 80 recouvre complètement une gorge annulaire 88 de la face aval 64 du rebord 36. Cette gorge 88 a une faible profondeur axiale, par exemple sensiblement égale à l'épaisseur de la tôle, et a une dimension radiale qui est légèrement inférieure à celle de la tôle 80. Elle est formée dans les secteurs de distributeur sur toute l'étendue angulaire de ces secteurs et peut s'étendre sur 360° autour de l'axe de la turbine. La tôle est formée de secteurs angulaires fixés chacun sur un secteur de distributeur et peut s'étendre sur 360° autour de l'axe de la turbine.The sheet 80 completely covers an annular groove 88 of the downstream face 64 of the flange 36. This groove 88 has a small axial depth, for example substantially equal to the thickness of the sheet, and has a radial dimension which is slightly smaller than that of the sheet. of the sheet 80. It is formed in the distributor areas over the entire angular extent of these sectors and can extend over 360 ° around the axis of the turbine. The sheet is formed of angular sectors each fixed on a distributor sector and can extend over 360 ° around the axis of the turbine.

La périphérie interne de la tôle 80 s'étend sur une circonférence située radialement à l'intérieur de la gorge 88 et cette périphérie interne est en appui axial sur une partie radialement interne de la face aval 64 du rebord 36. La périphérie externe de la tôle s'étend sur une circonférence située radialement à l'extérieur de la gorge et cette périphérie est en appui axial sur une partie radialement externe de la face aval 64 du rebord 36.The inner periphery of the sheet 80 extends over a circumference located radially inside the groove 88 and this inner periphery bears axially against a radially inner portion of the downstream face 64 of the flange 36. The outer periphery of the sheet extends over a circumference located radially outside the groove and this periphery bears axially on a radially outer portion of the downstream face 64 of the flange 36.

Dans l'exemple représenté, les orifices 84 et 86 de montage des rivets 82 débouchent à une de leurs extrémités dans la gorge annulaire 88 au voisinage de sa périphérie interne, et sont situés radialement à l'intérieur de l'anneau 28. L'extrémité amont de l'anneau 28 est en butée axiale sur la tôle 80 dans une zone située entre les rivets et la périphérie externe de la gorge 88.In the example shown, the orifices 84 and 86 for mounting the rivets 82 open at one of their ends into the annular groove 88 in the vicinity of its inner periphery, and are located radially inside the ring 28. upstream end of the ring 28 is in axial abutment on the sheet 80 in an area between the rivets and the outer periphery of the groove 88.

Dans la position de montage, la tôle 80 est précontrainte élastiquement par l'anneau qui exerce une force suffisante en direction axiale vers l'amont sur la tôle pour que celle-ci subisse une légère déformation élastique en flexion. La précontrainte axiale de la tôle 80 est déterminée d'une part pour rattraper les tolérances de fabrication des différentes pièces, et pour conserver les trois zones annulaires d'appui étanche sur le rebord de distributeur et sur l'anneau, malgré les dilatations thermiques différentielles des pièces en fonctionnement. La déformation de la tôle 80 peut donc varier lors d'un cycle de fonctionnement de la turbomachine.In the mounting position, the sheet 80 is elastically prestressed by the ring which exerts a sufficient force in the axial direction upstream on the sheet so that it undergoes a slight elastic deformation in bending. The axial prestressing of the sheet 80 is determined on the one hand to make up the manufacturing tolerances of the different parts, and to preserve the three annular sealing zones on the distributor flange and on the ring, despite the differential thermal expansions. parts in operation. The deformation of the sheet 80 may therefore vary during an operating cycle of the turbomachine.

Les trois zones d'appui assurent une bonne étanchéité entre la veine de la turbine et l'espace annulaire 62 de logement du rebord amont 56 de l'anneau et du rail de carter 58. Les appuis en C1, entre la périphérie interne de la tôle 80 et le rebord 36 du distributeur, en C2, entre la tôle et l'extrémité amont de l'anneau 28, et en C3, entre la périphérie externe de la tôle 80 et le rebord 36 du distributeur, empêchent le passage de gaz depuis la veine de la turbine vers l'extérieur dans l'espace annulaire 62, et les fuites d'air depuis l'espace 62 vers l'intérieur dans la veine de turbine.The three bearing zones provide a good seal between the turbine duct and the annular space 62 for housing the upstream flange 56 of the ring and the casing rail 58. The supports C1, between the inner periphery of the sheet 80 and the flange 36 of the distributor, C2, between the sheet and the upstream end of the ring 28, and C3, between the outer periphery of the sheet 80 and the flange 36 of the distributor, prevent the passage of gas from the vein of the turbine to the outside in the annular space 62, and air leakage from the space 62 inward into the turbine duct.

Les conduits 70 de la figure 3 qui assurent la communication fluidique entre le passage annulaire 72 et l'espace annulaire 62 sont ici remplacés par des perçages axiaux 90 formés dans le rebord 36 du distributeur et des rainures axiales 92 formées dans les pattes annulaires 38 de ce rebord. Les perçages 90 débouchent à leurs extrémités aval radialement à l'extérieur de la tôle 80. En variante, le rebord 36 du distributeur peut comprendre des conduits 70 similaires à ceux de la figure 3, ces conduits débouchant à leurs extrémités aval radialement à l'extérieur de la tôle.The ducts 70 of the figure 3 which provide the fluidic communication between the annular passage 72 and the annular space 62 are here replaced by axial holes 90 formed in the flange 36 of the distributor and axial grooves 92 formed in the annular tabs 38 of this flange. The holes 90 open at their downstream ends radially outside the sheet 80. In a variant, the flange 36 of the dispenser may comprise ducts 70 similar to those of FIG. figure 3 these ducts opening at their ends downstream radially outside the sheet.

Avant le montage de l'anneau 28 sur le carter de turbine 16, la tôle 80 peut déjà être plaquée au moyen des rivets sur la face aval 64 du rebord de distributeur. L'anneau 28 est alors monté sur le rail de carter 58 et vient buter sur la tôle 80 pour la précontraindre axialement.Before mounting the ring 28 on the turbine casing 16, the plate 80 can already be plated by means of the rivets on the downstream face 64 of the distributor flange. The ring 28 is then mounted on the housing rail 58 and abuts on the sheet 80 to preload axially.

En variante, avant le montage de l'anneau 28, la tôle 80 est maintenue par les rivets et s'étend d'amont en aval vers l'extérieur de sorte que seule sa périphérie interne soit en contact avec la face aval du rebord 36. La fixation de l'anneau sur le carter permet alors de plaquer la périphérie externe de la tôle sur le rebord externe du distributeur.Alternatively, before mounting the ring 28, the sheet 80 is held by the rivets and extends from upstream to downstream to the outside so that only its inner periphery is in contact with the downstream face of the flange 36 Fixing the ring on the casing then makes it possible to press the outer periphery of the sheet onto the external rim of the distributor.

Dans encore une autre variante représentée en figure 5, la tôle annulaire 80' n'est pas plane mais incurvée avec une concavité orientée axialement vers l'amont. Dans l'exemple représenté, la tôle 80' comprend au voisinage de sa périphérie externe une partie annulaire incurvée à section en forme de V ou de U dont l'ouverture est orientée vers l'amont. Cette tôle 80' est montée de la même manière que la tôle 80 décrit précédemment, et sa partie incurvée délimite un espace annulaire 94 avec la face aval 64 du rebord externe 36 du distributeur. Il n'est donc pas nécessaire de prévoir une gorge annulaire sur cette face 64, comme c'est le cas dans le mode de réalisation de la figure 3. La partie incurvée de la tôle 80' est en appui contre l'extrémité amont de l'anneau (en C3), cet anneau exerçant une force suffisante en direction axiale vers l'amont sur la tôle 80' pour que celle-ci subisse une légère déformation élastique en flexion, comme cela a été décrit en référence à la figure 3.In yet another variant represented in figure 5 , the annular plate 80 'is not flat but curved with a concavity oriented axially upstream. In the example shown, the sheet 80 'comprises in the vicinity of its outer periphery a curved annular portion V-shaped section or U whose opening is oriented upstream. This sheet 80 'is mounted in the same manner as the sheet 80 described above, and its curved portion delimits an annular space 94 with the downstream face 64 of the outer flange 36 of the distributor. It is therefore not necessary to provide an annular groove on this face 64, as is the case in the embodiment of the figure 3 . The curved portion of the sheet 80 'bears against the upstream end of the ring (at C3), this ring exerting a sufficient force in the axial direction upstream on the sheet 80' so that it undergoes a slight elastic deformation in flexion, as described with reference to figure 3 .

La tôle d'étanchéité 80, 80' est réalisée en alliage métallique, et a une épaisseur relativement faible de l'ordre de un à quelques millimètres environ.The sealing plate 80, 80 'is made of metal alloy, and has a relatively small thickness of about one to a few millimeters.

Bien que la tôle 80, 80' selon l'invention soit associée dans l'exemple représenté à un distributeur dont le rebord externe 36 comprend des moyens de communication fluidique entre le passage annulaire 72 et l'espace annulaire 62, cette tôle pourrait être associée à un distributeur dépourvu de tels moyens. La tôle pourrait en outre être fixée sur le distributeur par d'autres moyens de fixation que les rivets 82. Elle pourrait éventuellement être fixée sur l'extrémité amont de l'anneau 28.Although the sheet 80, 80 'according to the invention is associated in the example shown with a distributor whose outer rim 36 comprises means for fluid communication between the annular passage 72 and the annular space 62, this sheet could be associated to a distributor without such means. The sheet could also be fixed on the distributor by other fastening means than the rivets 82. It could possibly be fixed on the upstream end of the ring 28.

Claims (8)

  1. A turbine stage of a turbomachine, the stage comprising a rotor wheel (18) mounted inside a sectorized ring (28) carried by a turbine casing (16), and a nozzle (12) situated upstream from the wheel and made up of an annular row of stator vanes (14), the nozzle including at its downstream end an outer annular rim (36) having fastener means (38) for fastening to the turbine casing, sealing means being provided between the outer rim of the nozzle and the upstream end of the ring to limit the passage of gas in a radial direction between the outer rim of the nozzle and the ring, the stage being characterized in that the sealing means comprise an annular sheet (80, 80') extending substantially radially between the outer rim of the nozzle and the upstream end of the ring, and comprising at its inner periphery and at its outer periphery means for bearing axially against a downstream face (64) of the outer rim of the nozzle, the middle annular portion of said sheet being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring, the sheet being elastically prestressed in the axial direction by the upstream end of the ring.
  2. A turbine stage according to claim 1, characterized in that the sheet (80, 80') is fastened to the outer rim (36) of the nozzle, e.g. by means of rivets (82).
  3. A turbine stage according to claim 1, characterized in that the sheet (80, 80') is fastened via its inner periphery to a radially inner end portion of the outer rim (36) of the nozzle.
  4. A turbine stage according to claim 1, characterized in that the sheet (80) is substantially plane and, in the assembled position, is pressed against the downstream face (64) of the outer rim (36) of the nozzle, covering an annular groove (88) in the downstream face (64) of the outer rim (36).
  5. A turbine stage according to claim 1, characterized in that the sheet (80') comprises an annular portion of U-shaped or V-shaped section with its opening facing upstream, said annular portion bearing axially against the upstream end of the ring and co-operating with the downstream face (64) of the outer rim (36) of the nozzle to define an annular space (49).
  6. A turbine stage according to claim 1, characterized in that the sealing sheet (80, 80') is made up of sheet sectors, each fastened to a nozzle sector.
  7. A turbine stage according to claim 1, characterized in that the sheet (80, 80') is made of metal.
  8. A turbomachine such as an airplane turbojet or turboprop, characterized in that it includes at least one turbine stage according to claim 1.
EP08163591A 2007-11-13 2008-09-03 Sealing of a stator guide vane ring in a turbine stage Active EP2060743B1 (en)

Applications Claiming Priority (1)

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FR0707942A FR2923525B1 (en) 2007-11-13 2007-11-13 SEALING A ROTOR RING IN A TURBINE FLOOR

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EP2060743A1 EP2060743A1 (en) 2009-05-20
EP2060743B1 true EP2060743B1 (en) 2010-12-22

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EP (1) EP2060743B1 (en)
JP (1) JP5210804B2 (en)
CN (1) CN101435346B (en)
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DE (1) DE602008004061D1 (en)
ES (1) ES2356701T3 (en)
FR (1) FR2923525B1 (en)
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FR2923525A1 (en) 2009-05-15
FR2923525B1 (en) 2009-12-18
CN101435346A (en) 2009-05-20
JP2009121461A (en) 2009-06-04
CA2644309C (en) 2015-12-29
RU2008144750A (en) 2010-05-20
JP5210804B2 (en) 2013-06-12
CA2644309A1 (en) 2009-05-13
EP2060743A1 (en) 2009-05-20
US20090129917A1 (en) 2009-05-21
CN101435346B (en) 2013-01-23
ES2356701T3 (en) 2011-04-12
US8100644B2 (en) 2012-01-24
DE602008004061D1 (en) 2011-02-03
RU2476710C2 (en) 2013-02-27

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