EP0243274A1 - Sectional turbine shroud - Google Patents

Sectional turbine shroud Download PDF

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Publication number
EP0243274A1
EP0243274A1 EP87400934A EP87400934A EP0243274A1 EP 0243274 A1 EP0243274 A1 EP 0243274A1 EP 87400934 A EP87400934 A EP 87400934A EP 87400934 A EP87400934 A EP 87400934A EP 0243274 A1 EP0243274 A1 EP 0243274A1
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EP
European Patent Office
Prior art keywords
axial
sector
face
circumferential
sectors
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
EP87400934A
Other languages
German (de)
French (fr)
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EP0243274B1 (en
Inventor
Carmen Miraucourt
Rémy Paul Charles Ritt
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0243274A1 publication Critical patent/EP0243274A1/en
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Publication of EP0243274B1 publication Critical patent/EP0243274B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—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
    • F01D11/08—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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals

Definitions

  • the present invention relates to a turbine ring with sectored elements of ceramic composite entering the stator part of a turbomachine.
  • FR-A 2 371 575 describes a gas turbine ring comprising an annular support in two parts fixed inside the turbine casing and a ring made of a ceramic material which has good properties in abradability and erosion, good resistance to high temperatures and which acts as a thermal barrier.
  • This ceramic material ring is formed by sectors.
  • a particular method of mounting the ceramic sectors in the metal support, calling in particular on elastic means, aims to ensure good service behavior, taking into account the differential thermal expansions generating mechanical stresses between ceramic elements and metal support and properties of weak ductility and relative brittleness of the ceramic material used.
  • the invention thus aims to ensure the seals, both on the upstream side and on the downstream side, defined with respect to the normal direction of circulation of the gases in the turbomachine, as well as an improved positioning of the sectors and the invention seeks a particular mode of mounting of the ceramic ring sectors which allows the sectors to deform without inducing excessive mechanical stresses in the sectors, and in particular tensile stresses on the external face of the sectors.
  • a turbine ring according to the invention of the aforementioned kind characterized in that the two annular support parts cooperate with each other by means of an axial annular groove and of a sliding axial male part and each comprise, in a radially inner part, respectively an annular axial U-shaped groove, the inner face of the lower branch of which is respectively circumferential and cooperates with the radially inner face of an axial rim of the sectors and the inner face of the upper branch cooperates with the radially facing exterior of an axial edge of the sectors, face which comprises on each sector at least one flat zone connected to at least one circumferential zone of the sector face.
  • the radially external part of a first annular support part is blocked between a radially internal flange of the turbine casing and a cylindrical part extended by a radial flange fixed between two radial flanges of the casing
  • the radially external part of a second part of the annular support comprises an axial flange sliding in an annular axial groove formed in a radially internal flange of the turbine casing and a flexible annular ferrule fixed at one end to a flange of the turbine casing at its other end in axial support on the radially inner part of the second part of the annular support, in line with the corresponding axial edge of the sectors.
  • At least one flat area can also be provided on the radially inner face of an axial rim of the sectors.
  • a part of the casing of a gas turbine has been designated by 1.
  • This part of the casing 1 respectively has at each end an upstream annular radial flange 2 and a downstream annular radial flange 3, both directed outwards, the upstream and downstream being defined with respect to the normal direction of gas flow in the turbomachine to which the turbine belongs.
  • the housing part 1 also comprises two annular radial flanges directed towards the longitudinal axis of the machine, respectively upstream 4 and downstream 5.
  • In the radially internal downstream flange 5 is formed an axial annular groove 6.
  • Upstream is located a part 7 housing cooperating with the radial flange 2 of the part 1 of the housing by means of an annular radial flange 8 directed outwards.
  • Downstream is located a part 9 of the casing cooperating with the radial flange 3 of part 1 of the casing by means of an annular radial flange 10 directed towards the outside.
  • a turbine ring 11 composed of a first annular support part 12 arranged on the upstream side, a second annular support part 13 arranged on the downstream side and a ring 14 sealing.
  • the first annular support part 12 comprises a radially external part 15, an intermediate part 16 and a radially internal part 17.
  • an axial annular groove 18 open downstream.
  • an axial annular groove 19 in the shape of a coated U, open downstream, having an upper branch 20 with internal face 21 and a lower branch 22 with internal face 23.
  • the second part 13 of annular support comprises a cylindrical element 24 directed upstream from a radially median zone of the part 13.
  • the parts 12 and 13 of the annular support cooperate by means of the groove 18 and of an axial male part 25 sliding at the end of the cylindrical element 24.
  • the radially outer part of the second annular support part 13 has an axial flange 26 directed upstream.
  • the second part 13 of annular support comprises, in its radially inner part 27, an axial groove 28 in the shape of a coated U, open upstream, having an upper branch 29 with internal face 30 and a lower branch 31 with an internal face 32.
  • the sealing ring 14 consists of a circumferential succession of contiguous sectors 14a, made of a suitable ceramic material such as a known composite formed of fibers embedded in a matrix of the same material and which has properties of good resistance to high temperatures, good properties in abradability and erosion and low thermal conductivity capable of giving it a role of thermal barrier.
  • Each ceramic sector 14a has on its axial edges, respectively an upstream circumferential rim 33 and a downstream circumferential rim 34, which cooperate with the axial grooves of the annular support, respectively 19 upstream and 28 downstream.
  • the radially inner face 33a and 34a of the axial flanges 33 and 34 of the sectors 14a is circumferential and is therefore in contact over its entire surface with the inner face 23 and 32 respectively of the lower branches 22 and 31 forming the U-shaped axial grooves 19 and 28.
  • the internal faces 21 and 30 of the upper branches 20 and 29 forming the axial U-shaped grooves 19 and 28, have a polygonal peripheral shape.
  • each side of the polygon is placed in line with a sector.
  • each sector 14a has a radially outer face 33b and 34b of the axial flanges 33 and 34 respectively comprising a flat zone 33c or, similarly at the other end, 34c, located in the middle zone of each sector and on which takes place between the sector 14a and the support parts 12 and 13, as shown in FIG. 1.
  • a radial flange 35 of a cylindrical piece 36 disposed inside the casing 1 of the turbine and concentrically thereto.
  • the downstream end 37 of the cylindrical part 36 maintains the radially outer part 15 of the first portion 12 of annular support 5 bearing against the upstream inner flange 4 casing.
  • a radial flange 38 of a flexible annular ferrule 39 is inserted and fixed, the other end (output 40 is axially supported on the radially inner part 27 of the second part 13 ring support.
  • the turbine ring according to the invention which has just been described makes it possible to ensure the upstream and downstream seals. Indeed, permanent contact is ensured between, on the one hand, the respectively upstream and downstream edges of the axial flanges, respectively 33 and 34, of the ring sectors 14a and the bottoms of the axial grooves, respectively 19 and 28, of somewhere else.
  • the axial retention provided by the end 37 of the cylindrical piece 36 on the inner flange 4 of the casing and by the end 40 of the ferrule 39 makes it possible, thanks to the elastic flexibility of the ferrule 39, to make up for the differences in axial dilations of thermal origin between the ring sectors 14a and the turbine casing 1.
  • the tongues 41 are engaged axially in grooves 42 and 43 formed at the same radial level on the facing flanks of the contiguous sectors 14a and thus ensure sealing between said sectors.
  • a means of locking in rotation for example a pin 44, is provided between an axial rim, for example the axial rim 34 of a sector 14a, and the upper branch 29 of the axial groove 28 of the second part 13 of annular support.
  • the present invention is not limited to the embodiment described above. It encompasses all of its variants, only a few of which will be indicated below, by way of nonlimiting examples.
  • FIG. 3 Such an alternative embodiment of the invention is shown in FIG. 3.
  • the flat areas 133c formed on the radially outer face of the axial rim 133 of each sector 14a are carried over to each circumferential end of the sector, upstream side and so are even for the flat areas 134c of the axial flanges 134, downstream side.
  • the respective internal faces 121 and 130 of the upper branches 120 and 129 of the axial grooves 19 and 28 of the annular support 12-13 (shown in FIG. 1) are circumferential.
  • the contact zone between the outer face of each sector 14a and the axial groove face is located in the circumferential middle zone of each sector and the circumferential zones of end have a clearance j between the outer sector face and the cooperating groove face.
  • the ring sectors 14a can deform under the action of a thermal gradient without undergoing excessive mechanical stresses which would be, in the absence of the mounting method. provided by the invention, capable of causing u ⁇ à2 deterioration of the sectors and defects in service performance of the turbine ring.
  • FIG. 4 represents another possibility which constitutes an alternative embodiment of the invention.
  • the groove face cooperating with the outer face of the ring sectors 14a is circumferential and this radially outer sector face 14a has a flat area at each circumferential end of the axial rim.
  • a third flat area, respectively 233c and 234c is provided in the circumferential middle area of each axial sector rim 14a.
  • each sector 14a has two spaced circumferential zones, respectively 233d on the upstream axial flange 33 and 234d on the downstream axial flange 34 (flanges shown in Figure 1) which are in contact with the circumferential groove face.
  • a minimization of the mechanical stresses exerted on the sectors 14a under the effect of the thermal gradient is obtained in this way.
  • FIG. 5 represents this new variant applied to the embodiment of FIG. 4.
  • the radially inner face of the axial edges 33 and 34 of sectors 14a instead of being circumferential as shown in 33a and 34a in FIG.

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

Abstract

Un anneau de turbine est constitué d'un support annulaire en deux parties (12,13) et d'un anneau (14) d'étanchéité en secteurs céramiques (14a). Les deux parties (12,13) de support coopèrent par une gorge axiale (18) et une partie mâle coulissante (25). Chacune comporte une rainure annulaire axiale (19,28) dans laquelle est engagé le rebord axial (33,34) de chaque secteur (14a). Les faces coopérantes radialement intérieures (33a,34a,21,30) respectivement du rebord et de la rainure sont circonférentielles alors que la face radialement extérieure (33b,34b) de chaque secteur (14a) comporte au moins une zone plate (33c,34c). Ladite face (21,30) de rainure peut être polygonale.A turbine ring consists of an annular support in two parts (12,13) and a sealing ring (14) in ceramic sectors (14a). The two support parts (12, 13) cooperate by an axial groove (18) and a sliding male part (25). Each has an axial annular groove (19,28) in which is engaged the axial flange (33,34) of each sector (14a). The radially inner cooperating faces (33a, 34a, 21.30) respectively of the rim and the groove are circumferential while the radially outer face (33b, 34b) of each sector (14a) comprises at least one flat area (33c, 34c ). Said groove face (21,30) can be polygonal.

Description

La présente invention concerne un anneau de turbine à éléments sectorisés en composite céramique entrant dans la partie statorique d'une turbomachine.The present invention relates to a turbine ring with sectored elements of ceramic composite entering the stator part of a turbomachine.

FR-A 2 371 575 décrit un anneau de turbine à gaz comportant un support annulaire en deux parties fixé à l'intérieur du carter de turbine et un anneau en un matériau céramique qui présente de bonnes propriétés en abradabilité et érosion, une bonne tenue aux hautes températures et qui joue un rôle de barrière thermique. Cet anneau en matériau céramique est formé de secteurs. Un mode particulier de montage des secteurs céramiques dans le support métallique faisant appel notamment à des moyens élastiques vise à assurer une bonne tenue en service, en tenant compte des dilatations thermiques différentielles génératrices de contraintes mécaniques entre éléments céramiques et support métallique et des propriétés de faible ductilité et de relative fragilité du matériau céramique utilisé.FR-A 2 371 575 describes a gas turbine ring comprising an annular support in two parts fixed inside the turbine casing and a ring made of a ceramic material which has good properties in abradability and erosion, good resistance to high temperatures and which acts as a thermal barrier. This ceramic material ring is formed by sectors. A particular method of mounting the ceramic sectors in the metal support, calling in particular on elastic means, aims to ensure good service behavior, taking into account the differential thermal expansions generating mechanical stresses between ceramic elements and metal support and properties of weak ductility and relative brittleness of the ceramic material used.

Ces dispositions connues se sont révélées toutefois insuffisantes pour certaines applications aux turbomachines où de hautes performances et en particulier des températures élevées de fonctionnement sont recherchées. L'invention vise ainsi à assurer les étanchéités, tant du côté amont que du côté aval, définis par rapport au sens normal de circulation des gaz dans la turbomachine, ainsi qu'un positionnement amélioré des secteurs et l'invention recherche un mode particulier de montage des secteurs d'anneau en céramique qui permette aux secteurs de se déformer sans induire de contraintes mécaniques excessives dans les secteurs, et en particulier des contraintes de traction sur la face externe des secteurs.These known arrangements have however proved to be insufficient for certain applications in turbomachinery where high performance and in particular high operating temperatures are desired. The invention thus aims to ensure the seals, both on the upstream side and on the downstream side, defined with respect to the normal direction of circulation of the gases in the turbomachine, as well as an improved positioning of the sectors and the invention seeks a particular mode of mounting of the ceramic ring sectors which allows the sectors to deform without inducing excessive mechanical stresses in the sectors, and in particular tensile stresses on the external face of the sectors.

Ces résultats avantageux sont obtenus et les inconvénients précédents évités par un anneau de turbine selon l'invention du genre précité, caractérisé en ce que les deux parties de support annulaire coopèrent entre elles au moyen d'une gorge annulaire axiale et d'une partie mâle axiale coulissante et comportent chacune, dans une partie radialement intérieure, respectivement une rainure annulaire axiale en U couché dont respectivement la face interne de la branche inférieure est circonférentielle et coopère avec la face radialement intérieure d'un rebord axial des secteurs et la face interne de la branche supérieure coopère avec la face radialement extérieure d'un rebord axial des secteurs, face qui comporte sur chaque secteur au moins une zone plate raccordée à au moins une zone circonférentielle de face de secteur.These advantageous results are obtained and the disadvantages precedents avoided by a turbine ring according to the invention of the aforementioned kind, characterized in that the two annular support parts cooperate with each other by means of an axial annular groove and of a sliding axial male part and each comprise, in a radially inner part, respectively an annular axial U-shaped groove, the inner face of the lower branch of which is respectively circumferential and cooperates with the radially inner face of an axial rim of the sectors and the inner face of the upper branch cooperates with the radially facing exterior of an axial edge of the sectors, face which comprises on each sector at least one flat zone connected to at least one circumferential zone of the sector face.

Avantageusement, la partie radialement extérieure d'une première partie de support annulaire est bloquée entre une bride radialement interne du carter de turbine et une pièce cylindrique prolongée par une bride radiale fixée entre deux brides radiales du carter, et la partie radialement extérieure d'une deuxième partie du support annulaire comporte une bride axiale coulissant dans une gorge axiale annulaire ménagée dans une bride radialement interne du carter de turbine et une virole annulaire souple fixée à une extrémité à une bride du carter de turbine a son autre extrémité en appui axial sur la partie radialement intérieure de la deuxième partie du support annulaire, au droit du bord axial correspondant des secteurs.Advantageously, the radially external part of a first annular support part is blocked between a radially internal flange of the turbine casing and a cylindrical part extended by a radial flange fixed between two radial flanges of the casing, and the radially external part of a second part of the annular support comprises an axial flange sliding in an annular axial groove formed in a radially internal flange of the turbine casing and a flexible annular ferrule fixed at one end to a flange of the turbine casing at its other end in axial support on the radially inner part of the second part of the annular support, in line with the corresponding axial edge of the sectors.

Avantageusement, au moins une zone plate peut également être ménagée sur la face radialement intérieure d'un rebord axial des secteurs.Advantageously, at least one flat area can also be provided on the radially inner face of an axial rim of the sectors.

A titre d'exemple, on a décrit ci-dessous un mode de réalisation d'un anneau de turbine conforme à la présente invention, ainsi que deux variantes s'appliquant à cette forme de réalisation d'où il ressort d'autres caractéristiques et avantages de l'invention, en référence aux dessins annexés sur lesquels :

  • - la figure 1 est une vue partielle, en coupe par un demi-plan axial, du carter d'une turbine, muni d'un anneau selon la présente invention ;
  • - la figure 2 est une vue partielle, en section transversale, selon les lignes II-II de la figure 1, du rebord axial des secteurs d'anneau montés dans leur logement ;
  • - la figure 3 est une vue analogue à la figure 2, représentant une première variante de réalisation ;
  • - la figure 4 est une vue partielle analogue aux figures 2 et 3, représentant une deuxième variante de réalisation.
  • - la figure 5 est une vue partielle analogue aux figures 2, 3 et 4, représentant une troisième variante de réalisation.
By way of example, an embodiment of a turbine ring according to the present invention has been described below, as well as two variants applying to this embodiment from which other characteristics emerge. ticks and advantages of the invention, with reference to the accompanying drawings in which:
  • - Figure 1 is a partial view, in section through an axial half-plane, of the casing of a turbine, provided with a ring according to the present invention;
  • - Figure 2 is a partial view, in cross section, along lines II-II of Figure 1, of the axial flange of the ring sectors mounted in their housing;
  • - Figure 3 is a view similar to Figure 2, showing a first alternative embodiment;
  • - Figure 4 is a partial view similar to Figures 2 and 3, showing a second alternative embodiment.
  • - Figure 5 is a partial view similar to Figures 2, 3 and 4, showing a third alternative embodiment.

Sur la figure 1, on a désigné par 1 une partie du carter d'une turbine à gaz. Cette partie du carter 1 comporte respectivement à chaque extrémité une bride radiale annulaire amont 2 et une bride radiale annulaire aval 3, toutes deux dirigées vers l'extérieur, l'amont et l'aval étant définis par rapport au sens normal de circulation des gaz dans la turbomachine à laquelle appartient la turbine. La partie de carter 1 comporte également deux brides radiales annulaires dirigées vers l'axe longitudinal de la machine, respectivement amont 4 et aval 5. Dans la bride radialement interne aval 5 est ménagée une gorge annulaire axiale 6. En amont est située une partie 7 de carter coopérant avec la bride radiale 2 de la partie 1 du carter au moyen d'une bride radiale annulaire 8 dirigée vers l'extérieur. En aval, est située une partie 9 du carter coopérant avec la bride radiale 3 de la partie 1 du carter au moyen d'une bride radiale annulaire 10 dirigée vers l'extérieur.In FIG. 1, a part of the casing of a gas turbine has been designated by 1. This part of the casing 1 respectively has at each end an upstream annular radial flange 2 and a downstream annular radial flange 3, both directed outwards, the upstream and downstream being defined with respect to the normal direction of gas flow in the turbomachine to which the turbine belongs. The housing part 1 also comprises two annular radial flanges directed towards the longitudinal axis of the machine, respectively upstream 4 and downstream 5. In the radially internal downstream flange 5 is formed an axial annular groove 6. Upstream is located a part 7 housing cooperating with the radial flange 2 of the part 1 of the housing by means of an annular radial flange 8 directed outwards. Downstream, is located a part 9 of the casing cooperating with the radial flange 3 of part 1 of the casing by means of an annular radial flange 10 directed towards the outside.

A l'intérieur du carter 1 de turbine est monté un anneau de turbine 11 composé d'une première partie 12 de support annulaire disposée du côté amont, d'une deuxième partie 13 de support annulaire disposée du côté aval et d'un anneau 14 d'étanchéité. La première partie 12 de support annulaire comporte une partie 15 radialement extérieure, une partie intermédiaire 16 et une partie 17 radialement intérieure. Dans la partie intermédiaire 16 est ménagée une gorge annulaire axiale 18 ouverte vers l'aval. Dans la partie intérieure 17 est ménagée une rainure annulaire axiale 19 en forme de U couché, ouvert vers l'aval, présentant une branche supérieure 20 à face interne 21 et une branche inférieure 22 à face interne 23. La deuxième partie 13 de support annulaire comporte un élément cylindrique 24 dirigé vers l'amont à partir d'une zone radialement médiane de la partie 13. Les parties 12 et 13 du support annulaire coopèrent au moyen de la gorge 18 et d'une partie mâle 25 axiale coulissante d'extrémité de l'élément cylindrique 24. La partie radialement extérieure de la deuxième partie 13 de support annulaire comporte un rebord axial 26 dirigé vers l'amont. De manière analogue à la première partie 12, la deuxième partie 13 de support annulaire comporte, dans sa partie 27 radialement intérieure, une rainure axiale 28 en forme de U couché, ouvert vers l'amont, présentant une branche supérieure 29 à face interne 30 et une branche inférieure 31 à face interne 32.Inside the turbine casing 1 is mounted a turbine ring 11 composed of a first annular support part 12 arranged on the upstream side, a second annular support part 13 arranged on the downstream side and a ring 14 sealing. The first annular support part 12 comprises a radially external part 15, an intermediate part 16 and a radially internal part 17. In the intermediate part 16 is formed an axial annular groove 18 open downstream. In the inner part 17 is formed an axial annular groove 19 in the shape of a coated U, open downstream, having an upper branch 20 with internal face 21 and a lower branch 22 with internal face 23. The second part 13 of annular support comprises a cylindrical element 24 directed upstream from a radially median zone of the part 13. The parts 12 and 13 of the annular support cooperate by means of the groove 18 and of an axial male part 25 sliding at the end of the cylindrical element 24. The radially outer part of the second annular support part 13 has an axial flange 26 directed upstream. Similarly to the first part 12, the second part 13 of annular support comprises, in its radially inner part 27, an axial groove 28 in the shape of a coated U, open upstream, having an upper branch 29 with internal face 30 and a lower branch 31 with an internal face 32.

L'anneau d'étanchéité 14 est constitué d'une succession circonférentielle de secteurs 14a contigus, en un matériau céramique adéquat tel qu'un composite connu formé de fibres noyées dans une matrice en la même matière et qui présente des propriétés de bonne tenue aux températures élevées, de bonnes propriétés en abradabilité et érosion et de faible conductivité thermique susceptible de lui conférer un rôle de barrière thermique. Chaque secteur céramique 14a comporte sur ses bords axiaux, respectivement un rebord circonférentiel amont 33 et un rebord circonférentiel aval 34, qui coopèrent avec les rainures axiales du support annulaire, respectivement 19 à l'amont et 28 à l'aval. La face radialement intérieure 33a et 34a des rebords axiaux 33 et 34 des secteurs 14a est circonférentielle et est par conséquent en contact sur toute sa surface avec la face interne respectivement 23 et 32 des branches inférieures 22 et 31 formant les rainures axiales en U 19 et 28.The sealing ring 14 consists of a circumferential succession of contiguous sectors 14a, made of a suitable ceramic material such as a known composite formed of fibers embedded in a matrix of the same material and which has properties of good resistance to high temperatures, good properties in abradability and erosion and low thermal conductivity capable of giving it a role of thermal barrier. Each ceramic sector 14a has on its axial edges, respectively an upstream circumferential rim 33 and a downstream circumferential rim 34, which cooperate with the axial grooves of the annular support, respectively 19 upstream and 28 downstream. The radially inner face 33a and 34a of the axial flanges 33 and 34 of the sectors 14a is circumferential and is therefore in contact over its entire surface with the inner face 23 and 32 respectively of the lower branches 22 and 31 forming the U-shaped axial grooves 19 and 28.

Selon le mode de réalisation représenté à la figure 2, les faces internes 21 et 30 des branches supérieures 20 et 29 formant les rainures axiales en U 19 et 28, ont une forme périphérique polygonale. De préférence, chaque côté du polygone est placé au droit d'un secteur. Dans ce cas, chaque secteur 14a présente une face radialement extérieure 33b et 34b des rebords axiaux 33 et 34 respectivement comportant une zone plate 33c ou, de manière analogue à l'autre extrémité, 34c, située dans la zone médiane de chaque secteur et sur laquelle s'effectue l'appui entre le secteur 14a et les parties de support 12 et 13, comme représenté à la figure 1.According to the embodiment shown in Figure 2, the internal faces 21 and 30 of the upper branches 20 and 29 forming the axial U-shaped grooves 19 and 28, have a polygonal peripheral shape. Preferably, each side of the polygon is placed in line with a sector. In this case, each sector 14a has a radially outer face 33b and 34b of the axial flanges 33 and 34 respectively comprising a flat zone 33c or, similarly at the other end, 34c, located in the middle zone of each sector and on which takes place between the sector 14a and the support parts 12 and 13, as shown in FIG. 1.

Entre les brides radialement extérieures 2 et 7 du carter est insérée et fixée une bride radiale 35 d'une pièce cylindrique 36 disposée à l'intérieur du carter 1 de turbine et concentriquement à lui. L'extrémité aval 37 de la pièce cylindrique 36 maintient la partie radialement extérieure 15 de la première partie 12 de support 5 annulaire en appui contre la bride interne amont 4 de carter. De même entre les brides radialement extérieures 3 et 10 de carter est insérée et fixée une bride radiale 38 d'une virole 39 annulaire souple dont l'autre ext(émité 40 est en appui axial sur la partie radialement intérieure 27 de la deuxième partie 13 de support annulaire.Between the radially outer flanges 2 and 7 of the casing is inserted and fixed a radial flange 35 of a cylindrical piece 36 disposed inside the casing 1 of the turbine and concentrically thereto. The downstream end 37 of the cylindrical part 36 maintains the radially outer part 15 of the first portion 12 of annular support 5 bearing against the upstream inner flange 4 casing. Likewise, between the radially outer flanges 3 and 10 of the casing, a radial flange 38 of a flexible annular ferrule 39 is inserted and fixed, the other end (output 40 is axially supported on the radially inner part 27 of the second part 13 ring support.

En fonctionnement, particulièrement lorsque des températures élevées à l'entrée de la turbine sont atteintes, l'anneau de turbine selon l'invention qui vient d'être décrite permet d'assurer les étanchéités amont et aval. En effet, un contact permanent est assuré entre, d'une part, les bords respectivement amont et aval des rebords axiaux, respectivement 33 et 34, des secteurs 14a d'anneau et les fonds des rainures axiales, respectivement 19 et 28, d'autre part. Le maintien axial assuré par l'extrémité 37 de la pièce cylindrique 36 sur la bride intérieure 4 de carter et par l'extrémité 40 de la virole 39 permet, grâce à la souplesse élastique de la virole 39, de rattraper les différences des dilatations axiales d'origine thermique entre les secteurs 14a d'anneau et le carter 1 de turbine. Par ailleurs, la limitation du contact entre la face extérieure, respectivement 33b et 34b, de chaque rebord axial 33 et 34 de secteur 14a et la face interne, respectivement 21 et 30, de la branche supérieure 20 et 29 de rainure en U 19 et 28, à une zone médiane plate, respectivement 33c et 34c, permet toute déformation des secteurs d'anneau 14a sous l'action des gradients thermiques sans l'apparition de contraintes mécaniques supérieures aux capacités de résistance du matériau composite céramique constituant lesdits secteurs 14a, en particulier la résistance à la traction sur la face extérieure des secteurs 14a. En même temps, un maintien radial et circonférentiel des secteurs 14a est ainsi assuré. De plus, les languettes 41 sont engagées axialement dans des rainures 42 et 43 pratiquées au même niveau radial sur les flancs en regards des secteurs 14a contigus et assurent ainsi l'étanchéité entre lesdits secteurs. En outre, de manière connue, un moyen de blocage en rotation, par exemple un pion 44, est prévu entre un rebord axial, par exemple le rebord axial 34 d'un secteur 14a, et la branche supérieure 29 de la rainure axiale 28 de la deuxième partie 13 de support annulaire.In operation, particularly when high temperatures at the inlet of the turbine are reached, the turbine ring according to the invention which has just been described makes it possible to ensure the upstream and downstream seals. Indeed, permanent contact is ensured between, on the one hand, the respectively upstream and downstream edges of the axial flanges, respectively 33 and 34, of the ring sectors 14a and the bottoms of the axial grooves, respectively 19 and 28, of somewhere else. The axial retention provided by the end 37 of the cylindrical piece 36 on the inner flange 4 of the casing and by the end 40 of the ferrule 39 makes it possible, thanks to the elastic flexibility of the ferrule 39, to make up for the differences in axial dilations of thermal origin between the ring sectors 14a and the turbine casing 1. Furthermore, limiting the contact between the outer face, respectively 33b and 34b, of each axial rim 33 and 34 of sector 14a and the inner face, respectively 21 and 30, of the upper branch 20 and 29 of U-shaped groove 19 and 28, at a flat central zone, respectively 33c and 34c, allows any deformation of the ring sectors 14a under the action of thermal gradients without the appearance of mechanical stresses greater than the resistance capacities of the ceramic composite material constituting said sectors 14a, in particular the tensile strength on the outer face of the sectors 14a. At the same time, a radial and circumferential retention of the sectors 14a is thus ensured. In addition, the tongues 41 are engaged axially in grooves 42 and 43 formed at the same radial level on the facing flanks of the contiguous sectors 14a and thus ensure sealing between said sectors. Furthermore, in known manner, a means of locking in rotation, for example a pin 44, is provided between an axial rim, for example the axial rim 34 of a sector 14a, and the upper branch 29 of the axial groove 28 of the second part 13 of annular support.

La présente invention n'est pas limitée à la forme de réalisation précédemment décrite. Elle englobe toutes ses variantes, dont quelques unes seulement vont être indiquées ci-après, à titre d'exemples non limitatifs.The present invention is not limited to the embodiment described above. It encompasses all of its variants, only a few of which will be indicated below, by way of nonlimiting examples.

Une telle variante de réalisation de l'invention est représentée à la figure 3. Les zones plates 133c ménagées sur la face radialement extérieure du rebord axial 133 de chaque secteur 14a sont reportées à chaque extrémité circonférentielle de secteur, côté amont et il en est de même pour les zones plates 134c des rebords axiaux 134, côté aval. En outre, selon cette variante de réalisation, les faces internes respectives 121 et 130 des branches supérieures 120 et 129 des rainures axiales 19 et 28 du support annulaire 12-13 (représenté à la figure 1) sont circonférentielles. Ainsi, comme dans la réalisation précédemment décrite en référence aux figures 1 et 2, la zone de contact entre la face extérieure de chaque secteur 14a et la face de rainure axiale est située dans la zone médiane circonférentielle de chaque secteur et les zones circonférentielles d'extrémité présentent un jeu j entre la face extérieure de secteur et la face de rainure coopérante. Comme précédemment, en fonctionnement et en particulier aux températures élevées, les secteurs d'anneau 14a peuvent se déformer sous l'action d'un gradient thermique sans subir de contraintes mécaniques excessives qui seraient, en l'absence du mode de montage prévu par l'invention, susceptibles d'entraîner uÀà2 détérioration des secteurs et des défauts de tenue en service de l'anneau de turbine.Such an alternative embodiment of the invention is shown in FIG. 3. The flat areas 133c formed on the radially outer face of the axial rim 133 of each sector 14a are carried over to each circumferential end of the sector, upstream side and so are even for the flat areas 134c of the axial flanges 134, downstream side. In addition, according to this alternative embodiment, the respective internal faces 121 and 130 of the upper branches 120 and 129 of the axial grooves 19 and 28 of the annular support 12-13 (shown in FIG. 1) are circumferential. Thus, as in the embodiment previously described with reference to Figures 1 and 2, the contact zone between the outer face of each sector 14a and the axial groove face is located in the circumferential middle zone of each sector and the circumferential zones of end have a clearance j between the outer sector face and the cooperating groove face. As before, in operation and in particular at high temperatures, the ring sectors 14a can deform under the action of a thermal gradient without undergoing excessive mechanical stresses which would be, in the absence of the mounting method. provided by the invention, capable of causing uÀà2 deterioration of the sectors and defects in service performance of the turbine ring.

La figure 4 représente une autre possibilité qui constitue une variante de réalisation de l'invention. Comme dans la variante représentée à la figure 3 et précédemment décrite, la face de rainure coopérant avec la face extérieure des secteurs d'anneau 14a est circonférentielle et cette face radialement extérieure de secteur 14a comporte une zone plate à chaque extrémité circonférentielle de rebord axial. Selon la présente variante, une troisième zone plate, respectivement 233c et 234c, est ménagée dans la zone médiane circonférentielle de chaque rebord axial de secteur 14a. De cette manière, chaque secteur 14a présente deux zones circonférentielles espacées, respectivement 233d sur le rebord axial amont 33 et 234d sur le rebord axial aval 34 (rebords représentés à la figure 1) qui sont en contact avec la face circonférentielle de rainure. Comme précédemment, une minimisation des contraintes mécaniques s'exerçant sur les secteurs 14a sous l'effet du gradient thermique est obtenue de cette façon.FIG. 4 represents another possibility which constitutes an alternative embodiment of the invention. As in the variant shown in Figure 3 and previously described, the groove face cooperating with the outer face of the ring sectors 14a is circumferential and this radially outer sector face 14a has a flat area at each circumferential end of the axial rim. According to the present variant, a third flat area, respectively 233c and 234c, is provided in the circumferential middle area of each axial sector rim 14a. In this way, each sector 14a has two spaced circumferential zones, respectively 233d on the upstream axial flange 33 and 234d on the downstream axial flange 34 (flanges shown in Figure 1) which are in contact with the circumferential groove face. As before, a minimization of the mechanical stresses exerted on the sectors 14a under the effect of the thermal gradient is obtained in this way.

Enfin, comme représenté à la figure 5, il peut s'avérer dans certaines applications particulières, souhaitable de porter sur le diamètre interne des secteurs en céramique les mêmes dispositions que celles qui ont été décrites pour leur diamètre externe. Cette variante de réalisation peut être appliquée à chacune des trois variantes de réalisation précédemment décrites en référence respectivement aux figures 2,3 et 4. La figure 5 représente cette nouvelle variante appliquée à la réalisation de la figure 4. Ainsi, la face radialement intérieure des rebords axiaux 33 et 34 des secteurs 14a au lieu d'être circonférentielle comme représenté en 33a et 34a sur la figure 1, présente des zones plates 333c, 433c et 533c et de manière analogue à l'autre extrémité, 333d, 433d et 533d, de manière à assurer dans ce cas un appui régulier des secteurs 14a sur la face interne respectivement, 23 et 32, des branches inférieures 22 et 31 formant les rainures axiales en U 19 et 28 (voir figure 1).Finally, as shown in FIG. 5, in certain particular applications, it may prove desirable to wear the same arrangements on the internal diameter of the ceramic sectors as those which have been described for their external diameter. This alternative embodiment can be applied to each of the three alternative embodiments previously described with reference to FIGS. 2, 3 and 4. FIG. 5 represents this new variant applied to the embodiment of FIG. 4. Thus, the radially inner face of the axial edges 33 and 34 of sectors 14a instead of being circumferential as shown in 33a and 34a in FIG. 1, has flat zones 333c, 433c and 533c and similarly at the other end, 333d, 433d and 533d, so as to ensure in this case regular support of the sectors 14a on the internal face respectively, 23 and 32, of the lower branches 22 and 31 forming the axial U-shaped grooves 19 and 28 (see FIG. 1).

Claims (9)

1. Anneau de turbine comportant un support annulaire en deux parties (12 et 13) fixé à l'intérieur du carter de la turbine et un anneau d'étanchéité (14) constitué d'une succession de secteurs (14a) contigus en un matériau composite céramique caractérisé en ce que les deux parties (12, 13) de support annulaire coopèrent entre elles au moyen d'une gorge annulaire axiale (18) et d'une partie mâle axiale coulissante (25) et comportent chacune, dans une partie radialement intérieure (17, 27), respectivement une rainure (19, 28) annulaire axiale en U couché dont respectivement la face interne (23, 32) de la branche inférieure (22, 31) est circonférentielle et coopère avec la face (33a, 34a) radialement intérieure d'un rebord axial (33, 34) des secteurs (14a) et la face interne (21, 30) de la branche supérieure (20, 29) coopère avec la face radialement extérieure (33b, 34b) du rebord axial (33, 34) des secteurs (14a), face qui comporte sur chaque secteur (14a) au moins une zone plate (33c, 34c ; 133c, 134c ; 233c, 234c) raccordée à au moins une zone circonférentielle de face de secteur.1. Turbine ring comprising an annular support in two parts (12 and 13) fixed inside the turbine casing and a sealing ring (14) consisting of a succession of contiguous sectors (14a) made of a material ceramic composite, characterized in that the two annular support parts (12, 13) cooperate with each other by means of an axial annular groove (18) and an axial sliding male part (25) and each comprise, in a radially part inner (17, 27), respectively an axial annular groove (19, 28) in a coated U whose respectively the inner face (23, 32) of the lower branch (22, 31) is circumferential and cooperates with the face (33a, 34a ) radially inner to an axial rim (33, 34) of the sectors (14a) and the inner face (21, 30) of the upper branch (20, 29) cooperates with the radially outer face (33b, 34b) of the axial rim (33, 34) of the sectors (14a), face which comprises on each sector (14a) at least one flat area (33c, 3 4c; 133c, 134c; 233c, 234c) connected to at least one circumferential sector face area. 2. Anneau de turbine selon la revendication 1 caractérisé en ce que la face interne (21, 30) de la branche supérieure (20, 29) des rainures (19, 28) du support annulaire (12 et 13) est polygonale et que la zone plate (33c) d'appui des secteurs (14a) est placée dans la zone médiane de chaque secteur (14a), chaque côté dudit polygone étant situé au droit d'un desdits secteurs.2. Turbine ring according to claim 1 characterized in that the internal face (21, 30) of the upper branch (20, 29) of the grooves (19, 28) of the annular support (12 and 13) is polygonal and that the flat area (33c) for supporting the sectors (14a) is placed in the middle zone of each sector (14a), each side of said polygon being situated at the right of one of said sectors. 3. Anneau de turbine selon la revendication 1 caractérisé en ce que chaque secteur (14a) comporte sur sa face radialement extérieure de chaque rebord axial une zone plate (133c, 134c) à chaque extrémité, ces deux zones étant reliées par une zone circonférentielle et la face interne (121, 130) de la branche supérieure (120, 129) des rainures du support annulaire (12 et 13) étant circonférentielle.3. turbine ring according to claim 1 characterized in that each sector (14a) has on its radially outer face of each axial flange a flat area (133c, 134c) at each end, these two areas being connected by a circumferential zone and the internal face (121, 130) of the upper branch (120, 129) of the grooves of the annular support (12 and 13) being circumferential. 4. Anneau de turbine selon la revendication 1 caractérisé - - en ce que chaque secteur (14a) comporte sur sa face radialement extérieure deux zones circonférentielles (233d, 234d) coopérant avec la face interne circonférentielle de la branche supérieure des rainures du support annulaire, lesdites zones circonférentielles de secteur étant respectivement situées entre une zone plate d'extrémité (133c, 134c) et une zone plate médiane (233c, 234c).4. Turbine ring according to claim 1 characterized - - in that each sector (14a) has on its radially outer face two circumferential zones (233d, 234d) cooperating with the inner circumferential face of the upper branch of the grooves of the annular support, said sector circumferential areas being respectively located between a flat end area (133c, 134c) and a middle flat area (233c, 234c). 5. Anneau de turbine selon l'une quelconque des revendications précédentes caractérisé en ce que la partie radialement extérieure (15) d'une première partie (12) de support annulaire est bloquée entre une bride (4) radialement interne du carter (1) de turbine et une pièce cylindrique (36) prolongée par une bride radiale (35) fixée entre deux brides radiales (2, 8) de carter, que la partie radialement extérieure d'une deuxième partie (13) de support annulaire comporte un rebord axial (26) coulissant dans une gorge (6) axiale annulaire ménagée dans une bride (5) radialement interne de carter (1) de turbine et qu'une virole (39) annulaire souple fixée à une extrémité entre deux brides (3, 10) de carter a son autre extrémité (40) en appui axial sur la partie radialement intérieure (27) de la deuxième partie (13) du support annulaire, au droit du bord axial correspondant des secteurs (14a).5. Turbine ring according to any one of the preceding claims, characterized in that the radially external part (15) of a first part (12) of annular support is blocked between a radially internal flange (4) of the casing (1) turbine and a cylindrical part (36) extended by a radial flange (35) fixed between two radial flanges (2, 8) of casing, that the radially outer part of a second annular support part (13) has an axial flange (26) sliding in an annular axial groove (6) formed in a radially internal flange (5) of the turbine casing (1) and that a flexible annular ferrule (39) fixed at one end between two flanges (3, 10) casing at its other end (40) in axial support on the radially inner part (27) of the second part (13) of the annular support, in line with the corresponding axial edge of the sectors (14a). 6. Anneau de turbine selon l'une quelconque des revendications précédentes caractérisé en ce qu'un moyen de blocage en rotation du genre pion (44) est monté entre au moins un secteur (14a) et la branche supérieure (29) de rainure axiale (28) d'une partie (13) de support annulaire.6. Turbine ring according to any one of the preceding claims, characterized in that a locking means in rotation of the pin type (44) is mounted between at least one sector (14a) and the upper branch (29) of axial groove (28) of a part (13) of annular support. 7. Anneau de turbine selon l'une quelconque des revendications précédentes caractérisé en ce que la face radialement intérieure (33a, 34a) du rebord axial (33,34) des secteurs (14a) comporte sur chaque secteur (14a) au moins une zone plate (333c, 333d, 433c, 433d, 533c, 533d) raccordée à au moins une zone circonférentielle de face de secteur.7. Turbine ring according to any one of the preceding claims, characterized in that the radially inner face (33a, 34a) of the axial rim (33,34) of the sectors (14a) comprises on each sector (14a) at least one zone flat (333c, 333d, 433c, 433d, 533c, 533d) connected to at least one circumferential sector face area. 8. Anneau de turbine selon la revendication 7 caractérisé en ce que chaque secteur (14a) comporte sur sa face radialement intérieure de chaque rebord axial une zone plate (333c, 333d, 533c, 533d) à chaque extrémité, ces deux zones étant reliées par une zone circonférentielle.8. Turbine ring according to claim 7 characterized in that each sector (14a) has on its radially inner face of each axial flange a flat area (333c, 333d, 533c, 533d) at each end, these two areas being connected by a circumferential area. 9. Anneau de turbine selon la revendication 7 caractérisé en ce que chaque secteur (14a) comporte sur sa face radialement intérieure une zone plate (333c, 333d, 533c, 533d) à chaque extrémité et une zone plate (433c, 433d) en position médiane, ces zones plates étant reliées respectivement par deux zones circonférentielles.9. Turbine ring according to claim 7 characterized in that each sector (14a) has on its radially inner face a flat area (333c, 333d, 533c, 533d) at each end and a flat area (433c, 433d) in position median, these flat areas being connected respectively by two circumferential areas.
EP87400934A 1986-04-24 1987-04-23 Sectional turbine shroud Expired EP0243274B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8605924 1986-04-24
FR8605924A FR2597921A1 (en) 1986-04-24 1986-04-24 SECTORIZED TURBINE RING

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EP0243274A1 true EP0243274A1 (en) 1987-10-28
EP0243274B1 EP0243274B1 (en) 1989-01-25

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EP (1) EP0243274B1 (en)
DE (1) DE3760045D1 (en)
FR (1) FR2597921A1 (en)

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US10100649B2 (en) 2015-03-31 2018-10-16 Rolls-Royce North American Technologies Inc. Compliant rail hanger
US9759079B2 (en) 2015-05-28 2017-09-12 Rolls-Royce Corporation Split line flow path seals
EP3118419A1 (en) * 2015-07-15 2017-01-18 Siemens Aktiengesellschaft Non-concentrically shaped ring segment
US10422241B2 (en) * 2016-03-16 2019-09-24 United Technologies Corporation Blade outer air seal support for a gas turbine engine
US10060294B2 (en) * 2016-04-15 2018-08-28 Rolls-Royce High Temperature Composites Inc. Gas turbine engine assemblies with ceramic matrix composite components having undulated features
US10392957B2 (en) 2017-10-05 2019-08-27 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having load distribution features
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US10934876B2 (en) * 2018-07-18 2021-03-02 Raytheon Technologies Corporation Blade outer air seal AFT hook retainer
FR3100838B1 (en) * 2019-09-13 2021-10-01 Safran Aircraft Engines TURBOMACHINE SEALING RING
US11149563B2 (en) 2019-10-04 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having axial reaction load distribution features
US11187098B2 (en) 2019-12-20 2021-11-30 Rolls-Royce Corporation Turbine shroud assembly with hangers for ceramic matrix composite material seal segments

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US5137421A (en) * 1989-09-15 1992-08-11 Rolls-Royce Plc Shroud rings
EP0953729A1 (en) * 1998-05-01 1999-11-03 Techspace aero Guide vanes for a turbomachine
US6296442B1 (en) * 1998-05-01 2001-10-02 Techspace Aero Turbomachine stator vane set
WO2004074639A1 (en) * 1998-05-01 2004-09-02 Hung Quac Tran Turbomachine guide bucket
FR3064022A1 (en) * 2017-03-16 2018-09-21 Safran Aircraft Engines TURBINE RING ASSEMBLY
FR3064023A1 (en) * 2017-03-16 2018-09-21 Safran Aircraft Engines TURBINE RING ASSEMBLY
WO2018172653A1 (en) * 2017-03-16 2018-09-27 Safran Aircraft Engines Turbine ring assembly
WO2018172654A1 (en) * 2017-03-16 2018-09-27 Safran Aircraft Engines Turbine ring assembly
CN110506149A (en) * 2017-03-16 2019-11-26 赛峰航空器发动机 Turbine ring assemblies
US11021988B2 (en) 2017-03-16 2021-06-01 Safran Aircraft Engines Turbine ring assembly
US11111822B2 (en) 2017-03-16 2021-09-07 Safran Aircraft Engines Turbine ring assembly

Also Published As

Publication number Publication date
DE3760045D1 (en) 1989-03-02
US4759687A (en) 1988-07-26
FR2597921A1 (en) 1987-10-30
EP0243274B1 (en) 1989-01-25

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