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EP1099826A1 - Positioning device for a turbine liner - Google Patents

Positioning device for a turbine liner Download PDF

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Publication number
EP1099826A1
EP1099826A1 EP00403105A EP00403105A EP1099826A1 EP 1099826 A1 EP1099826 A1 EP 1099826A1 EP 00403105 A EP00403105 A EP 00403105A EP 00403105 A EP00403105 A EP 00403105A EP 1099826 A1 EP1099826 A1 EP 1099826A1
Authority
EP
European Patent Office
Prior art keywords
spacer
ring
mortise
tenon
hook
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP00403105A
Other languages
German (de)
French (fr)
Other versions
EP1099826B1 (en
Inventor
Jean-Baptiste Arilla
Sylvie Coulon
Pierre Debeneix
Florence Irène Noelle Leutard
Paul Rodriques
Patrice Jean Marc Rosset
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1099826A1 publication Critical patent/EP1099826A1/en
Application granted granted Critical
Publication of EP1099826B1 publication Critical patent/EP1099826B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • 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
    • 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

Definitions

  • This invention is part of an assembly particular between a turbine ring, having for function to border the turbine by delimiting the vein gas flow, and a piece called a spacer which belongs to the structure of the turbine.
  • a modern assembly is described in the patent American 5,197,853 and illustrated in Figure 4.
  • a body turbine 1 carries a spacer 2 which carries itself a ring 3.
  • the assembly parts of ring 3 to spacer 2 include, on the upstream side, a hook spacer 4 and a ring hook 5 which are nested one inside the other: mounting the ring 3 is produced by pushing the end of the hook ring 5 in the hollow of the spacer hook 4, then by rotating the ring 3 to approach its opposite end, located downstream from that of the spacer 2; the other 6 assembly parts are located on these downstream ends.
  • flange ring 8 It is a ledge of spacer 7 first radially inward, then downstream, and a ring flange 8 directed radially towards outside then axially downstream; the flange ring 8 is shaped into a mortise 9 in which accommodates part of the spacer flange 7, which plays thus the role of tenon.
  • the post has two flanges 10 and 11, directed radially towards the interior and which come up against the bottom of the mortise 9. Staples 12 are then fixed over the parallel ends of the flanges 7 and 8, so that its branches 13 and 14 enclose them and keep them from falling apart.
  • This axial clearance creates an air leak downstream of the system. It is therefore important to reduce it as much as possible. A minimum value must however be observed so to preserve the tilting assembly of the ring.
  • ring 3 For perform a good seal on the downstream hook, ring 3 must be plated: its opposite face must press on the collar 10. For this, the collar 10 is locally deformed in an axial direction to cause this tightening. So this point tightening system allows both to ensure the axial clearance necessary for the tilting and sealing by pressing.
  • the invention relates to an assembly perfected between a turbine ring and its spacer, in which we substantially resume the principles of this previous assembly (fixing in radial direction by hooks nested on one side, and by abutment faces of flanges on another side; and limitation of axial movement by a tenon system mortise on this other side), but which is superior in with regard to the cohesion of the adjustment, the protection of the spacer against overheating excessive and mechanical strength.
  • the post now belongs to the ring, and the mortise to the spacer, and that the tenon and mortise are separated from the stop faces on the edges of the spacer and the ring, and placed behind the portions of these edges which carry the stop faces.
  • the spacer 2 is generally made of a material that is easier to machine, which allows you to easily create the mortise, for example by shaping a tongue, which helps to surround the mortise in conjunction with an adjoining part of the spacer.
  • the tongue may be sufficiently flexible to be deformed and lock the post in good conditions and perform axial tightening to obtain a plane seal.
  • the tenon and the mortise thus offer a resistance to gas leaks between the chamber interior and circulation vein. It then becomes possible under good conditions to separate the spacer and ring edges on most of their length and keep only a small area stop, instead of the two flanges 10 and 11 spaced from the previous conception: heat transmissions from ring 3 to spacer 2 are then more reduced.
  • the clips that keep the edges tight can see their soul lodged in gashes of these edges, which does not affect the waterproofness of assembly since the edges would have been separated at the location of the cuts; but pushing the souls of staples to the notches, they avoid protruding outside the edges and we reduce the overall size; in addition, the staples are now used to limit the sliding movement angle of the rings on the spacers, abutting against the lateral faces of the notches. So we can remove the pawns from the previous realization and their holes which were the seat of concentrations significant constraints.
  • the cuts are also responsible for stress concentrations, but who are less important because of their size and of their more regular shape.
  • the hook of the ring 3 can cover the spacer hook, unlike the design which again has the advantage of locally protect the spacer from overheating produced by the vein.
  • the spacer and the ring whose general shape of each remains similar to that of achievement known, here bear the respective references 102 and 103. They are conventionally formed of butted segments along a circumference, and the segments of the ring 103 carry discarded strip seals 30 between segments to limit gas flows in the radial and axial directions. Room interior 31 similar to chamber 17 is delimited by the spacer 102 and the ring 103.
  • the spacer 102 On the upstream side, the spacer 102 carries a hook 32 whose rod 33, extending radially inwards, gives on the chamber 31 and whose end 34 extends upstream; the hook 35 of the ring 103 extends outside the previous and covers it, with a rod 36 coming in front its tip 34 and a tip 37 coming in front of the rod 33; the hooks are thus reversed with respect to the earlier design but their assembly by nesting remains the same.
  • the spacer 102 and the ring 103 are provided with edges 38 and 39 which extend parallel to downstream like edges 7 and 8 of the design front, but here the edge 38 of the spacer 102 includes only a flange 40 which establishes the stop with rim 39; edges 38 and 39 are separated over most of their length of a set 57.
  • the tightening of the ring 103 on the spacer 102 in axial direction is due to a pin 41 established on the ring 103 and located behind the rim 38 of the spacer 102, on the side of the chamber 31; this tenon is retained in a mortise 42 bounded by the ledge 38 and above all by a curved tongue 43, built on the rear face of this rim 38.
  • the end 44 of the tongue 43 is flexible, which allows the fold when mounting is done, to remove the axial play of the stud 41 between the flange 38 and the tongue 43; the low rigidity of the tip 44 allows to introduce only moderate constraints, which are not likely to become excessive during operation, when dilations and vibrations difficult to assess affected the assembly.
  • a seal 55 can be inserted into a groove 56 dug in one of the edges 39, at the place abutment faces, to complete the seal.

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

Abstract

The invention concerns a ring (103) assembled to the strut (102) of the turbine by an assembly of hooks (32, 35) nested on one side, and a rim locking stops (38, 39) and a mortise-and-tenon joint (41, 42) on the other side. The invention is characterised in that the mortise-and-tenon (41, 42) are separated from the rim locking stops (38, 39) to limit the clearances in axial direction produced by construction or thermal expansions, to improve the mechanical resistance and simplify manufacture.

Description

Cette invention ressortit à un assemblage particulier entre un anneau de turbine, ayant pour fonction de border la turbine en délimitant la veine d'écoulement des gaz, et une pièce appelée entretoise qui appartient à la structure de la turbine.This invention is part of an assembly particular between a turbine ring, having for function to border the turbine by delimiting the vein gas flow, and a piece called a spacer which belongs to the structure of the turbine.

Un assemblage moderne est décrit dans le brevet américain 5,197,853 et illustré à la figure 4. Un corps de turbine 1 porte une entretoise 2 qui porte elle-même un anneau 3. Les pièces d'assemblage de l'anneau 3 à l'entretoise 2 comprennent, du côté amont, un crochet d'entretoise 4 et un crochet d'anneau 5 qui sont imbriqués l'un dans l'autre : le montage de l'anneau 3 est produit en enfonçant l'extrémité du crochet d'anneau 5 dans le creux du crochet d'entretoise 4, puis en faisant pivoter l'anneau 3 pour approcher son extrémité opposée, située en aval, de celle de l'entretoise 2 ; les autres pièces 6 d'assemblage sont situées sur ces extrémités aval.A modern assembly is described in the patent American 5,197,853 and illustrated in Figure 4. A body turbine 1 carries a spacer 2 which carries itself a ring 3. The assembly parts of ring 3 to spacer 2 include, on the upstream side, a hook spacer 4 and a ring hook 5 which are nested one inside the other: mounting the ring 3 is produced by pushing the end of the hook ring 5 in the hollow of the spacer hook 4, then by rotating the ring 3 to approach its opposite end, located downstream from that of the spacer 2; the other 6 assembly parts are located on these downstream ends.

Il s'agit d'un rebord d'entretoise 7 dirigé d'abord radialement vers l'intérieur, puis vers l'aval, et d'un rebord d'anneau 8 dirigé radialement vers l'extérieur puis axialement vers l'aval ; le rebord d'anneau 8 est façonné en une mortaise 9 dans laquelle se loge une partie du rebord d'entretoise 7, qui joue ainsi le rôle de tenon. Le tenon présente deux collerettes 10 et 11, dirigées radialement vers l'intérieur et qui viennent buter contre le fond de la mortaise 9. Des agrafes 12 sont ensuite fixées par-dessus les extrémités parallèles des rebords 7 et 8, de manière que ses branches 13 et 14 les enserrent et les empêchent de se disjoindre. La disjonction entre l'entretoise 2 et l'anneau 3 est également interdite par l'imbrication des crochets 4 et 5 de l'autre côté ; l'anneau 3 peut jouer légèrement en direction axiale sur l'entretoise 2, à l'intérieur d'une course dont la longueur est définie par le jeu total entre les flancs des collerettes 10 et 11 et les flancs de la mortaise 9, aux endroits notés par les références 15 et 16.It is a ledge of spacer 7 first radially inward, then downstream, and a ring flange 8 directed radially towards outside then axially downstream; the flange ring 8 is shaped into a mortise 9 in which accommodates part of the spacer flange 7, which plays thus the role of tenon. The post has two flanges 10 and 11, directed radially towards the interior and which come up against the bottom of the mortise 9. Staples 12 are then fixed over the parallel ends of the flanges 7 and 8, so that its branches 13 and 14 enclose them and keep them from falling apart. The disjunction between the spacer 2 and the ring 3 is also prohibited by the interlocking of hooks 4 and 5 on the other side; ring 3 can play slightly in the axial direction on spacer 2, inside a race whose length is defined by the total clearance between the sides flanges 10 and 11 and the sides of the mortise 9, at the locations noted by references 15 and 16.

Ce jeu axial crée une fuite d'air à l'aval du système. Il importe donc de le réduire au mieux. Une valeur minimale doit cependant être respectée de façon à préserver le montage en bascule de l'anneau. Pour effectuer une bonne étanchéité sur le crochet aval, l'anneau 3 doit être plaqué : sa face en regard doit appuyer sur la collerette 10. Pour cela, la collerette 10 est déformée localement en sens axial pour provoquer ce serrage. Ainsi, ce système de serrage ponctuel permet à la fois d'assurer le jeu axial nécessaire à la bascule et une étanchéité par appui.This axial clearance creates an air leak downstream of the system. It is therefore important to reduce it as much as possible. A minimum value must however be observed so to preserve the tilting assembly of the ring. For perform a good seal on the downstream hook, ring 3 must be plated: its opposite face must press on the collar 10. For this, the collar 10 is locally deformed in an axial direction to cause this tightening. So this point tightening system allows both to ensure the axial clearance necessary for the tilting and sealing by pressing.

L'invention est relative à un assemblage perfectionné entre un anneau de turbine et son entretoise, dans lequel on reprend sensiblement les principes de cet assemblage antérieur (fixation en direction radiale par des crochets imbriqués d'un côté, et par des faces de butée de rebords d'un autre côté ; et limitation du mouvement axial par un système à tenon mortaise de cet autre côté), mais qui soit supérieur en ce qui concerne la cohésion de l'ajustement, la protection de l'entretoise contre les échauffements excessifs et la résistance mécanique.The invention relates to an assembly perfected between a turbine ring and its spacer, in which we substantially resume the principles of this previous assembly (fixing in radial direction by hooks nested on one side, and by abutment faces of flanges on another side; and limitation of axial movement by a tenon system mortise on this other side), but which is superior in with regard to the cohesion of the adjustment, the protection of the spacer against overheating excessive and mechanical strength.

Il comprend divers perfectionnements, dont le plus notable est peut-être que le tenon appartient désormais à l'anneau, et la mortaise à l'entretoise, et que le tenon et la mortaise sont séparés des faces de butée sur les rebords de l'entretoise et de l'anneau, et placés derrière lés portions de ces rebords qui portent les faces de butée.It includes various improvements, the most notable is perhaps that the post now belongs to the ring, and the mortise to the spacer, and that the tenon and mortise are separated from the stop faces on the edges of the spacer and the ring, and placed behind the portions of these edges which carry the stop faces.

On obtient donc l'avantage que le tenon et la mortaise donnent sur la chambre intérieure, référencée par 17 dans la figure 4, et sont ainsi moins exposés aux échauffements et aux dilatations. La présence du tenon sur l'anneau est également avantageuse en elle-même, puisque l'anneau est généralement en un matériau monocristallin qu'il est assez difficile d'usiner ; on constate qu'il est moins difficile d'y créer un tenon que la mortaise 9. L'entretoise 2 est généralement construite en un matériau plus facile à usiner, ce qui permet d'y créer facilement la mortaise, par exemple en y façonnant une languette, qui contribue à entourer la mortaise en liaison avec une partie attenante de l'entretoise. La languette peut être suffisamment flexible pour être déformée et bloquer le tenon dans de bonnes conditions et effectuer un serrage axial pour obtenir une étanchéité plane.We therefore obtain the advantage that the tenon and the mortise overlook the interior room, referenced by 17 in figure 4, and are thus less exposed to heating and dilation. The presence of tenon on the ring is also advantageous in itself, since the ring is generally made of a material monocrystalline which is quite difficult to machine; we finds it less difficult to create a post than the mortise 9. The spacer 2 is generally made of a material that is easier to machine, which allows you to easily create the mortise, for example by shaping a tongue, which helps to surround the mortise in conjunction with an adjoining part of the spacer. The tongue may be sufficiently flexible to be deformed and lock the post in good conditions and perform axial tightening to obtain a plane seal.

Le tenon et la mortaise offrent ainsi une résistance aux fuites de gaz entre la chambre intérieure et la veine de circulation. Il devient alors possible dans de bonnes conditions de désolidariser les rebords d'entretoise et d'anneau sur l'essentiel de leur longueur et de ne conserver qu'une petite surface de butée, au lieu des deux collerettes 10 et 11 espacées de la conception antérieure : les transmissions de chaleur de l'anneau 3 à l'entretoise 2 sont alors plus réduites.The tenon and the mortise thus offer a resistance to gas leaks between the chamber interior and circulation vein. It then becomes possible under good conditions to separate the spacer and ring edges on most of their length and keep only a small area stop, instead of the two flanges 10 and 11 spaced from the previous conception: heat transmissions from ring 3 to spacer 2 are then more reduced.

Un autre perfectionnement devient alors possible : les agrafes qui maintiennent le serrage des rebords peuvent voir leur âme logée dans des entailles de ces rebords, ce qui n'affecte point l'étanchéité de l'assemblage puisque les rebords auraient été séparés à l'endroit des entailles ; mais en poussant les âmes des agrafes vers les entailles, on évite qu'elles saillent à l'extérieur des rebords et on réduit ainsi l'encombrement de l'ensemble ; de plus, les agrafes servent désormais à limiter le mouvement de glissement angulaire des anneaux sur les entretoises, en butant contre les faces latérales des entailles. On peut donc supprimer les pions de la réalisation antérieure et leurs perçages qui étaient le siège de concentrations de contraintes importantes. Les entailles sont aussi responsables de concentrations de contraintes, mais qui sont moins importantes à cause de leurs dimensions et de leur forme plus régulière.Another improvement then becomes possible: the clips that keep the edges tight can see their soul lodged in gashes of these edges, which does not affect the waterproofness of assembly since the edges would have been separated at the location of the cuts; but pushing the souls of staples to the notches, they avoid protruding outside the edges and we reduce the overall size; in addition, the staples are now used to limit the sliding movement angle of the rings on the spacers, abutting against the lateral faces of the notches. So we can remove the pawns from the previous realization and their holes which were the seat of concentrations significant constraints. The cuts are also responsible for stress concentrations, but who are less important because of their size and of their more regular shape.

Il n'est pas jusqu'au côté opposé, porteur des crochets, qui ne puisse être perfectionné selon l'invention : le crochet de l'anneau 3 peut couvrir le crochet d'entretoise, contrairement à la conception antérieure, ce qui présente encore ici l'avantage de protéger localement l'entretoise des échauffements produits par la veine. It is not to the opposite side, carrying the hooks, which cannot be improved according to the invention: the hook of the ring 3 can cover the spacer hook, unlike the design which again has the advantage of locally protect the spacer from overheating produced by the vein.

L'invention va maintenant être décrite en détail à l'aide des figures suivantes qui représentent une réalisation préférée :

  • la figure 1 est une vue générale de l'invention,
  • la figure 2 est un détail de la figure 1,
  • la figure 3 est une vue en perspective des pièces de la figure 2,
  • et la figure 4, déjà décrite, illustre l'art antérieur.
The invention will now be described in detail using the following figures which show a preferred embodiment:
  • FIG. 1 is a general view of the invention,
  • FIG. 2 is a detail of FIG. 1,
  • FIG. 3 is a perspective view of the parts of FIG. 2,
  • and Figure 4, already described, illustrates the prior art.

La figure 1 est abordée maintenant.Figure 1 is discussed now.

L'entretoise et l'anneau, dont la forme générale de chacun reste semblable à celle de la réalisation connue, portent ici les références respectives 102 et 103. Ils sont classiquement formés de segments aboutés le long d'une circonférence, et les segments de l'anneau 103 portent des joints en lamelle 30 jetés entre les segments pour limiter les circulations de gaz dans les directions radiale et axiale. Une chambre intérieure 31 analogue à la chambre 17 est délimitée par l'entretoise 102 et l'anneau 103. Du côté amont, l'entretoise 102 porte un crochet 32 dont la tige 33, s'allongeant radialement vers l'intérieur, donne sur la chambre 31 et dont le bout 34 s'étend vers l'amont ; le crochet 35 de l'anneau 103 s'étend à l'extérieur du précédent et le couvre, avec une tige 36 venant devant son bout 34 et un bout 37 venant devant la tige 33 ; les crochets sont ainsi inversés par rapport à la conception antérieure, mais leur assemblage par imbrication reste identique. The spacer and the ring, whose general shape of each remains similar to that of achievement known, here bear the respective references 102 and 103. They are conventionally formed of butted segments along a circumference, and the segments of the ring 103 carry discarded strip seals 30 between segments to limit gas flows in the radial and axial directions. Room interior 31 similar to chamber 17 is delimited by the spacer 102 and the ring 103. On the upstream side, the spacer 102 carries a hook 32 whose rod 33, extending radially inwards, gives on the chamber 31 and whose end 34 extends upstream; the hook 35 of the ring 103 extends outside the previous and covers it, with a rod 36 coming in front its tip 34 and a tip 37 coming in front of the rod 33; the hooks are thus reversed with respect to the earlier design but their assembly by nesting remains the same.

On se reporte maintenant au côté aval de l'assemblage et principalement aux figures 2 et 3 ; l'entretoise 102 et l'anneau 103 sont pourvus de rebords 38 et 39 qui s'étendent parallèlement vers l'aval comme les rebords 7 et 8 de la conception antérieure, mais ici le rebord 38 de l'entretoise 102 ne comprend qu'une collerette 40 qui établit la butée avec le rebord 39 ; les rebords 38 et 39 sont séparés sur la plus grande partie de leur longueur d'un jeu 57.We now refer to the downstream side of the assembly and mainly in Figures 2 and 3; the spacer 102 and the ring 103 are provided with edges 38 and 39 which extend parallel to downstream like edges 7 and 8 of the design front, but here the edge 38 of the spacer 102 includes only a flange 40 which establishes the stop with rim 39; edges 38 and 39 are separated over most of their length of a set 57.

Le serrage de l'anneau 103 sur l'entretoise 102 en direction axiale est dû à un tenon 41 établi sur l'anneau 103 et situé derrière le rebord 38 de l'entretoise 102, du côté de la chambre 31 ; ce tenon est retenu dans une mortaise 42 délimitée par le rebord 38 et surtout par une languette 43 recourbée, construite sur la face arrière de ce rebord 38. Le bout 44 de la languette 43 est flexible, ce qui permet de le plier quand le montage est réalisé, pour supprimer le jeu en direction axiale du tenon 41 entre le rebord 38 et la languette 43 ; la faible rigidité du bout 44 permet de n'y introduire que des contraintes modérées, qui ne risquent pas de devenir excessives pendant le fonctionnement, quand des dilatations et des vibrations difficiles à évaluer ont affecté l'assemblage.The tightening of the ring 103 on the spacer 102 in axial direction is due to a pin 41 established on the ring 103 and located behind the rim 38 of the spacer 102, on the side of the chamber 31; this tenon is retained in a mortise 42 bounded by the ledge 38 and above all by a curved tongue 43, built on the rear face of this rim 38. The end 44 of the tongue 43 is flexible, which allows the fold when mounting is done, to remove the axial play of the stud 41 between the flange 38 and the tongue 43; the low rigidity of the tip 44 allows to introduce only moderate constraints, which are not likely to become excessive during operation, when dilations and vibrations difficult to assess affected the assembly.

On retrouve des agrafes 45 dont les branches 46 et 47 servent à enserrer les rebords 38 et 39 entre elles pour maintenir la butée par la collerette 40 ; cependant, les rebords 38 et 39 sont munis d'entailles 48 et 49 en regard et suffisamment larges pour qu'on puisse y glisser l'âme 50 de l'agrafe 45 en la poussant vers l'amont. L'âme 50 limite ainsi les mouvements angulaires de l'anneau 103 sur l'entretoise 102 grâce à des butées entre l'âme 50 et des faces latérales 51, 52, 53 et 54 des entailles 48 et 49. Aucun autre moyen n'est plus nécessaire pour arrêter ces mouvements : les pions utilisés auparavant et glissés dans des perçages des rebords deviennent inutiles et sont omis.There are staples 45 whose branches 46 and 47 are used to enclose the edges 38 and 39 therebetween to maintain the stop by the collar 40; however, the edges 38 and 39 are provided with notches 48 and 49 opposite and wide enough to can slide the core 50 of the clip 45 into it by pushing it upstream. Soul 50 thus limits movement of the ring 103 on the spacer 102 thanks to stops between the core 50 and side faces 51, 52, 53 and 54 of cuts 48 and 49. No other way is no longer necessary to stop these movements: pawns previously used and slid into holes ledges become useless and are omitted.

Un joint d'étanchéité 55 peut être inséré dans une gorge 56 creusée dans un des rebords 39, à l'endroit des faces de butée, pour y parfaire l'étanchéité.A seal 55 can be inserted into a groove 56 dug in one of the edges 39, at the place abutment faces, to complete the seal.

Claims (6)

Assemblage entre un anneau de turbine (103) bordant une entretoise (102) de structure de turbine (101) comprenant, à un côté amont, un crochet d'anneau (35) et un crochet d'entretoise (32) qui sont imbriqués et, à un côté aval, un système de jonction comprenant un rebord d'entretoise (38) et un rebord d'anneau (39) en butée, et enserrés par des agrafes (45) et un tenon et une mortaise de rétention axiale façonnés sur l'anneau et l'entretoise, le tenon étant engagé dans la mortaise, caractérisé en ce que le tenon et la mortaise sont situés en amont des rebords en butée.Assembly between a turbine ring (103) bordering a spacer (102) of structure turbine (101) comprising, on an upstream side, a hook ring (35) and a spacer hook (32) which are nested and, at one downstream side, a junction system comprising a spacer rim (38) and a rim ring (39) in abutment, and clamped by staples (45) and a tenon and an axial retention mortise shaped on the ring and the spacer, the tenon being engaged in the mortise, characterized in that the tenon and the mortise are located upstream of the edges in stop. Assemblage selon la revendication 1, caractérisé en ce que la mortaise est délimitée par une languette (43) flexible de l'entretoise, le tenon étant engagé dans la mortaise avec un jeu nul.Assembly according to claim 1, characterized in that the mortise is delimited by a flexible tongue (43) of the spacer, the tenon being engaged in mortise with zero play. Assemblage selon la revendication 2, caractérisé en ce que le rebord d'entretoise (38) et le rebord de butée (39) sont en butée sur une partie de leur longueur et séparés d'un jeu sur une autre partie de leur longueur.Assembly according to claim 2, characterized in that the spacer flange (38) and the abutment flange (39) abuts on part of their length and separated from a game on another part of their length. Assemblage selon la revendication 3, caractérisé en ce que les rebords (38, 39) sont munis d'entailles (48, 49) en regard recevant une âme (50) des agrafes (45).Assembly according to claim 3, characterized in that the edges (38, 39) are provided notches (48, 49) facing receiving a soul (50) staples (45). Assemblage selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le tenon et la mortaise donnent dans une chambre intérieure délimitée par l'entretoise et par l'anneau.Assembly according to any one of Claims 1 to 4, characterized in that the post and mortise give in an interior room delimited by the spacer and by the ring. Assemblage selon l'une quelconque des revendications 1 à 5, caractérisé en ce que le crochet de l'anneau (39) couvre le crochet de l'entretoise (32).Assembly according to any one of Claims 1 to 5, characterized in that the hook of the ring (39) covers the hook of the spacer (32).
EP00403105A 1999-11-10 2000-11-09 Positioning device for a turbine liner Expired - Lifetime EP1099826B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9914103A FR2800797B1 (en) 1999-11-10 1999-11-10 ASSEMBLY OF A RING BORDING A TURBINE TO THE TURBINE STRUCTURE
FR9914103 1999-11-10

Publications (2)

Publication Number Publication Date
EP1099826A1 true EP1099826A1 (en) 2001-05-16
EP1099826B1 EP1099826B1 (en) 2005-01-26

Family

ID=9551941

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00403105A Expired - Lifetime EP1099826B1 (en) 1999-11-10 2000-11-09 Positioning device for a turbine liner

Country Status (11)

Country Link
US (1) US6575697B1 (en)
EP (1) EP1099826B1 (en)
JP (1) JP4181323B2 (en)
KR (1) KR100724779B1 (en)
CA (1) CA2359049C (en)
DE (1) DE60017676T2 (en)
ES (1) ES2232397T3 (en)
FR (1) FR2800797B1 (en)
RU (1) RU2256082C2 (en)
UA (1) UA67818C2 (en)
WO (1) WO2001034946A1 (en)

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US7665958B2 (en) 2005-03-24 2010-02-23 Alstom Technology Ltd. Heat accumulation segment
WO2006100233A1 (en) * 2005-03-24 2006-09-28 Alstom Technology Ltd Heat accumulation segment
WO2006100235A1 (en) * 2005-03-24 2006-09-28 Alstom Technology Ltd Heat accumulation segment for sealing a flow channel of a turbine engine
US7665957B2 (en) 2005-03-24 2010-02-23 Alstom Technology Ltd Heat shield for sealing a flow channel of a turbine engine
US7658593B2 (en) 2005-03-24 2010-02-09 Alstom Technology Ltd Heat accumulation segment
WO2006100237A1 (en) * 2005-03-24 2006-09-28 Alstom Technology Ltd Heat accumulation segment
KR101259205B1 (en) * 2005-03-24 2013-04-29 알스톰 테크놀러지 리미티드 Heat accumulation segment
WO2007016220A2 (en) * 2005-07-30 2007-02-08 United Technologies Corporation Stator assembly
WO2007016220A3 (en) * 2005-07-30 2007-05-18 United Technologies Corp Stator assembly
US8182216B2 (en) 2006-12-27 2012-05-22 Techspace Aero Connecting system with jaws of two ferrules, including a compressor
EP1939459A1 (en) * 2006-12-27 2008-07-02 Techspace aero System with jaws for connecting two flanges, in particular for a compressor shroud
FR2921410A1 (en) * 2007-09-24 2009-03-27 Snecma Sa RING SECTOR INTERLOCKING DEVICE ON A TURBOMACHINE HOUSING, COMPRISING MEANS FOR ITS PRETENSION
US8038393B2 (en) 2007-09-24 2011-10-18 Snecma Member for locking ring sectors onto a turbomachine casing, comprising means allowing it to be grasped
EP2039885A1 (en) * 2007-09-24 2009-03-25 Snecma Element for locking ring sectors on the casing of a turbomachine, comprising handling means
EP2060750A1 (en) * 2007-11-13 2009-05-20 Snecma Stage of a turbine or compressor, in particular of a turbomachine
US8133013B2 (en) 2007-11-13 2012-03-13 Snecma Stage of a turbine or compressor, particularly for a turbomachine
FR2923526A1 (en) * 2007-11-13 2009-05-15 Snecma Sa TURBINE OR TURBOMACHINE COMPRESSOR STAGE
US8277179B2 (en) 2007-11-13 2012-10-02 Snecma Turbine or compressor stage for a turbomachine
FR2923527A1 (en) * 2007-11-13 2009-05-15 Snecma Sa STAGE OF TURBINE OR COMPRESSOR, IN PARTICULAR TURBOMACHINE
EP2060744A1 (en) * 2007-11-13 2009-05-20 Snecma Stage of a turbine or turbomachine compressor
RU2498088C2 (en) * 2008-05-16 2013-11-10 Снекма Fastening assembly for device to fix ring sections on gas-turbine engine casing, device to fix ring sections on gas-turbine engine casing, turbine of gas-turbine engine and gas-turbine engine
CN102272419A (en) * 2009-03-09 2011-12-07 斯奈克玛 Turbine ring assembly
US9080463B2 (en) 2009-03-09 2015-07-14 Snecma Turbine ring assembly
WO2010103213A1 (en) * 2009-03-09 2010-09-16 Snecma Turbine ring assembly
FR2942845A1 (en) * 2009-03-09 2010-09-10 Snecma High pressure turbine ring assembly for gas turbine of aviation engine, has ring sectors with pie shaped section, and upstream and downstream end portions of tabs maintained without radial clearance by metallic ring support structure
FR2942844A1 (en) * 2009-03-09 2010-09-10 Snecma High pressure turbine shroud assembly for e.g. aeronautical gas turbine engine, has ring sector axially maintained by mutual engagement of groove and rib on supporting surfaces opposite to anchoring tab and flange of support structure
FR2955359A1 (en) * 2010-01-21 2011-07-22 Snecma Turbine stage for turbine engine e.g. turbojet or turbo propeller of airplane, has casing whose annular attachment radially extends towards upstream end of sectorized ring, where radial clearance is determined between casing and ring
FR2955898A1 (en) * 2010-02-02 2011-08-05 Snecma Turbine-stage for use in e.g. turboprop engine in airplane, has groove including sidewalls with annular rib in which annular seal is housed, where seal is clamped between bottom of groove and upstream edge of ring
EP2653662A1 (en) * 2012-04-17 2013-10-23 General Electric Company Mica-based seals for gas turbine shroud retaining clip
CN105579670A (en) * 2013-08-13 2016-05-11 斯奈克玛 Improvement for the locking of blade-supporting components
FR3009739A1 (en) * 2013-08-13 2015-02-20 Snecma IMPROVEMENT FOR LOCKING AUBAGE SUPPORT PARTS
FR3009740A1 (en) * 2013-08-13 2015-02-20 Snecma IMPROVEMENT FOR LOCKING AUBAGE SUPPORT PARTS
WO2015022468A1 (en) * 2013-08-13 2015-02-19 Snecma Improvement for the locking of blade-supporting components
US10247039B2 (en) 2013-08-13 2019-04-02 Safran Aircraft Engines Locking of blade-supporting components
EP3093455A1 (en) * 2015-05-11 2016-11-16 General Electric Company Shroud retention system with keyed retention clips
US9828879B2 (en) 2015-05-11 2017-11-28 General Electric Company Shroud retention system with keyed retention clips
US9932901B2 (en) 2015-05-11 2018-04-03 General Electric Company Shroud retention system with retention springs
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WO2019048766A1 (en) * 2017-09-06 2019-03-14 Safran Aircraft Engines Turbine assembly with ring segments
CN111051649A (en) * 2017-09-06 2020-04-21 赛峰飞机发动机公司 Turbine assembly with ring segment
US11149574B2 (en) 2017-09-06 2021-10-19 Safran Aircraft Engines Turbine assembly with ring segments
CN111051649B (en) * 2017-09-06 2022-04-01 赛峰飞机发动机公司 Turbine assembly with ring segment

Also Published As

Publication number Publication date
JP2003514182A (en) 2003-04-15
CA2359049A1 (en) 2001-05-17
KR20010089800A (en) 2001-10-08
EP1099826B1 (en) 2005-01-26
RU2256082C2 (en) 2005-07-10
WO2001034946A1 (en) 2001-05-17
DE60017676T2 (en) 2005-12-29
UA67818C2 (en) 2004-07-15
JP4181323B2 (en) 2008-11-12
FR2800797A1 (en) 2001-05-11
CA2359049C (en) 2009-01-13
KR100724779B1 (en) 2007-06-04
ES2232397T3 (en) 2005-06-01
DE60017676D1 (en) 2005-03-03
FR2800797B1 (en) 2001-12-07
US6575697B1 (en) 2003-06-10

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