EP1965034A1 - Turbine stage in a turbomachine - Google Patents

Turbine stage in a turbomachine Download PDF

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Publication number
EP1965034A1
EP1965034A1 EP08151521A EP08151521A EP1965034A1 EP 1965034 A1 EP1965034 A1 EP 1965034A1 EP 08151521 A EP08151521 A EP 08151521A EP 08151521 A EP08151521 A EP 08151521A EP 1965034 A1 EP1965034 A1 EP 1965034A1
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EP
European Patent Office
Prior art keywords
turbine
annular
stage according
turbine stage
ring sectors
Prior art date
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Granted
Application number
EP08151521A
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German (de)
French (fr)
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EP1965034B1 (en
Inventor
Mathieu Dakowski
Claire Dorin
Alain Dominique Gendraud
Vincent Philippot
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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 a turbine stage in a turbomachine such as in particular an airplane turbojet or turboprop.
  • a turbomachine comprises a plurality of turbine stages each comprising a distributor formed of an annular row of stationary vanes and a rotor wheel rotatably mounted downstream of the distributor in a cylindrical or frustoconical envelope formed by ring sectors arranged circumferentially at the end.
  • the first of these stages is a high-pressure stage and the other stages downstream are low-pressure stages.
  • the ring sectors that surround the impeller of the high-pressure stage comprise at their upstream and downstream ends hooking means cooperating with corresponding means provided on an annular support disposed between the ring sectors and the casing. of turbine.
  • the hot gases leaving the combustion chamber of the turbomachine flow through the distributor of the high-pressure stage and exert on it an axial thrust downstream.
  • This distributor tends to move downstream and come to bear by its outer periphery on the annular support of the ring sectors and to push downstream, resulting variations of the radial clearances between the blades. of the wheel and ring sectors.
  • the invention aims in particular to provide a simple, effective and economical solution to all the problems of the prior art.
  • a turbine stage in a turbomachine comprising ring sectors arranged around a turbine wheel and suspended from a turbine casing by an annular support, characterized in that the annular support comprises means for attaching the ring sectors and fastening means on the turbine casing, connected by two coaxial annular walls connected to one another and extending one to the inside of the other, this support section having a V-shaped or U-shaped and being elastically deformable in the radial direction to absorb at least part of the deformations of the turbine casing in operation.
  • the ring sectors are suspended from the turbine casing by a radially deformable annular support so as to at least partially absorb the carcass distortions of the outer casing so that the casing formed by the ring sectors keeps a substantially constant diameter in operation.
  • the invention makes it possible to maintain a substantially constant radial clearance between the wheel and the ring sectors of the high-pressure stage, as well as at the leading and trailing edges of the blades of this wheel.
  • the annular support has moreover a good axial rigidity so that it can withstand without deformation in the axial support of the upstream side of the distributor of the high-pressure stage subjected to the thrust of the combustion gases.
  • the elastically deformable support comprises two coaxial annular walls connected to one another at one end and extending one inside the other, this support having a V-shaped or U-shaped section with a cross-section. oriented upstream or downstream.
  • the two coaxial walls of the support can move toward or away from one another to damp the carcass distortions of the turbine casing.
  • the junction between the two walls is shaped to deform elastically and provide the support a spring function.
  • This double wall structure also makes it possible to reinforce the axial rigidity of the support of the ring sectors.
  • the annular support has a V-shaped cross-section and has two frustoconical walls respectively internal and external.
  • the frustoconical wall For example, the internal portion may extend from hooking means of the ring sectors radially outwards and upstream to the outer frustoconical wall which extends radially outwards and downstream.
  • the support defines an annular groove which opens axially downstream.
  • the annular support has a U-shaped cross-section and comprises two substantially cylindrical walls, respectively internal and external.
  • the inner cylindrical wall may be connected at its upstream end to hooking means of the ring sectors and at its downstream end to the downstream end of the outer cylindrical wall.
  • the support here defines an annular groove oriented axially upstream.
  • the outer wall comprises a radially outer annular flange for attachment to the turbine casing.
  • the inner wall is connected to an upstream end of the hooking means of the ring sectors so as to reinforce the axial rigidity of the support.
  • the junction between the inner and outer walls may have a C-shaped curved shape defining a concave annular surface and a convex annular surface.
  • This junction advantageously comprises an annular rib extending substantially axially from its convex annular surface to stiffen the junction area of the two walls and distribute the stresses in this area.
  • This annular rib has for example a cylindrical shape centered on the axis of revolution of the support.
  • the present invention also relates to a turbomachine turbine and a turbomachine, such as an airplane turbojet or turboprop, comprising at least one stage as described above.
  • the invention also relates to an annular support of ring sectors in a turbine stage of a turbomachine, characterized in that it has a U or V section and comprises at its inner periphery hooking means of the ring sectors, and at its outer periphery a radially outer annular flange.
  • the figure 1 schematically represents a part of a turbomachine such as an airplane turbojet or turboprop comprising a turbine 10, 12 arranged downstream of a combustion chamber 14, this turbine comprising several stages: an upstream stage or high stage 10 and downstream stages or low-pressure stages 12.
  • a turbomachine such as an airplane turbojet or turboprop comprising a turbine 10, 12 arranged downstream of a combustion chamber 14, this turbine comprising several stages: an upstream stage or high stage 10 and downstream stages or low-pressure stages 12.
  • the high-pressure stage 10 comprises a distributor 16 formed of an annular row of fixed vanes, and a vane wheel 18 mounted downstream of the distributor 16 and rotating in a substantially cylindrical casing formed by ring sectors. 20 arranged circumferentially end to end and suspended from a turbine casing 22.
  • Each low-pressure stage 12 also comprises a distributor and a paddle wheel of the aforementioned type, only the distributor 30 of the first low-pressure stage being visible in FIG. figure 1 .
  • This distributor 30 is fixed to the turbine casing 22 by means of an annular support piece 32 arranged between the distributor 30 and the casing 22.
  • the support piece 32 comprises at its radially inner end annular grooves which open towards the outside. downstream and in which are engaged circumferential edges 34 provided at the outer periphery of the distributor.
  • the part 32 comprises a frustoconical wall 36 which extends radially outwards and upstream and is connected at its radially outer end to a radially outer annular flange 38 for attachment to a corresponding annular flange 24 provided at the end. upstream of the turbine casing 22.
  • An outer casing 28 surrounding the combustion chamber 14 is also provided at its downstream end with a radially outer annular flange 26 which is held axially tight on the flanges 38 and 24 of the support piece 32 and the turbine casing 22 by the intermediate means 40 of the screw-nut type.
  • the combustion chamber 14 is fixed to the outer casing 28 via an annular wall 29 extending from the downstream end of the chamber radially outwardly and downstream and comprising at its radially outer end fastening means to the outer casing 28.
  • the ring sectors 20 are suspended from the turbine casing 22 by means of an annular support 50 which is housed in an annular enclosure 52 delimited upstream by the annular wall 29 of the combustion chamber 14 and at the same time. downstream by the frustoconical wall 36 of the support piece 32.
  • This annular support comprises at its inner periphery means 54 for hooking the ring sectors 20 and at its outer periphery means 72 for fixing on the turbine casing 22 .
  • this annular support 50 is elastically deformable in the radial direction to at least partially damp the carcass distortions to which the turbine casing 22 is subjected in operation of the turbomachine, so that the cylindrical envelope formed by the sectors of ring 20 retains a substantially constant diameter.
  • the annular support 50 comprises at its inner periphery two radial annular walls 57, 58, respectively upstream and downstream, which are connected to one another by a cylindrical wall 60.
  • the radial walls 57, 58 comprise at their radially internal ends downstream cylindrical flanges 62 which cooperate with hooks circumferential members 63, 64 provided at the upstream and downstream ends of the ring sectors 20.
  • An annular locking member 66 with a C-section is engaged axially downstream on the downstream cylindrical rim 62 of the support and on the downstream hooks 64 of the sectors. ring to ensure the locking of the assembly.
  • the median portion of the annular support 50 is elastically deformable in the radial direction and has a U-shaped section whose base is oriented downstream, this part comprising two coaxial cylindrical walls 68, 70 extending from one to the other. inside each other and connected to each other at their downstream end.
  • the internal cylindrical wall 68 extends around the cylindrical wall 60 of the attachment means, at a distance from the latter, and is connected at its upstream end to the radially outer end of the upstream radial wall 57 of the locking means. hanging.
  • the downstream end of the inner wall 68 is connected to the downstream end of the outer cylindrical wall 70 which has a smaller axial dimension than that of the inner wall 68 and which extends around a downstream part of the wall internal 68, away from it.
  • the junction 74 between the inner 68 and outer 70 walls has a curved shape C.
  • the upstream end of the outer wall 70 is connected to a radially outer annular flange 72 which is clamped between the flange 26 of the outer casing 28 and the flanges 38, 24 of the support piece 32 and the turbine casing 22.
  • the housings 28 and 22 are not uniformly ventilated and cooled on their periphery, which generates large temperature gradients on these housings and results in carcass distortions.
  • the annular support 50 for fixing the ring sectors 20 makes it possible to dampen these distortions by elastic deformation of its medial portion in the radial direction. This deformation results in the approximation or removal of the walls 68, 70 in the radial direction.
  • This support is sufficiently rigid in the axial direction to be able to resist without deformation to the axial thrust exerted on the upstream side by the distributor 16 of the high-pressure stage, this distributor being supported at 76 by its outer periphery on the upstream face of the upstream radial wall 57 of the support.
  • the radial clearances 78 between the vanes of the wheel 18 and the ring sectors 20 can thus be adjusted precisely, in particular according to the different operating speeds of the turbomachine.
  • FIG 2 We have shown in figure 2 an alternative embodiment of the invention in which the elastically deformable middle portion of the annular support 50 has a biconical shape and has a V-shaped section whose tip is oriented upstream.
  • This part comprises two coaxial frustoconical walls 80, 82 extending one inside the other and connected to each other at their upstream ends.
  • the internal frustoconical wall 80 extends from the radially outer end of the upstream radial wall 57 'of the attachment means 54', radially outwardly and upstream, that is to say upstream of the hooking means 54 '.
  • the radially outer end of the inner wall 80 is connected to the radially inner end of the outer frustoconical wall 82 which extends radially outwards and downstream around the inner wall 80.
  • the outer wall 82 is connected at its downstream end to a radially outer annular flange 84 which is clamped axially between the flange 26 of the outer casing 28 and the flanges 38, 24 of the support piece 32 and the turbine casing 22.
  • the junction 86 between the inner walls 80 and outer 82 has a curved shape at C and defines upstream a convex annular surface and downstream a concave annular surface.
  • the upstream radial walls 57 'and downstream 58' of the attachment means 54 ' are here interconnected by a frustoconical wall 60' which is aligned with the internal frustoconical wall 80 of the support to increase its axial rigidity.
  • the figure 3 represents another variant embodiment of the device according to the invention which differs from that of the figure 2 in that it includes a cylindrical rib 88 which extends axially upstream from the radial annular surface of the junction 86 of the inner and outer walls of the support.
  • This rib 88 makes it possible to stiffen the junction zone of the two walls and to distribute the stresses in this zone.

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

Abstract

Ring sectors (20) are arranged about a turbine impeller (18) and are suspended from a turbine casing (22) by an annular support (50). The annular support supports the ring sectors and attaches to the turbine casing. The annular support deforms elastically in the radial direction to partly cushion the carcass distortions where the turbine casing is subjected in operation of the turbomachine turbine. An independent claim is included for the turbomachine turbine.

Description

La présente invention concerne un étage de turbine dans une turbomachine telle en particulier qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to a turbine stage in a turbomachine such as in particular an airplane turbojet or turboprop.

Une turbomachine comprend plusieurs étages de turbine comportant chacun un distributeur formé d'une rangée annulaire d'aubes fixes de redressement et une roue à aubes montée rotative en aval du distributeur dans une enveloppe cylindrique ou tronconique formée par des secteurs d'anneau disposés circonférentiellement bout à bout. Le premier de ces étages est un étage haute-pression et les autres étages situés en aval sont des étages basse-pression.A turbomachine comprises a plurality of turbine stages each comprising a distributor formed of an annular row of stationary vanes and a rotor wheel rotatably mounted downstream of the distributor in a cylindrical or frustoconical envelope formed by ring sectors arranged circumferentially at the end. The first of these stages is a high-pressure stage and the other stages downstream are low-pressure stages.

Il est important que les jeux radiaux entre les roues à aubes et les secteurs d'anneau correspondants soient optimisés, pour améliorer le rendement de la turbomachine et pour éviter tout frottement des extrémités des aubes sur les secteurs d'anneau, qui se traduirait par une usure de ces extrémités et par une dégradation du rendement de la turbomachine à tous les régimes de fonctionnement.It is important that the radial clearances between the paddle wheels and the corresponding ring sectors be optimized, to improve the efficiency of the turbomachine and to avoid any friction of the ends of the blades on the ring sectors, which would result in wear of these ends and degradation of the efficiency of the turbomachine at all operating speeds.

Les secteurs d'anneau qui entourent la roue à aubes de l'étage haute-pression comprennent à leurs extrémités amont et aval des moyens d'accrochage coopérant avec des moyens correspondants prévus sur un support annulaire disposé entre les secteurs d'anneau et le carter de turbine.The ring sectors that surround the impeller of the high-pressure stage comprise at their upstream and downstream ends hooking means cooperating with corresponding means provided on an annular support disposed between the ring sectors and the casing. of turbine.

En fonctionnement, les gaz chauds sortant de la chambre de combustion de la turbomachine s'écoulent à travers le distributeur de l'étage haute-pression et exercent sur celui-ci une poussée axiale vers l'aval. Ce distributeur a tendance à se déplacer vers l'aval et à venir en appui par sa périphérie externe sur le support annulaire des secteurs d'anneau et à le pousser vers l'aval, ce qui entraîne des variations des jeux radiaux entre les aubes mobiles de la roue et les secteurs d'anneau.In operation, the hot gases leaving the combustion chamber of the turbomachine flow through the distributor of the high-pressure stage and exert on it an axial thrust downstream. This distributor tends to move downstream and come to bear by its outer periphery on the annular support of the ring sectors and to push downstream, resulting variations of the radial clearances between the blades. of the wheel and ring sectors.

Une solution à ce problème consiste à rigidifier le support annulaire en le formant d'une seule pièce avec un carter support situé en aval des secteurs d'anneau et permettant de suspendre le distributeur du premier étage basse-pression au carter de turbine.One solution to this problem is to stiffen the annular support by forming it in one piece with a support housing located downstream of the ring sectors and for suspending the distributor of the first low-pressure stage to the turbine housing.

Cependant, cette solution présente de nombreux inconvénients. Le support annulaire et les secteurs d'anneau sont reliés fixement au carter support. Il n'est donc pas possible d'optimiser les jeux radiaux entre les aubes mobiles et les secteurs d'anneau en fonction du régime de la turbomachine. De plus, le carter de turbine est soumis en fonctionnement à des circulations d'air de refroidissement non uniformes sur sa périphérie qui font apparaître des gradients de température importants sur le carter, ce qui entraîne des déformations du carter appelées « distorsions de carcasse » et se traduisent par des déplacements du carter support et des secteurs d'anneau accrochés sur le support annulaire. Les déplacements des secteurs d'anneau sont aléatoires et non maîtrisés et provoquent des variations des jeux radiaux entre les aubes mobiles et les secteurs d'anneau de l'étage haute-pression qui réduisent les performances de la turbomachine.However, this solution has many disadvantages. The annular support and the ring sectors are fixedly connected to the support casing. It is therefore not possible to optimize the radial clearances between the blades and the ring sectors as a function of the speed of the turbomachine. In addition, the turbine casing is subjected in operation to non-uniform cooling air circulations on its periphery which show significant temperature gradients on the housing, resulting in deformations of the housing called "carcass distortions" and result in movements of the support housing and ring sectors hung on the annular support. The displacements of the ring sectors are random and uncontrolled and cause variations in the radial clearances between the blades and the ring sectors of the high-pressure stage which reduce the performance of the turbomachine.

Une autre solution au problème précité consiste à fixer le support directement sur le carter de turbine. Cependant, cette solution n'est pas non plus satisfaisante car pour assurer une bonne rigidité axiale de ce support, ses moyens de fixation ont en général un encombrement axial très important. Par ailleurs, cette solution ne permet pas de résoudre les problèmes de déplacements des secteurs d'anneau liés aux distorsions de carcasse du carter de turbine.Another solution to the problem mentioned above is to fix the support directly on the turbine casing. However, this solution is not satisfactory either because to ensure good axial rigidity of this support, its fastening means generally have a very large axial size. Moreover, this solution does not make it possible to solve the problems of displacement of the ring sectors related to carcass distortions of the turbine casing.

L'invention a notamment pour but d'apporter une solution simple, efficace et économique à l'ensemble des problèmes de la technique antérieure.The invention aims in particular to provide a simple, effective and economical solution to all the problems of the prior art.

Elle propose à cet effet un étage de turbine dans une turbomachine, comprenant des secteurs d'anneau agencés autour d'une roue de turbine et suspendus à un carter de turbine par un support annulaire, caractérisé en ce que le support annulaire comprend des moyens d'accrochage des secteurs d'anneau et des moyens de fixation sur le carter de turbine, reliés par deux parois annulaires coaxiales reliées l'une à l'autre et s'étendant l'une à l'intérieur de l'autre, ce support ayant en section une forme en V ou en U et étant déformable élastiquement en direction radiale pour absorber au moins en partie les déformations du carter de turbine en fonctionnement.It proposes for this purpose a turbine stage in a turbomachine, comprising ring sectors arranged around a turbine wheel and suspended from a turbine casing by an annular support, characterized in that the annular support comprises means for attaching the ring sectors and fastening means on the turbine casing, connected by two coaxial annular walls connected to one another and extending one to the inside of the other, this support section having a V-shaped or U-shaped and being elastically deformable in the radial direction to absorb at least part of the deformations of the turbine casing in operation.

Selon l'invention les secteurs d'anneau sont suspendus au carter de turbine par un support annulaire déformable en direction radiale de manière à absorber au moins en partie les distorsions de carcasse du carter externe afin que l'enveloppe formée par les secteurs d'anneau conserve un diamètre sensiblement constant en fonctionnement. L'invention permet de conserver un jeu radial sensiblement constant entre la roue et les secteurs d'anneau de l'étage haute-pression, ainsi qu'au niveau des bords d'attaque et de fuite des aubes mobiles de cette roue. Le support annulaire a de plus une bonne rigidité axiale de sorte qu'il peut résister sans se déformer à l'appui axial du côté amont du distributeur de l'étage haute-pression soumis à la poussée des gaz de combustion.According to the invention the ring sectors are suspended from the turbine casing by a radially deformable annular support so as to at least partially absorb the carcass distortions of the outer casing so that the casing formed by the ring sectors keeps a substantially constant diameter in operation. The invention makes it possible to maintain a substantially constant radial clearance between the wheel and the ring sectors of the high-pressure stage, as well as at the leading and trailing edges of the blades of this wheel. The annular support has moreover a good axial rigidity so that it can withstand without deformation in the axial support of the upstream side of the distributor of the high-pressure stage subjected to the thrust of the combustion gases.

Lle support élastiquement déformable comprend deux parois annulaires coaxiales reliées l'une à l'autre à une extrémité et s'étendant l'une à l'intérieur de l'autre, ce support ayant en section une forme en V ou en U à sommet orienté vers l'amont ou vers l'aval.The elastically deformable support comprises two coaxial annular walls connected to one another at one end and extending one inside the other, this support having a V-shaped or U-shaped section with a cross-section. oriented upstream or downstream.

En fonctionnement, les deux parois coaxiales du support peuvent se rapprocher ou s'écarter l'une de l'autre pour amortir les distorsions de carcasse du carter de turbine. La jonction entre les deux parois est conformée pour se déformer élastiquement et assurer au support une fonction de ressort. Cette structure à double paroi permet également de renforcer la rigidité axiale du support des secteurs d'anneau.In operation, the two coaxial walls of the support can move toward or away from one another to damp the carcass distortions of the turbine casing. The junction between the two walls is shaped to deform elastically and provide the support a spring function. This double wall structure also makes it possible to reinforce the axial rigidity of the support of the ring sectors.

Selon un premier mode de réalisation de l'invention, le support annulaire a en section une forme en V et comporte deux parois tronconiques respectivement interne et externe. La paroi tronconique interne peut par exemple s'étendre depuis des moyens d'accrochage des secteurs d'anneau radialement vers l'extérieur et vers l'amont jusqu'à la paroi tronconique externe qui s'étend radialement vers l'extérieur et vers l'aval. Dans ce cas, le support définit une rainure annulaire qui débouche axialement vers l'aval.According to a first embodiment of the invention, the annular support has a V-shaped cross-section and has two frustoconical walls respectively internal and external. The frustoconical wall For example, the internal portion may extend from hooking means of the ring sectors radially outwards and upstream to the outer frustoconical wall which extends radially outwards and downstream. In this case, the support defines an annular groove which opens axially downstream.

Selon un second mode de réalisation de l'invention, le support annulaire a en section une forme en U et comporte deux parois sensiblement cylindriques respectivement interne et externe. La paroi cylindrique interne peut être reliée à son extrémité amont à des moyens d'accrochage des secteurs d'anneau et à son extrémité aval à l'extrémité aval de la paroi cylindrique externe. Le support définit ici une rainure annulaire orientée axialement vers l'amont.According to a second embodiment of the invention, the annular support has a U-shaped cross-section and comprises two substantially cylindrical walls, respectively internal and external. The inner cylindrical wall may be connected at its upstream end to hooking means of the ring sectors and at its downstream end to the downstream end of the outer cylindrical wall. The support here defines an annular groove oriented axially upstream.

Préférentiellement, la paroi externe comporte une bride annulaire radialement externe de fixation sur le carter de turbine.Preferably, the outer wall comprises a radially outer annular flange for attachment to the turbine casing.

Avantageusement, la paroi interne est raccordée à une extrémité amont des moyens d'accrochage des secteurs d'anneau de manière à renforcer la rigidité axiale du support.Advantageously, the inner wall is connected to an upstream end of the hooking means of the ring sectors so as to reinforce the axial rigidity of the support.

La jonction entre les parois interne et externe peut avoir a une forme incurvée en C définissant une surface annulaire concave et une surface annulaire convexe. Cette jonction comprend avantageusement une nervure annulaire s'étendant sensiblement axialement depuis sa surface annulaire convexe pour rigidifier la zone de jonction des deux parois et répartir les contraintes dans cette zone. Cette nervure annulaire a par exemple une forme cylindrique centrée sur l'axe de révolution du support.The junction between the inner and outer walls may have a C-shaped curved shape defining a concave annular surface and a convex annular surface. This junction advantageously comprises an annular rib extending substantially axially from its convex annular surface to stiffen the junction area of the two walls and distribute the stresses in this area. This annular rib has for example a cylindrical shape centered on the axis of revolution of the support.

La présente invention concerne également une turbine de turbomachine ainsi qu'un turbomachine, telle que qu'un turboréacteur ou un turbopropulseur d'avion, comprenant au moins un étage tel que décrit ci-dessus.The present invention also relates to a turbomachine turbine and a turbomachine, such as an airplane turbojet or turboprop, comprising at least one stage as described above.

L'invention concerne aussi un support annulaire de secteurs d'anneau dans un étage de turbine d'une turbomachine, caractérisé en ce qu'il a une section en U ou en V et comprend à sa périphérie interne des moyens d'accrochage des secteurs d'anneau, et à sa périphérie externe une bride annulaire radialement externe.The invention also relates to an annular support of ring sectors in a turbine stage of a turbomachine, characterized in that it has a U or V section and comprises at its inner periphery hooking means of the ring sectors, and at its outer periphery a radially outer annular flange.

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 et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une demi vue schématique partielle en coupe axiale d'un dispositif de fixation de secteurs d'anneau selon l'invention ;
  • la figure 2 est une demi vue schématique partielle en coupe axiale d'une variante de réalisation du dispositif de fixation selon l'invention ;
  • la figure 3 est une vue schématique partielle en perspective d'une autre variante de réalisation du dispositif de fixation selon 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 nonlimiting example and with reference to the accompanying drawings in which:
  • the figure 1 is a partial schematic half-view in axial section of a ring sector fixing device according to the invention;
  • the figure 2 is a partial schematic half view in axial section of an alternative embodiment of the fixing device according to the invention;
  • the figure 3 is a partial schematic perspective view of another alternative embodiment of the fastening device according to the invention;

La figure 1 représente de manière schématique une partie d'une turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion comprenant une turbine 10, 12 agencée en aval d'une chambre de combustion 14, cette turbine comportant plusieurs étages : un étage amont ou étage haute-pression 10 et des étages aval ou étages basse-pression 12.The figure 1 schematically represents a part of a turbomachine such as an airplane turbojet or turboprop comprising a turbine 10, 12 arranged downstream of a combustion chamber 14, this turbine comprising several stages: an upstream stage or high stage 10 and downstream stages or low-pressure stages 12.

L'étage haute-pression 10 comprend un distributeur 16 formé d'une rangée annulaire d'aubes fixes de redressement, et une roue à aubes 18 montée en aval du distributeur 16 et tournant dans une enveloppe sensiblement cylindrique formée par des secteurs d'anneau 20 disposés circonférentiellement bout à bout et suspendus à un carter de turbine 22.The high-pressure stage 10 comprises a distributor 16 formed of an annular row of fixed vanes, and a vane wheel 18 mounted downstream of the distributor 16 and rotating in a substantially cylindrical casing formed by ring sectors. 20 arranged circumferentially end to end and suspended from a turbine casing 22.

Chaque étage basse-pression 12 comprend également un distributeur et une roue à aubes du type précité, seul le distributeur 30 du premier étage basse-pression étant visible en figure 1. Ce distributeur 30 est fixé au carter de turbine 22 par l'intermédiaire d'une pièce annulaire de support 32 agencée entre le distributeur 30 et le carter 22. La pièce de support 32 comprend à son extrémité radialement interne des rainures annulaires qui débouchent vers l'aval et dans lesquelles sont engagés des rebords circonférentiels 34 prévus à la périphérie externe du distributeur. La pièce 32 comprend une paroi tronconique 36 qui s'étend radialement vers l'extérieur et vers l'amont et est reliée à son extrémité radialement externe à une bride annulaire radialement externe 38 de fixation à une bride annulaire correspondante 24 prévue à l'extrémité amont du carter de turbine 22.Each low-pressure stage 12 also comprises a distributor and a paddle wheel of the aforementioned type, only the distributor 30 of the first low-pressure stage being visible in FIG. figure 1 . This distributor 30 is fixed to the turbine casing 22 by means of an annular support piece 32 arranged between the distributor 30 and the casing 22. The support piece 32 comprises at its radially inner end annular grooves which open towards the outside. downstream and in which are engaged circumferential edges 34 provided at the outer periphery of the distributor. The part 32 comprises a frustoconical wall 36 which extends radially outwards and upstream and is connected at its radially outer end to a radially outer annular flange 38 for attachment to a corresponding annular flange 24 provided at the end. upstream of the turbine casing 22.

Un carter externe 28 entourant la chambre de combustion 14 est également pourvu à son extrémité aval d'une bride annulaire radialement externe 26 qui est maintenue axialement serrée sur les brides 38 et 24 de la pièce de support 32 et du carter de turbine 22 par l'intermédiaire de moyens 40 du type vis-écrou. La chambre de combustion 14 est fixée au carter externe 28 par l'intermédiaire d'une paroi annulaire 29 s'étendant depuis l'extrémité aval de la chambre radialement vers l'extérieur et vers l'aval et comprenant à son extrémité radialement externe des moyens d'attache au carter externe 28.An outer casing 28 surrounding the combustion chamber 14 is also provided at its downstream end with a radially outer annular flange 26 which is held axially tight on the flanges 38 and 24 of the support piece 32 and the turbine casing 22 by the intermediate means 40 of the screw-nut type. The combustion chamber 14 is fixed to the outer casing 28 via an annular wall 29 extending from the downstream end of the chamber radially outwardly and downstream and comprising at its radially outer end fastening means to the outer casing 28.

Les secteurs d'anneau 20 sont suspendus au carter de turbine 22 par l'intermédiaire d'un support annulaire 50 qui est logé dans une enceinte annulaire 52 délimitée à l'amont par la paroi annulaire 29 de la chambre de combustion 14 et à l'aval par la paroi tronconique 36 de la pièce de support 32. Ce support annulaire comprend à sa périphérie interne des moyens d'accrochage 54 des secteurs d'anneau 20 et à sa périphérie externe des moyens 72 de fixation sur le carter de turbine 22.The ring sectors 20 are suspended from the turbine casing 22 by means of an annular support 50 which is housed in an annular enclosure 52 delimited upstream by the annular wall 29 of the combustion chamber 14 and at the same time. downstream by the frustoconical wall 36 of the support piece 32. This annular support comprises at its inner periphery means 54 for hooking the ring sectors 20 and at its outer periphery means 72 for fixing on the turbine casing 22 .

Selon l'invention, ce support annulaire 50 est déformable élastiquement en direction radiale pour amortir au moins en partie les distorsions de carcasse auquel est soumis le carter de turbine 22 en fonctionnement de la turbomachine, afin que l'enveloppe cylindrique formée par les secteurs d'anneau 20 conserve un diamètre sensiblement constant.According to the invention, this annular support 50 is elastically deformable in the radial direction to at least partially damp the carcass distortions to which the turbine casing 22 is subjected in operation of the turbomachine, so that the cylindrical envelope formed by the sectors of ring 20 retains a substantially constant diameter.

Le support annulaire 50 comprend à sa périphérie interne deux parois annulaire radiales 57, 58, respectivement amont et aval, qui sont reliées l'une à l'autre par une paroi cylindrique 60. Les parois radiales 57, 58 comprennent à leurs extrémités radialement internes des rebords cylindriques 62 orientés vers l'aval qui coopèrent avec des crochets circonférentiels 63, 64 prévus aux extrémités amont et aval des secteurs d'anneau 20. Un organe annulaire de verrouillage 66 à section en C est engagé axialement depuis l'aval sur le rebord cylindrique aval 62 du support et sur les crochets aval 64 des secteurs d'anneau pour assurer le verrouillage de l'ensemble.The annular support 50 comprises at its inner periphery two radial annular walls 57, 58, respectively upstream and downstream, which are connected to one another by a cylindrical wall 60. The radial walls 57, 58 comprise at their radially internal ends downstream cylindrical flanges 62 which cooperate with hooks circumferential members 63, 64 provided at the upstream and downstream ends of the ring sectors 20. An annular locking member 66 with a C-section is engaged axially downstream on the downstream cylindrical rim 62 of the support and on the downstream hooks 64 of the sectors. ring to ensure the locking of the assembly.

En figure 1, la partie médiane du support annulaire 50 est élastiquement déformable en direction radiale et a en section une forme en U dont la base est orientée vers l'aval, cette partie comportant deux parois cylindriques coaxiales 68, 70 s'étendant l'une à l'intérieur de l'autre et reliées l'une à l'autre à leur extrémité aval.In figure 1 , the median portion of the annular support 50 is elastically deformable in the radial direction and has a U-shaped section whose base is oriented downstream, this part comprising two coaxial cylindrical walls 68, 70 extending from one to the other. inside each other and connected to each other at their downstream end.

La paroi cylindrique interne 68 s'étend autour de la paroi cylindrique 60 des moyens d'accrochage, à distance de celle-ci, et est reliée à son extrémité amont à l'extrémité radialement externe de la paroi radiale amont 57 des moyens d'accrochage. L'extrémité aval de la paroi interne 68 est raccordée à l'extrémité aval de la paroi cylindrique externe 70 qui a une plus faible dimension axiale que celle de la paroi interne 68 et qui s'étend autour d'une partie aval de la paroi interne 68, à distance de celle-ci. La jonction 74 entre les parois interne 68 et externe 70 a une forme incurvée en C. L'extrémité amont de la paroi externe 70 est reliée à une bride annulaire radialement externe 72 qui est serrée entre la bride 26 du carter externe 28 et les brides 38, 24 de la pièce de support 32 et du carter de turbine 22.The internal cylindrical wall 68 extends around the cylindrical wall 60 of the attachment means, at a distance from the latter, and is connected at its upstream end to the radially outer end of the upstream radial wall 57 of the locking means. hanging. The downstream end of the inner wall 68 is connected to the downstream end of the outer cylindrical wall 70 which has a smaller axial dimension than that of the inner wall 68 and which extends around a downstream part of the wall internal 68, away from it. The junction 74 between the inner 68 and outer 70 walls has a curved shape C. The upstream end of the outer wall 70 is connected to a radially outer annular flange 72 which is clamped between the flange 26 of the outer casing 28 and the flanges 38, 24 of the support piece 32 and the turbine casing 22.

En fonctionnement de la turbomachine, les carters 28 et 22 ne sont pas ventilés et refroidis de manière uniforme sur leur périphérie ce qui engendre des gradients de température importants sur ces carters et se traduit par des distorsions de carcasse. Le support annulaire 50 de fixation des secteurs d'anneau 20 permet d'amortir ces distorsions par déformation élastique de sa partie médiane en direction radiale. Cette déformation se traduit par le rapprochement ou l'éloignement des parois 68, 70 en direction radiale. Ce support est suffisamment rigide en direction axiale pour pouvoir résister sans se déformer à la poussée axiale exercée du côté amont par le distributeur 16 de l'étage haute-pression, ce distributeur prenant appui en 76 par sa périphérie externe sur la face amont de la paroi radiale amont 57 du support. Les jeux radiaux 78 entre les aubes de la roue 18 et les secteurs d'anneau 20 peuvent ainsi être réglés avec précision, en particulier en fonction des différents régimes de fonctionnement de la turbomachine.In operation of the turbomachine, the housings 28 and 22 are not uniformly ventilated and cooled on their periphery, which generates large temperature gradients on these housings and results in carcass distortions. The annular support 50 for fixing the ring sectors 20 makes it possible to dampen these distortions by elastic deformation of its medial portion in the radial direction. This deformation results in the approximation or removal of the walls 68, 70 in the radial direction. This support is sufficiently rigid in the axial direction to be able to resist without deformation to the axial thrust exerted on the upstream side by the distributor 16 of the high-pressure stage, this distributor being supported at 76 by its outer periphery on the upstream face of the upstream radial wall 57 of the support. The radial clearances 78 between the vanes of the wheel 18 and the ring sectors 20 can thus be adjusted precisely, in particular according to the different operating speeds of the turbomachine.

On a représenté en figure 2 une variante de réalisation de l'invention dans laquelle la partie médiane élastiquement déformable du support annulaire 50 a une forme biconique et a en section une forme en V dont la pointe est orientée vers l'amont. Cette partie comprend deux parois tronconiques coaxiales 80, 82 s'étendant l'une à l'intérieur de l'autre et reliées l'une à l'autre à leurs extrémités amont.We have shown in figure 2 an alternative embodiment of the invention in which the elastically deformable middle portion of the annular support 50 has a biconical shape and has a V-shaped section whose tip is oriented upstream. This part comprises two coaxial frustoconical walls 80, 82 extending one inside the other and connected to each other at their upstream ends.

La paroi tronconique interne 80 s'étend depuis l'extrémité radialement externe de la paroi radiale amont 57' des moyens d'accrochage 54', radialement vers l'extérieur et vers l'amont, c'est-à-dire en amont des moyens d'accrochage 54'.The internal frustoconical wall 80 extends from the radially outer end of the upstream radial wall 57 'of the attachment means 54', radially outwardly and upstream, that is to say upstream of the hooking means 54 '.

L'extrémité radialement externe de la paroi interne 80 est reliée à l'extrémité radialement interne de la paroi tronconique externe 82 qui s'étend radialement vers l'extérieur et vers l'aval autour de la paroi interne 80. La paroi externe 82 est reliée à son extrémité aval à une bride annulaire radialement externe 84 qui est serrée axialement entre la bride 26 du carter externe 28 et les brides 38, 24 de la pièce de support 32 et du carter de turbine 22. La jonction 86 entre les parois interne 80 et externe 82 a une forme incurvée en C et définit à l'amont une surface annulaire convexe et à l'aval une surface annulaire concave.The radially outer end of the inner wall 80 is connected to the radially inner end of the outer frustoconical wall 82 which extends radially outwards and downstream around the inner wall 80. The outer wall 82 is connected at its downstream end to a radially outer annular flange 84 which is clamped axially between the flange 26 of the outer casing 28 and the flanges 38, 24 of the support piece 32 and the turbine casing 22. The junction 86 between the inner walls 80 and outer 82 has a curved shape at C and defines upstream a convex annular surface and downstream a concave annular surface.

Les parois radiales amont 57' et aval 58' des moyens d'accrochage 54' sont ici reliées entre elles par une paroi tronconique 60' qui est alignée avec la paroi tronconique interne 80 du support pour augmenter sa rigidité axiale.The upstream radial walls 57 'and downstream 58' of the attachment means 54 'are here interconnected by a frustoconical wall 60' which is aligned with the internal frustoconical wall 80 of the support to increase its axial rigidity.

La figure 3 représente une autre variante de réalisation du dispositif selon l'invention qui diffère de celui de la figure 2 en ce qu'il comprend une nervure cylindrique 88 qui s'étend axialement vers l'amont depuis la surface annulaire radiale de la jonction 86 des parois interne et externe du support. Cette nervure 88 permet de rigidifier la zone de jonction des deux parois et de répartir les contraintes dans cette zone.The figure 3 represents another variant embodiment of the device according to the invention which differs from that of the figure 2 in that it includes a cylindrical rib 88 which extends axially upstream from the radial annular surface of the junction 86 of the inner and outer walls of the support. This rib 88 makes it possible to stiffen the junction zone of the two walls and to distribute the stresses in this zone.

Claims (14)

Etage de turbine dans une turbomachine, comprenant des secteurs d'anneau (20) agencés autour d'une roue de turbine (18) et suspendus à un carter de turbine (22) par un support annulaire (50), caractérisé en ce que le support annulaire comprend des moyens d'accrochage (54, 54') des secteurs d'anneau et des moyens (72) de fixation sur le carter de turbine (22), reliés par deux parois annulaires coaxiales (68, 70, 80, 82) reliées l'une à l'autre et s'étendant l'une à l'intérieur de l'autre, ce support ayant en section une forme en V ou en U et étant déformable élastiquement en direction radiale pour absorber au moins en partie les déformations du carter de turbine en fonctionnement.Turbine stage in a turbomachine, comprising ring sectors (20) arranged around a turbine wheel (18) and suspended from a turbine casing (22) by an annular support (50), characterized in that the annular support comprises hooking means (54, 54 ') of the ring sectors and means (72) for attachment to the turbine casing (22), connected by two coaxial annular walls (68, 70, 80, 82 ) connected to one another and extending one inside the other, this support having a cross-section V-shaped or U-shaped and being elastically deformable in the radial direction to absorb at least partially deformations of the turbine casing in operation. Etage de turbine selon la revendication 1, caractérisé en ce que le support annulaire (50) a en section une forme en V et comporte deux parois tronconiques (80, 82) respectivement interne et externe.Turbine stage according to claim 1, characterized in that the annular support (50) has a V-shaped section and has two frustoconical walls (80, 82) respectively internal and external. Etage de turbine selon la revendication 2, caractérisé en ce que la paroi tronconique interne (80) s'étend depuis des moyens d'accrochage (54') des secteurs d'anneau radialement vers l'extérieur et vers l'amont jusqu'à la paroi tronconique externe (82) qui s'étend radialement vers l'extérieur et vers l'aval.Turbine stage according to claim 2, characterized in that the internal frustoconical wall (80) extends from the hooking means (54 ') of the ring sectors radially outwards and upstream to the outer frustoconical wall (82) extending radially outwardly and downstream. Etage de turbine selon la revendication 1, caractérisé en ce que le support annulaire (50) a en section une forme en U et comporte deux parois sensiblement cylindriques (68, 70) respectivement interne et externe.Turbine stage according to Claim 1, characterized in that the annular support (50) has a U-shaped section and has two substantially cylindrical walls (68, 70), respectively internal and external. Etage de turbine selon la revendication 4, caractérisé en ce que la paroi cylindrique interne (68) est reliée à son extrémité amont à des moyens d'accrochage (54) des secteurs d'anneau et à son extrémité aval à l'extrémité aval de la paroi cylindrique externe (70).Turbine stage according to claim 4, characterized in that the internal cylindrical wall (68) is connected at its upstream end to hooking means (54) of the ring sectors and at its downstream end to the downstream end of the ring. the outer cylindrical wall (70). Etage de turbine selon l'une des revendications 1 à 5, caractérisé en ce que la paroi externe (70, 82) comporte une bride annulaire radialement externe (72, 84) de fixation sur le carter de turbine (22).Turbine stage according to one of claims 1 to 5, characterized in that the outer wall (70, 82) has a radially outer annular flange (72, 84) for attachment to the turbine casing (22). Etage de turbine selon l'une des revendications 1 à 6, caractérisé en ce que la paroi interne (68, 80) est raccordée à une extrémité amont de moyens d'accrochage (54, 54') des secteurs d'anneau.Turbine stage according to one of claims 1 to 6, characterized in that the inner wall (68, 80) is connected to an upstream end of hooking means (54, 54 ') of the ring sectors. Etage de turbine selon l'une des revendications 1 à 7, caractérisé en ce que la jonction (74, 86) entre les parois interne et externe a une forme incurvée en C définissant une surface annulaire concave et une surface annulaire convexe.Turbine stage according to one of claims 1 to 7, characterized in that the junction (74, 86) between the inner and outer walls has a C-shaped curved shape defining a concave annular surface and a convex annular surface. Etage de turbine selon la revendication 8, caractérisé en ce que la jonction (86) comprend une nervure annulaire (88) s'étendant sensiblement axialement depuis sa surface annulaire convexe.Turbine stage according to claim 8, characterized in that the junction (86) comprises an annular rib (88) extending substantially axially from its convex annular surface. Etage de turbine selon la revendication 9, caractérisé en ce que la nervure annulaire (88) est de forme cylindrique centrée sur l'axe de révolution du support annulaire (50).Turbine stage according to claim 9, characterized in that the annular rib (88) is cylindrical in shape centered on the axis of revolution of the annular support (50). Etage de turbine selon l'une des revendications précédentes, caractérisé en ce que le support annulaire (50) est formé d'une seule pièce.Turbine stage according to one of the preceding claims, characterized in that the annular support (50) is formed in one piece. Turbine de turbomachine, caractérisée en ce qu'elle comprend au moins un étage selon l'une des revendications précédentes.Turbomachine turbine, characterized in that it comprises at least one stage according to one of the preceding claims. Turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend au moins un étage de turbine selon l'une des revendications 1 à 11.Turbomachine, such as an airplane turbojet or turboprop engine, characterized in that it comprises at least one turbine stage according to one of claims 1 to 11. Support annulaire de secteurs d'anneau (20) dans un étage de turbine d'une turbomachine, caractérisé en ce qu'il a une section en U ou en V et comprend à sa périphérie interne des moyens d'accrochage (54, 54') des secteurs d'anneau, et à sa périphérie externe une bride annulaire radialement externe (72, 84).Annular support of ring sectors (20) in a turbine stage of a turbomachine, characterized in that it has a U-shaped or V-shaped section and comprises at its inner periphery hooking means (54, 54 ' ) ring sectors, and at its outer periphery a radially outer annular flange (72, 84).
EP08151521.5A 2007-02-28 2008-02-15 Turbine stage in a turbomachine Active EP1965034B1 (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2944554A1 (en) * 2009-04-16 2010-10-22 Snecma High pressure turbine for turbo machine of aircraft, has downstream radial wall carrying axial support unit supported on upstream radial wall for axially retaining external structure of distributor with respect to case
FR3055655A1 (en) * 2016-09-06 2018-03-09 Safran Aircraft Engines INTERMEDIATE CASE OF TURBOMACHINE TURBINE

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2913051B1 (en) * 2007-02-28 2011-06-10 Snecma TURBINE STAGE IN A TURBOMACHINE
US9371835B2 (en) 2013-07-19 2016-06-21 Praxair Technology, Inc. Coupling for directly driven compressor
DE102013017713B4 (en) * 2013-10-24 2022-10-27 Man Energy Solutions Se turbomachine
US10443424B2 (en) * 2016-03-16 2019-10-15 United Technologies Corporation Turbine engine blade outer air seal with load-transmitting carriage
FR3074518B1 (en) 2017-12-05 2020-01-03 Safran Aircraft Engines CONNECTION BETWEEN A CERAMIC MATRIX COMPOSITE DISTRIBUTOR AND A METAL SUPPORT OF A TURBOMACHINE TURBINE
FR3087828B1 (en) 2018-10-26 2021-01-08 Safran Helicopter Engines MOBILE TURBOMACHINE BLADE
FR3097299B1 (en) * 2019-06-13 2021-07-23 Safran SET FOR A GAS TURBINE
US11215075B2 (en) * 2019-11-19 2022-01-04 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314648A (en) * 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
EP1059420A1 (en) 1999-06-10 2000-12-13 Snecma Moteurs Housing for a high pressure compressor
EP1408200A2 (en) 2002-10-10 2004-04-14 Rolls-Royce Deutschland Ltd & Co KG Turbine shroud segment attachment
EP1517005A1 (en) * 2003-09-19 2005-03-23 Snecma Moteurs Gas turbine sealing joint having lamellar structure
FR2887939A1 (en) 2005-06-29 2007-01-05 Snecma TURBOMACHINE MULTI-STAGE COMPRESSOR

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT251179B (en) * 1962-03-20 1966-12-27 Rudolf Baer Compressor unit
US4157232A (en) * 1977-10-31 1979-06-05 General Electric Company Turbine shroud support
FR2519374B1 (en) * 1982-01-07 1986-01-24 Snecma DEVICE FOR COOLING THE HEELS OF MOBILE BLADES OF A TURBINE
GB2117843B (en) * 1982-04-01 1985-11-06 Rolls Royce Compressor shrouds
US5181826A (en) * 1990-11-23 1993-01-26 General Electric Company Attenuating shroud support
US5593277A (en) * 1995-06-06 1997-01-14 General Electric Company Smart turbine shroud
GB2310255B (en) * 1996-02-13 1999-06-16 Rolls Royce Plc A turbomachine
DE19745683A1 (en) * 1997-10-16 1999-04-22 Bmw Rolls Royce Gmbh Suspension of an annular gas turbine combustion chamber
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
FR2819010B1 (en) * 2001-01-04 2004-05-28 Snecma Moteurs STATOR RING SUPPORT AREA OF THE TURBINE HIGH PRESSURE TURBINE ROTATOR WITH A TURBOMACHINE
FR2825787B1 (en) * 2001-06-06 2004-08-27 Snecma Moteurs FITTING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY FLEXIBLE LINKS
FR2860041B1 (en) * 2003-09-22 2005-11-25 Snecma Moteurs REALIZING THE SEALING IN A TURBOJET FOR THE DOUBLE BALL TUBE COLLECTION
GB2420830B (en) * 2004-12-01 2007-01-03 Rolls Royce Plc Improved casing arrangement
FR2913051B1 (en) * 2007-02-28 2011-06-10 Snecma TURBINE STAGE IN A TURBOMACHINE

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314648A (en) * 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
EP1059420A1 (en) 1999-06-10 2000-12-13 Snecma Moteurs Housing for a high pressure compressor
EP1408200A2 (en) 2002-10-10 2004-04-14 Rolls-Royce Deutschland Ltd & Co KG Turbine shroud segment attachment
EP1517005A1 (en) * 2003-09-19 2005-03-23 Snecma Moteurs Gas turbine sealing joint having lamellar structure
FR2887939A1 (en) 2005-06-29 2007-01-05 Snecma TURBOMACHINE MULTI-STAGE COMPRESSOR

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2944554A1 (en) * 2009-04-16 2010-10-22 Snecma High pressure turbine for turbo machine of aircraft, has downstream radial wall carrying axial support unit supported on upstream radial wall for axially retaining external structure of distributor with respect to case
FR3055655A1 (en) * 2016-09-06 2018-03-09 Safran Aircraft Engines INTERMEDIATE CASE OF TURBOMACHINE TURBINE
EP3299590A1 (en) * 2016-09-06 2018-03-28 Safran Aircraft Engines Intermediate casing of a turbomachine turbine

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CA2622119C (en) 2015-04-28
EP1965034B1 (en) 2017-04-05
CA2622119A1 (en) 2008-08-28
US20080206047A1 (en) 2008-08-28
FR2913051A1 (en) 2008-08-29
FR2913051B1 (en) 2011-06-10
US8403636B2 (en) 2013-03-26

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