EP3298244B1 - Turbine ring assembly with axial retention - Google Patents

Turbine ring assembly with axial retention Download PDF

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Publication number
EP3298244B1
EP3298244B1 EP16726365.6A EP16726365A EP3298244B1 EP 3298244 B1 EP3298244 B1 EP 3298244B1 EP 16726365 A EP16726365 A EP 16726365A EP 3298244 B1 EP3298244 B1 EP 3298244B1
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EP
European Patent Office
Prior art keywords
ring
support structure
tabs
flanges
sectors
Prior art date
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EP16726365.6A
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German (de)
French (fr)
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EP3298244A1 (en
Inventor
Lucien Henri Jacques QUENNEHEN
Sébastien Serge Francis CONGRATEL
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
Safran Ceramics SA
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Safran Aircraft Engines SAS
Safran Ceramics SA
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Publication of EP3298244A1 publication Critical patent/EP3298244A1/en
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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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the invention relates to a turbine ring assembly for a turbomachine, which assembly comprises a plurality of ring sectors in one piece of ceramic matrix composite material and a ring support structure.
  • the field of application of the invention is in particular that of gas turbine aero engines.
  • the invention is however applicable to other turbomachines, for example industrial turbines.
  • Ceramic matrix composite materials are known for their good mechanical properties which make them suitable for constituting structural elements, and for their ability to retain these properties at high temperatures.
  • CMCs for various hot parts of such engines has already been considered, especially since CMCs have a lower density than that of refractory metals traditionally used.
  • the production of turbine ring sectors in a single piece in CMC is described in particular in the document US 2012/0027572 .
  • the ring sectors comprise an annular base, the internal face of which defines the internal face of the turbine ring and an external face from which extend two parts forming legs. the ends of which are engaged in housings of a metal ring support structure.
  • CMC ring sectors significantly reduces the ventilation required to cool the turbine ring.
  • the seal between the gas flow stream on the inner side of the ring sectors and the outer side of the ring sectors remains a problem. Indeed, in order to ensure a good seal, it is necessary to be able to ensure good contact between the tabs of the CMC ring sectors and the metal flanges of the ring support structure.
  • the differential expansions between the metal of the ring support structure and the CMC of the ring sectors complicates the maintenance of the seal between these elements.
  • the flanges of the ring support structure may no longer be in contact with the legs of the sectors or, at the on the contrary, exert too much stress on the legs of the sectors, which can damage them.
  • maintaining the ring sectors on the ring support structure requires the use of a U-section clamp, which complicates the assembly of the sectors and increases the cost of the assembly.
  • the invention aims to avoid such drawbacks and provides for this purpose a turbine ring assembly comprising a plurality of ring sectors forming a ring and a ring support structure comprising two annular flanges, each ring sector having a first annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which radially extend two legs, the legs of each ring sector being held between the two flanges annulars of the ring support structure, the two annular flanges of the ring support structure exerting a stress on the tabs of the ring sectors, one of the flanges of the ring support structure being elastically deformable in the axial direction of the ring, characterized in that each ring sector is made of ceramic matrix composite material and in that the turbine ring assembly further comprises a plurality of pins engaged in at least one at least one annular flanges of the ring support structure and the tabs of the ring sectors facing said at least one annular flange and in that the elastically
  • the presence of the pins makes it possible to maintain the ring sectors in the radial and circumferential positions on the ring support structure. Indeed, the pins being engaged both in at least one annular flange of the ring support structure and in the tabs of the ring sectors facing the flange in question, it is possible to prevent any sliding or displacement. possible ring sectors in the circumferential and radial directions of the ring relative to the ring support structure, even in the event of contact between the top of a rotating vane and one or more sectors of ring.
  • the contact between the flanges of the ring support structure and the tabs of the ring sectors can be maintained independently of temperature variations.
  • the ring sectors can be mounted between the flanges with a “cold” prestress, so that the contact between the ring sectors and the flanges is ensured whatever the temperature conditions.
  • the flexibility of at least one of the flanges of the ring support structure allows by its deformation to accommodate the differential thermal expansions between the ring sectors and the flanges so as to avoid exerting too great a stress on the ring sectors.
  • At least one of the annular flanges of the ring support structure has a lip on its face facing the legs of the ring sectors.
  • the presence of a lip on a flange makes it possible to facilitate the definition of the contact portion between the flange of the ring support structure and the tabs of the ring sectors facing the latter.
  • the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that facing the legs of the sectors of ring.
  • the presence of the hooks makes it possible to facilitate the separation of the elastically deformable flange for the insertion of the tabs of the ring sectors between the flanges without having to slide the tabs by force between the flanges.
  • locking pins enables the ring sectors to be held in radial and circumferential positions on the ring support structure. Indeed, the pins being engaged both in at least one annular flange of the ring support structure and in the tabs of the ring sectors facing the flange in question, it is possible to prevent any sliding or displacement. possible ring sectors in the circumferential and radial directions of the ring relative to the ring support structure, even in the event of contact between the top of a rotating vane and one or more sectors of ring.
  • At least one of the annular flanges of the ring support structure has a lip on its face facing the tabs of the sectors of the ring. ring.
  • the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that facing the legs. ring sectors, the traction in the axial direction of the ring exerted on said elastically deformable flange being produced by a tool engaged in one or more hooks.
  • the figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 of ceramic matrix composite (CMC) material and a ring support metal structure 3.
  • the turbine ring 1 surrounds a set of rotating blades 5.
  • the turbine ring 1 is formed from a plurality of ring sectors 10, the figure 1 being a radial sectional view along a plane passing between two sectors of contiguous rings.
  • the arrow D A indicates the axial direction with respect to the turbine ring 1 while the arrow D R indicates the radial direction with respect to the turbine ring 1.
  • Each ring sector 10 has a section substantially in the shape of an inverted ⁇ with an annular base 12 whose internal face coated with a layer 13 of abradable material and / or with a thermal barrier defines the gas flow stream. in the turbine.
  • Upstream and downstream tabs 14, 16 extend from the outer face of the annular base 12 in the radial direction D R.
  • upstream and downstream are used here with reference to the direction of flow of the gas flow in the turbine (arrow F).
  • the ring support structure 3 which is integral with a turbine housing 30 comprises an annular upstream radial flange 32 comprising a lip 34 on its face facing the upstream tabs 14 of the ring sectors 10, the lip 34 resting on the outer face 14a of the upstream tabs 14.
  • the ring support structure comprises a radial flange annular downstream 36 comprising a lip 38 on its face facing the downstream lugs 16 of the ring sectors 10, the lip 38 both resting on the outer face 16a of the downstream lugs 16.
  • the tabs 14 and 16 of each ring sector 10 are pre-stressed between the annular flanges 32 and 54 so that the flanges exert, at least at "cold", that is, that is to say at an ambient temperature of about 20 ° C., but also at all the operating temperatures of the turbine, a stress on the tabs 14 and 16 and therefore a clamping of the sectors by the flanges.
  • This stress is maintained at all the temperatures to which the ring assembly may be subjected during operation of the turbine and is controlled, that is to say without over-stressing the ring sectors, thanks to the presence of 'at least one elastically deformable flange as explained above.
  • the ring sectors 10 are also held by locking pins. More precisely and as illustrated on the figure 1 , pins 40 are engaged both in the annular upstream radial flange 32 of the ring support structure 3 and in the upstream tabs 14 of the ring sectors 10. For this purpose, the pins 40 each pass through an orifice respectively 33 formed in the annular upstream radial flange 32 and an orifice 15 formed in each upstream lug 14, the orifices 33 and 15 being aligned during the mounting of the ring sectors 10 on the ring support structure 3. Likewise, pins 41 are engaged both in the annular downstream radial flange 36 of the ring support structure 3 and in the downstream tabs 16 of the ring sectors 10.
  • the pins 41 each respectively pass through an orifice 37 provided in the annular downstream radial flange 36 and an orifice 17 formed in each downstream lug 16, the orifices 37 and 17 being aligned during the mounting of the ring sectors 10 on the ring support structure 3.
  • the presence of the pins makes it possible to maintain the radial and circular positions nferential of the ring sectors on the ring support structure.
  • the pins being engaged both in at least one annular flange of the ring support structure and in the legs of the ring sectors facing the flange concerned, it is possible to prevent any sliding or possible displacement of the ring sectors in the circumferential and radial directions of the ring with respect to the ring support structure, and this even in the event of contact between the top of a rotating vane and one or more ring sectors.
  • inter-sector sealing is ensured by sealing tongues housed in grooves facing each other in the opposite edges of two neighboring ring sectors.
  • a tongue 22a extends almost the entire length of the annular base 12 in the middle part thereof.
  • Another tongue 22b extends along the tab 14 and over a portion of the annular base 12.
  • Another tab 22c extends along the tab 16. At one end, the tab 22c abuts the tab. 22a and on the tongue 22b.
  • the tongues 22a, 22b, 22c are for example metallic and are mounted with cold play in their housings in order to ensure the sealing function at the temperatures encountered in service.
  • ventilation openings 32a formed in the flange 32 make it possible to bring cooling air to the outer side of the turbine ring 10.
  • Each ring sector 10 described above is made of a ceramic matrix composite material (CMC) by forming a fiber preform having a shape close to that of the ring sector and densifying the ring sector with a ceramic matrix. .
  • CMC ceramic matrix composite material
  • Ceramic fiber threads for example SiC fiber threads such as those sold by the Japanese company Nippon Carbon under the name “Nicalon”, or carbon fiber threads.
  • the fiber preform is advantageously produced by three-dimensional weaving, or multi-layer weaving with provision of unbinding zones making it possible to separate the parts of the preforms corresponding to the tabs 14 and 16 of the sectors 10.
  • the weaving can be of the interlock type, as illustrated.
  • Other three-dimensional or multi-layer weaves can be used, for example multi-plain or multi-satin weaves.
  • the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification being able to be carried out in particular by chemical gas infiltration (CVI) or an MI ( “Melt Infiltrated”, liquid silicon introduced into the fiber preform by capillary action, the preform being previously consolidated by a CVI phase) which are well known per se.
  • CVI chemical gas infiltration
  • MI “Melt Infiltrated”
  • the ring support structure 3 is for its part made of a metallic material such as inconel, the C263 superalloy or Waspaloy®.
  • the distance E between the annular upstream radial flange 32 and the annular downstream radial flange 36 at "rest", that is to say when no ring sector is fitted between the flanges, is less than the distance D present between the external faces 14a and 16a of upstream and downstream legs 14 and 16 of the ring sectors.
  • the distance E is measured between the lips 34 and 38 present respectively at the end of the annular flanges 32 and 36.
  • the distance is measured between the internal faces of the flanges which will be in contact with the external surface of the tabs of the ring sectors.
  • the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction D A of the ring.
  • the annular downstream radial flange 36 which is elastically deformable.
  • the annular downstream radial flange 36 of the ring support structure 3 has a reduced thickness compared to the annular upstream radial flange 32, which gives it a certain elasticity.
  • the annular downstream radial flange 36 is pulled in the direction D A as shown in the figures 3 and 4 in order to increase the spacing between the flanges 32 and 36 and allow the insertion of the tabs 14 and 16 between the flanges 32 and 36 without risk of damage.
  • the latter comprises a plurality of hooks 39 distributed over its face 36a, which face is opposite to the face 36b of the flange 36 opposite the downstream tabs 16 of the ring sectors 10 ( figure 4 ).
  • the traction in the axial direction D A of the ring exerted on the elastically deformable flange 36 is here carried out by means of a tool 50 comprising at least an arm 51, the end of which comprises a hook 510 which is engaged in a hook 39 present on the outer face 36a of the flange 36.
  • the number of hooks 39 distributed over the face 36a of the flange 36 is defined as a function of the number of traction points that one wishes to have on the flange 36. This number depends mainly on the elastic nature of the flange. Other shapes and arrangements of means making it possible to exert traction in the axial direction D A on one of the flanges of the ring support structure can of course be envisaged within the framework of the present invention.
  • each tab 14 or 16 of the ring sector may include one or more orifices for the passage of a locking pin .
  • the shape and orientation of the hooks may vary.
  • the figure 5 shows an annular downstream radial flange 136 comprising a plurality of hooks 139 which open in the circumferential direction of the flange and into which a tab 151 of a traction tool is inserted.
  • the figure 6 shows an annular downstream radial flange 236 comprising a plurality of hooks 239 which open in the radial direction and towards the bottom of the flange and into which a tab 251 of a traction tool is inserted.

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

Description

Arrière-plan de l'inventionBackground of the invention

L'invention concerne un ensemble d'anneau de turbine pour une turbomachine, lequel ensemble comprend une pluralité de secteurs d'anneau en une seule pièce en matériau composite à matrice céramique et une structure de support d'anneau.The invention relates to a turbine ring assembly for a turbomachine, which assembly comprises a plurality of ring sectors in one piece of ceramic matrix composite material and a ring support structure.

Le domaine d'application de l'invention est notamment celui des moteurs aéronautiques à turbine à gaz. L'invention est toutefois applicable à d'autres turbomachines, par exemple des turbines industrielles.The field of application of the invention is in particular that of gas turbine aero engines. The invention is however applicable to other turbomachines, for example industrial turbines.

Les matériaux composites à matrice céramique, ou CMC, sont connus pour leurs bonnes propriétés mécaniques qui les rendent aptes à constituer des éléments de structure, et pour leur capacité à conserver ces propriétés à des températures élevées.Ceramic matrix composite materials, or CMCs, are known for their good mechanical properties which make them suitable for constituting structural elements, and for their ability to retain these properties at high temperatures.

Dans des moteurs aéronautiques à turbine à gaz, l'amélioration du rendement et la réduction des émissions polluantes conduisent à rechercher un fonctionnement à des températures toujours plus élevées. Dans le cas d'ensembles d'anneau de turbine entièrement métalliques, il est nécessaire de refroidir tous les éléments de l'ensemble et en particulier l'anneau de turbine qui est soumis à des flux hautes températures. Ce refroidissement a un impact significatif sur la performance du moteur puisque le flux de refroidissement utilisé est prélevé sur le flux principal du moteur. En outre, l'utilisation de métal pour l'anneau de turbine limite les possibilités d'augmenter la température au niveau de la turbine, ce qui permettrait pourtant d'améliorer les performances des moteurs aéronautiques.In gas turbine aero engines, improving efficiency and reducing polluting emissions lead to seeking operation at ever higher temperatures. In the case of entirely metal turbine ring assemblies, it is necessary to cool all the elements of the assembly and in particular the turbine ring which is subjected to high temperature flows. This cooling has a significant impact on the performance of the engine since the cooling flow used is taken from the main flow of the engine. In addition, the use of metal for the turbine ring limits the possibilities of increasing the temperature at the level of the turbine, which would nevertheless make it possible to improve the performance of aero engines.

L'utilisation de CMC pour différentes parties chaudes de tels moteurs a déjà été envisagée, d'autant que les CMC ont une masse volumique inférieure à celle de métaux réfractaires traditionnellement utilisés.The use of CMCs for various hot parts of such engines has already been considered, especially since CMCs have a lower density than that of refractory metals traditionally used.

Ainsi, la réalisation de secteurs d'anneau de turbine en une seule pièce en CMC est notamment décrite dans le document US 2012/0027572 . Les secteurs d'anneau comportent une base annulaire dont la face interne définit la face interne de l'anneau de turbine et une face externe à partir de laquelle s'étendent deux parties formant pattes dont les extrémités sont engagées dans des logements d'une structure métallique de support d'anneau.Thus, the production of turbine ring sectors in a single piece in CMC is described in particular in the document US 2012/0027572 . The ring sectors comprise an annular base, the internal face of which defines the internal face of the turbine ring and an external face from which extend two parts forming legs. the ends of which are engaged in housings of a metal ring support structure.

L'utilisation de secteurs d'anneau en CMC permet de réduire significativement la ventilation nécessaire au refroidissement de l'anneau de turbine. Toutefois, l'étanchéité entre la veine d'écoulement gazeux du côté intérieur des secteurs d'anneau et le côté extérieur des secteurs d'anneau demeure un problème. En effet, afin d'assurer une bonne étanchéité, il faut pouvoir assurer un bon contact entre les pattes des secteurs d'anneau en CMC et les brides métalliques de la structure de support d'anneau. Or, les dilatations différentielles entre le métal de la structure de support d'anneau et le CMC des secteurs d'anneau complique le maintien de l'étanchéité entre ces éléments. Ainsi, lors de dilatations différentielles et suivant la géométrie de montage des secteurs d'anneau sur la structure de support d'anneau, les brides de la structure de support d'anneau peuvent ne plus être en contact avec les pattes des secteurs ou, au contraire, exercer une contrainte trop forte sur les pattes des secteurs, ce qui peut les endommager. En outre, comme décrit dans le document US 2012/0027572 , le maintien des secteurs d'anneau sur la structure de support d'anneau nécessite l'utilisation d'une pince à section en U, ce qui complexifie le montage des secteurs et augmente le coût de l'ensemble.The use of CMC ring sectors significantly reduces the ventilation required to cool the turbine ring. However, the seal between the gas flow stream on the inner side of the ring sectors and the outer side of the ring sectors remains a problem. Indeed, in order to ensure a good seal, it is necessary to be able to ensure good contact between the tabs of the CMC ring sectors and the metal flanges of the ring support structure. However, the differential expansions between the metal of the ring support structure and the CMC of the ring sectors complicates the maintenance of the seal between these elements. Thus, during differential expansions and depending on the mounting geometry of the ring sectors on the ring support structure, the flanges of the ring support structure may no longer be in contact with the legs of the sectors or, at the on the contrary, exert too much stress on the legs of the sectors, which can damage them. In addition, as described in the document US 2012/0027572 , maintaining the ring sectors on the ring support structure requires the use of a U-section clamp, which complicates the assembly of the sectors and increases the cost of the assembly.

Les documents US 4 596 116 et US 4 087 199 divulguent un ensemble d'anneau de turbine dans lequel des secteurs d'anneau sont maintenus axialement entre des pattes d'une structure de support d'anneau. Toutefois, les solutions d'accrochage des secteurs d'anneaux divulguées dans ces documents ne permettent pas d'empêcher un déplacement ou glissement des secteurs d'anneau dans les directions radiale et circonférentielle de l'anneau, ce qui peut être problématique, en particulier en cas de contact entre le sommet d'une aube en rotation et la surface interne d'un ou plusieurs secteurs d'anneau.The documents US 4,596,116 and US 4,087,199 disclose a turbine ring assembly in which ring sectors are held axially between legs of a ring support structure. However, the solutions for attaching the ring sectors disclosed in these documents do not make it possible to prevent displacement or sliding of the ring sectors in the radial and circumferential directions of the ring, which can be problematic, in particular. in the event of contact between the top of a rotating vane and the internal surface of one or more ring sectors.

Objet et résumé de l'inventionPurpose and summary of the invention

L'invention vise à éviter de tels inconvénients et propose à cet effet un ensemble d'anneau de turbine comprenant une pluralité de secteurs d'anneau formant un anneau et une structure de support d'anneau comportant deux brides annulaires, chaque secteur d'anneau ayant une première partie formant base annulaire avec une face interne définissant la face interne de l'anneau de turbine et une face externe à partir de laquelle s'étendent radialement deux pattes, les pattes de chaque secteur d'anneau étant maintenues entre les deux brides annulaires de la structure de support d'anneau, les deux brides annulaires de la structure de support d'anneau exerçant une contrainte sur les pattes des secteurs d'anneau, une des brides de la structure de support d'anneau étant élastiquement déformable dans la direction axiale de l'anneau, caractérisé en ce que chaque secteur d'anneau est en matériau composite à matrice céramique et en ce que l'ensemble d'anneau de turbine comprend en outre une pluralité de pions engagés à la fois dans au moins une des brides annulaires de la structure de support d'anneau et les pattes des secteurs d'anneau en regard de ladite au moins une bride annulaire et en ce que la bride élastiquement déformable de la structure de support d'anneau présente une épaisseur inférieure à celle de l'autre bride de ladite structure de support d'anneau.The invention aims to avoid such drawbacks and provides for this purpose a turbine ring assembly comprising a plurality of ring sectors forming a ring and a ring support structure comprising two annular flanges, each ring sector having a first annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which radially extend two legs, the legs of each ring sector being held between the two flanges annulars of the ring support structure, the two annular flanges of the ring support structure exerting a stress on the tabs of the ring sectors, one of the flanges of the ring support structure being elastically deformable in the axial direction of the ring, characterized in that each ring sector is made of ceramic matrix composite material and in that the turbine ring assembly further comprises a plurality of pins engaged in at least one at least one annular flanges of the ring support structure and the tabs of the ring sectors facing said at least one annular flange and in that the elastically deformable flange of the support structure d 'ring has a thickness less than that of the other flange of said ring support structure.

La présence des pions permet d'assurer le maintien en positions radiale et circonférentielle des secteurs d'anneau sur la structure de support d'anneau. En effet, les pions étant engagés à la fois dans au moins une bride annulaire de la structure de support d'anneau et dans les pattes des secteurs d'anneau en regard de la bride concernée, il est possible d'empêcher tout glissement ou déplacement éventuel des secteurs d'anneau dans les directions circonférentielle et radiale de l'anneau par rapport dans la structure de support d'anneau, et ce même en cas de contact entre le sommet d'une aube en rotation et un ou plusieurs secteurs d'anneau.The presence of the pins makes it possible to maintain the ring sectors in the radial and circumferential positions on the ring support structure. Indeed, the pins being engaged both in at least one annular flange of the ring support structure and in the tabs of the ring sectors facing the flange in question, it is possible to prevent any sliding or displacement. possible ring sectors in the circumferential and radial directions of the ring relative to the ring support structure, even in the event of contact between the top of a rotating vane and one or more sectors of ring.

En outre, grâce à la présence d'au moins une bride élastiquement déformable, le contact entre les brides de la structure de support d'anneau et les pattes des secteurs d'anneau peut être maintenu indépendamment des variations de température. En effet, les secteurs d'anneau peuvent être montés entre les brides avec une précontrainte « à froid », de sorte que le contact entre les secteurs d'anneau et les brides soit assuré quelles que soient les conditions de température. La souplesse d'au moins une des brides de la structure de support d'anneau permet par sa déformation d'accommoder les dilatations thermiques différentielles entre les secteurs d'anneau et les brides de manière à éviter d'exercer une contrainte trop importante sur les secteurs d'anneau.Furthermore, thanks to the presence of at least one elastically deformable flange, the contact between the flanges of the ring support structure and the tabs of the ring sectors can be maintained independently of temperature variations. Indeed, the ring sectors can be mounted between the flanges with a “cold” prestress, so that the contact between the ring sectors and the flanges is ensured whatever the temperature conditions. The flexibility of at least one of the flanges of the ring support structure allows by its deformation to accommodate the differential thermal expansions between the ring sectors and the flanges so as to avoid exerting too great a stress on the ring sectors.

Selon un premier aspect de l'ensemble d'anneau de turbine selon l'invention, au moins une des brides annulaires de la structure de support d'anneau comporte une lèvre sur sa face en regard des pattes des secteurs d'anneau. La présence d'une lèvre sur une bride permet de faciliter la définition de la portion de contact entre la bride de la structure de support d'anneau et les pattes des secteurs d'anneau en regard de celle-ci.According to a first aspect of the turbine ring assembly according to the invention, at least one of the annular flanges of the ring support structure has a lip on its face facing the legs of the ring sectors. The presence of a lip on a flange makes it possible to facilitate the definition of the contact portion between the flange of the ring support structure and the tabs of the ring sectors facing the latter.

Selon un deuxième aspect de l'ensemble d'anneau de turbine selon l'invention, la bride élastiquement déformable de la structure de support d'anneau comporte une pluralité de crochets répartis sur sa face opposée à celle en regard des pattes des secteurs d'anneau. La présence des crochets permet de faciliter l'écartement de la bride élastiquement déformable pour l'insertion des pattes des secteurs d'anneau entre les brides sans avoir à glisser en force les pattes entre les brides.According to a second aspect of the turbine ring assembly according to the invention, the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that facing the legs of the sectors of ring. The presence of the hooks makes it possible to facilitate the separation of the elastically deformable flange for the insertion of the tabs of the ring sectors between the flanges without having to slide the tabs by force between the flanges.

La présente invention a également pour objet un procédé de réalisation d'un ensemble d'anneau de turbine comprenant

  • la fabrication d'une pluralité de secteurs d'anneau, chaque secteur d'anneau ayant une première partie formant base annulaire avec une face interne définissant la face interne de l'anneau de turbine et une face externe à partir de laquelle s'étendent radialement deux pattes,
  • la fabrication d'une structure de support d'anneau comportant deux brides annulaires,
  • le montage de chaque secteur d'anneau entre les deux brides annulaires de la structure de support d'anneau,
l'écartement entre les deux brides de la structure d'anneau étant inférieur à la distance entre les faces externes des pattes de chaque secteur d'anneau, une des brides de la structure de support d'anneau étant élastiquement déformable dans la direction axiale de l'anneau,
caractérisé en ce que, lors du montage de chaque secteur d'anneau, une traction dans la direction axiale de l'anneau est exercée sur ladite bride élastiquement déformable de manière à augmenter l'écartement entre les deux brides et engager les pattes du secteur d'anneau entre les deux brides de la structure de support d'anneau, en ce que chaque secteur d'anneau est réalisé en matériau composite à matrice céramique, et en ce que le procédé comprend en outre l'engagement d'une pluralité de pions à la fois dans au moins une des brides annulaires de la structure de support d'anneau et les pattes des secteurs d'anneau en regard de ladite au moins une bride annulaire et en ce que la bride élastiquement déformable de la structure de support d'anneau présente une épaisseur inférieure à celle de l'autre bride de ladite structure de support d'anneau.The present invention also relates to a method of producing a turbine ring assembly comprising
  • fabricating a plurality of ring sectors, each ring sector having a first annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which extend radially two legs,
  • the manufacture of a ring support structure comprising two annular flanges,
  • the mounting of each ring sector between the two annular flanges of the ring support structure,
the spacing between the two flanges of the ring structure being less than the distance between the outer faces of the legs of each ring sector, one of the flanges of the ring support structure being elastically deformable in the axial direction of the ring,
characterized in that, during the assembly of each ring sector, a traction in the axial direction of the ring is exerted on said elastically deformable flange so as to increase the distance between the two flanges and engage the tabs of the sector d 'ring between the two flanges of the ring support structure, in that each ring sector is made of matrix composite material ceramic, and in that the method further comprises engaging a plurality of pins both in at least one of the annular flanges of the ring support structure and the tabs of the ring sectors facing said at least one annular flange and in that the elastically deformable flange of the ring support structure has a thickness less than that of the other flange of said ring support structure.

L'utilisation de pions de blocage permet d'assurer le maintien en positions radiale et circonférentielle des secteurs d'anneau sur la structure de support d'anneau. En effet, les pions étant engagés à la fois dans au moins une bride annulaire de la structure de support d'anneau et dans les pattes des secteurs d'anneau en regard de la bride concernée, il est possible d'empêcher tout glissement ou déplacement éventuel des secteurs d'anneau dans les directions circonférentielle et radiale de l'anneau par rapport dans la structure de support d'anneau, et ce même en cas de contact entre le sommet d'une aube en rotation et un ou plusieurs secteurs d'anneau.The use of locking pins enables the ring sectors to be held in radial and circumferential positions on the ring support structure. Indeed, the pins being engaged both in at least one annular flange of the ring support structure and in the tabs of the ring sectors facing the flange in question, it is possible to prevent any sliding or displacement. possible ring sectors in the circumferential and radial directions of the ring relative to the ring support structure, even in the event of contact between the top of a rotating vane and one or more sectors of ring.

En outre grâce à la traction exercée sur la patte élastiquement déformable, il est possible d'insérer les pattes des secteurs d'anneau entre les brides de la structure de support d'anneau sans avoir à forcer sur lesdites pattes qui sont ensuite maintenues axialement avec une contrainte entre les brides après relâchement de la traction exercée sur la bride élastiquement déformable.In addition, thanks to the traction exerted on the elastically deformable tab, it is possible to insert the tabs of the ring sectors between the flanges of the ring support structure without having to force said tabs which are then held axially with a stress between the flanges after releasing the traction exerted on the elastically deformable flange.

Selon un premier aspect du procédé de réalisation d'un ensemble d'anneau de turbine selon l'invention, au moins une des brides annulaires de la structure de support d'anneau comporte une lèvre sur sa face en regard des pattes des secteurs d'anneau.According to a first aspect of the method for producing a turbine ring assembly according to the invention, at least one of the annular flanges of the ring support structure has a lip on its face facing the tabs of the sectors of the ring. ring.

Selon un deuxième aspect du procédé de réalisation d'un ensemble d'anneau de turbine selon l'invention, la bride élastiquement déformable de la structure de support d'anneau comporte une pluralité de crochets répartis sur sa face opposée à celle en regard des pattes des secteurs d'anneau, la traction dans la direction axiale de l'anneau exercée sur ladite bride élastiquement déformable étant réalisée par un outil engagé dans un ou plusieurs crochets.According to a second aspect of the method for producing a turbine ring assembly according to the invention, the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that facing the legs. ring sectors, the traction in the axial direction of the ring exerted on said elastically deformable flange being produced by a tool engaged in one or more hooks.

Brève description des dessins.Brief description of the drawings.

L'invention sera mieux comprise à la lecture faite ci-après, à titre indicatif mais non limitatif, en référence aux dessins annexés sur lesquels :

  • la figure 1 est une vue en demi-coupe radiale montrant un mode de réalisation d'un ensemble d'anneau de turbine selon l'invention ;
  • les figures 2 à 4 montrent schématiquement le montage d'un secteur d'anneau dans la structure de support d'anneau de l'ensemble d'anneau de la figure 1 ;
  • la figure 5 est une vue schématique en perspective montrant une variante de réalisation des crochets présents sur une bride de structure de support d'anneau élastiquement déformable ;
  • la figure 6 est une vue schématique en perspective montrant une autre variante de réalisation des crochets présents sur une bride de structure de support d'anneau élastiquement déformable.
The invention will be better understood on reading below, by way of indication but not by way of limitation, with reference to the appended drawings in which:
  • the figure 1 is a radial half-sectional view showing one embodiment of a turbine ring assembly according to the invention;
  • the figures 2 to 4 schematically show the mounting of a ring sector in the ring support structure of the ring assembly of the figure 1 ;
  • the figure 5 is a schematic perspective view showing an alternative embodiment of the hooks present on an elastically deformable ring support structure flange;
  • the figure 6 is a schematic perspective view showing another variant embodiment of the hooks present on an elastically deformable ring support structure flange.

Description détaillée de modes de réalisationDetailed description of embodiments

La figure 1 montre un ensemble d'anneau de turbine haute pression comprenant un anneau de turbine 1 en matériau composite à matrice céramique (CMC) et une structure métallique de support d'anneau 3. L'anneau de turbine 1 entoure un ensemble de pales rotatives 5. L'anneau de turbine 1 est formé d'une pluralité de secteurs d'anneau 10, la figure 1 étant une vue en coupe radiale selon un plan passant entre deux secteurs d'anneaux contigus. La flèche DA indique la direction axiale par rapport à l'anneau de turbine 1 tandis que la flèche DR indique la direction radiale par rapport à l'anneau de turbine 1.The figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 of ceramic matrix composite (CMC) material and a ring support metal structure 3. The turbine ring 1 surrounds a set of rotating blades 5. The turbine ring 1 is formed from a plurality of ring sectors 10, the figure 1 being a radial sectional view along a plane passing between two sectors of contiguous rings. The arrow D A indicates the axial direction with respect to the turbine ring 1 while the arrow D R indicates the radial direction with respect to the turbine ring 1.

Chaque secteur d'anneau 10 a une section sensiblement en forme de π inversé avec une base annulaire 12 dont la face interne revêtue d'une couche 13 de matériau abradable et/ou d'une barrière thermique définit la veine d'écoulement de flux gazeux dans la turbine. Des pattes amont et aval 14, 16 s'étendent à partir de la face externe de la base annulaire 12 dans la direction radiale DR. Les termes "amont" et "aval" sont utilisés ici en référence au sens d'écoulement du flux gazeux dans la turbine (flèche F).Each ring sector 10 has a section substantially in the shape of an inverted π with an annular base 12 whose internal face coated with a layer 13 of abradable material and / or with a thermal barrier defines the gas flow stream. in the turbine. Upstream and downstream tabs 14, 16 extend from the outer face of the annular base 12 in the radial direction D R. The terms “upstream” and “downstream” are used here with reference to the direction of flow of the gas flow in the turbine (arrow F).

La structure de support d'anneau 3 qui est solidaire d'un carter de turbine 30 comprend une bride radiale amont annulaire 32 comportant une lèvre 34 sur sa face en regard des pattes amont 14 des secteurs d'anneau 10, la lèvre 34 étant en appui sur la face externe 14a des pattes amont 14. Du côté aval, la structure de support d'anneau comprend une bride radiale aval annulaire 36 comportant une lèvre 38 sur sa face en regard des pattes aval 16 des secteurs d'anneau 10, la lèvre 38 tant en appui sur la face externe 16a des pattes aval 16.The ring support structure 3 which is integral with a turbine housing 30 comprises an annular upstream radial flange 32 comprising a lip 34 on its face facing the upstream tabs 14 of the ring sectors 10, the lip 34 resting on the outer face 14a of the upstream tabs 14. On the downstream side, the ring support structure comprises a radial flange annular downstream 36 comprising a lip 38 on its face facing the downstream lugs 16 of the ring sectors 10, the lip 38 both resting on the outer face 16a of the downstream lugs 16.

Comme expliqué ci-après en détails, les pattes 14 et 16 de chaque secteur d'anneau 10 sont montées en précontrainte entre les brides annulaires 32 et 54 de manière à ce que les brides exercent, au moins à « froid », c'est-à-dire à une température ambiante d'environ 20°C, mais également à toutes les températures de fonctionnement de la turbine, une contrainte sur les pattes 14 et 16 et donc un serrage des secteurs par les brides. Cette contrainte est maintenue à toutes les températures auxquelles l'ensemble d'anneau peut être soumis lors du fonctionnement de la turbine et est maîtrisée, c'est-à-dire sans sur-contraindre les secteurs d'anneau, grâce à la présence d'au moins une bride élastiquement déformable comme expliqué ci-avant.As explained in detail below, the tabs 14 and 16 of each ring sector 10 are pre-stressed between the annular flanges 32 and 54 so that the flanges exert, at least at "cold", that is, that is to say at an ambient temperature of about 20 ° C., but also at all the operating temperatures of the turbine, a stress on the tabs 14 and 16 and therefore a clamping of the sectors by the flanges. This stress is maintained at all the temperatures to which the ring assembly may be subjected during operation of the turbine and is controlled, that is to say without over-stressing the ring sectors, thanks to the presence of 'at least one elastically deformable flange as explained above.

Par ailleurs, dans l'exemple décrit ici, les secteurs d'anneau 10 sont en outre maintenus par des pions de blocage. Plus précisément et comme illustré sur la figure 1, des pions 40 sont engagés à la fois dans la bride radiale amont annulaire 32 de la structure de support d'anneau 3 et dans les pattes amont 14 des secteurs d'anneau 10. A cet effet, les pions 40 traversent chacun respectivement un orifice 33 ménagé dans la bride radiale amont annulaire 32 et un orifice 15 ménagé dans chaque patte amont 14, les orifices 33 et 15 étant alignés lors du montage des secteurs d'anneau 10 sur la structure de support d'anneau 3. De même, des pions 41 sont engagés à la fois dans la bride radiale aval annulaire 36 de la structure de support d'anneau 3 et dans les pattes aval 16 des secteurs d'anneau 10. A cet effet, les pions 41 traversent chacun respectivement un orifice 37 ménagé dans la bride radiale aval annulaire 36 et un orifice 17 ménagé chaque patte aval 16, les orifices 37 et 17 étant alignés lors du montage des secteurs d'anneau 10 sur la structure de support d'anneau 3. La présence des pions permet d'assurer le maintien en positions radiale et circonférentielle des secteurs d'anneau sur la structure de support d'anneau. En effet, les pions étant engagés à la fois dans au moins une bride annulaire de la structure de support d'anneau et dans les pattes des secteurs d'anneau en regard de la bride concernée, il est possible d'empêcher tout glissement ou déplacement éventuel des secteurs d'anneau dans les directions circonférentielle et radiale de l'anneau par rapport dans la structure de support d'anneau, et ce même en cas de contact entre le sommet d'une aube en rotation et un ou plusieurs secteurs d'anneau.Furthermore, in the example described here, the ring sectors 10 are also held by locking pins. More precisely and as illustrated on the figure 1 , pins 40 are engaged both in the annular upstream radial flange 32 of the ring support structure 3 and in the upstream tabs 14 of the ring sectors 10. For this purpose, the pins 40 each pass through an orifice respectively 33 formed in the annular upstream radial flange 32 and an orifice 15 formed in each upstream lug 14, the orifices 33 and 15 being aligned during the mounting of the ring sectors 10 on the ring support structure 3. Likewise, pins 41 are engaged both in the annular downstream radial flange 36 of the ring support structure 3 and in the downstream tabs 16 of the ring sectors 10. For this purpose, the pins 41 each respectively pass through an orifice 37 provided in the annular downstream radial flange 36 and an orifice 17 formed in each downstream lug 16, the orifices 37 and 17 being aligned during the mounting of the ring sectors 10 on the ring support structure 3. The presence of the pins makes it possible to maintain the radial and circular positions nferential of the ring sectors on the ring support structure. Indeed, the pins being engaged both in at least one annular flange of the ring support structure and in the legs of the ring sectors facing the flange concerned, it is possible to prevent any sliding or possible displacement of the ring sectors in the circumferential and radial directions of the ring with respect to the ring support structure, and this even in the event of contact between the top of a rotating vane and one or more ring sectors.

En outre, l'étanchéité inter-secteurs est assurée par des languettes d'étanchéité logées dans des rainures se faisant face dans les bords en regard de deux secteurs d'anneau voisin. Une languette 22a s'étend sur presque toute la longueur de la base annulaire 12 dans la partie médiane de celle-ci. Une autre languette 22b s'étend le long de la patte 14 et sur une partie de la base annulaire 12. Une autre languette 22c s'étend le long de la patte 16. A une extrémité, la languette 22c vient en butée sur la languette 22a et sur la languette 22b. Les languettes 22a, 22b, 22c sont par exemple métalliques et sont montées avec jeu à froid dans leurs logements afin d'assurer la fonction d'étanchéité aux températures rencontrées en service.In addition, the inter-sector sealing is ensured by sealing tongues housed in grooves facing each other in the opposite edges of two neighboring ring sectors. A tongue 22a extends almost the entire length of the annular base 12 in the middle part thereof. Another tongue 22b extends along the tab 14 and over a portion of the annular base 12. Another tab 22c extends along the tab 16. At one end, the tab 22c abuts the tab. 22a and on the tongue 22b. The tongues 22a, 22b, 22c are for example metallic and are mounted with cold play in their housings in order to ensure the sealing function at the temperatures encountered in service.

L'assemblage sans jeu des pattes 14, 16 du secteur d'anneau en CMC avec des parties métalliques de la structure de support d'anneau est rendu possible en dépit de la différence de coefficient de dilatation thermique du fait que :

  • cet assemblage est réalisé à distance de la face chaude de la base annulaire 12 exposée au flux gazeux,
  • les pattes 14, 16 présentent avantageusement en section radiale une longueur relativement grande par rapport à leur épaisseur moyenne de sorte qu'un découplage thermique efficace est obtenu entre la base annulaire 12 et les extrémités des pattes 14, 16, et
  • une des brides de la structure d'anneau est élastiquement déformable, ce qui permet de compenser les dilatations différentielles entre les pattes des secteurs d'anneau en CMC et les brides de la structure de support d'anneau en métal sans augmenter significativement la contrainte exercée « à froid » par les brides sur les pattes des secteurs d'anneau.
The clearance-free assembly of the legs 14, 16 of the CMC ring sector with metal parts of the ring support structure is made possible despite the difference in coefficient of thermal expansion due to the fact that:
  • this assembly is carried out at a distance from the hot face of the annular base 12 exposed to the gas flow,
  • the legs 14, 16 advantageously have in radial section a relatively large length compared to their average thickness so that an effective thermal decoupling is obtained between the annular base 12 and the ends of the legs 14, 16, and
  • one of the flanges of the ring structure is elastically deformable, which makes it possible to compensate for the differential expansions between the tabs of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the stress exerted "Cold" by the flanges on the legs of the ring sectors.

En outre, de façon classique, des orifices de ventilation 32a formés dans la bride 32 permettent d'amener de l'air de refroidissement du côté extérieur de l'anneau de turbine 10.In addition, conventionally, ventilation openings 32a formed in the flange 32 make it possible to bring cooling air to the outer side of the turbine ring 10.

On décrit maintenant un procédé de réalisation d'un ensemble d'anneau de turbine correspondant à celui représenté sur la figure 1.We now describe a method of making a turbine ring assembly corresponding to that shown in Figure figure 1 .

Chaque secteur d'anneau 10 décrit ci-avant est réalisé en matériau composite à matrice céramique (CMC) par formation d'une préforme fibreuse ayant une forme voisine de celle du secteur d'anneau et densification du secteur d'anneau par une matrice céramique.Each ring sector 10 described above is made of a ceramic matrix composite material (CMC) by forming a fiber preform having a shape close to that of the ring sector and densifying the ring sector with a ceramic matrix. .

Pour la réalisation de la préforme fibreuse, on peut utiliser des fils en fibres céramiques, par exemple des fils en fibres SiC tels que ceux commercialisés par la société japonaise Nippon Carbon sous la dénomination "Nicalon", ou des fils en fibres de carbone.For producing the fiber preform, one can use ceramic fiber threads, for example SiC fiber threads such as those sold by the Japanese company Nippon Carbon under the name “Nicalon”, or carbon fiber threads.

La préforme fibreuse est avantageusement réalisée par tissage tridimensionnel, ou tissage multicouches avec aménagement de zones de déliaison permettant d'écarter les parties de préformes correspondant aux pattes 14 et 16 des secteurs 10.The fiber preform is advantageously produced by three-dimensional weaving, or multi-layer weaving with provision of unbinding zones making it possible to separate the parts of the preforms corresponding to the tabs 14 and 16 of the sectors 10.

Le tissage peut être de type interlock, comme illustré. D'autres armures de tissage tridimensionnel ou multicouches peuvent être utilisées comme par exemple des armures multi-toile ou multi-satin. On pourra se référer au document WO 2006/136755 .The weaving can be of the interlock type, as illustrated. Other three-dimensional or multi-layer weaves can be used, for example multi-plain or multi-satin weaves. We can refer to the document WO 2006/136755 .

Après tissage, l'ébauche peut être mise en forme pour obtenir une préforme de secteur d'anneau qui est consolidée et densifiée par une matrice céramique, la densification pouvant être réalisée notamment par infiltration chimique en phase gazeuse (CVI) ou un procédé MI (« Melt Infiltrated », silicium liquide introduit dans la préforme fibreuse par capillarité, la préforme étant préalablement consolidée par une phase CVI) qui sont bien connus en soi.After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification being able to be carried out in particular by chemical gas infiltration (CVI) or an MI ( “Melt Infiltrated”, liquid silicon introduced into the fiber preform by capillary action, the preform being previously consolidated by a CVI phase) which are well known per se.

Un exemple détaillé de fabrication de secteurs d'anneau en CMC est notamment décrit dans le document US 2012/0027572 .A detailed example of manufacturing ring sectors in CMC is described in particular in the document US 2012/0027572 .

La structure de support d'anneau 3 est quant à elle réalisée en un matériau métallique tel que de l'inconel, le superalliage C263 ou du Waspaloy®.The ring support structure 3 is for its part made of a metallic material such as inconel, the C263 superalloy or Waspaloy®.

La réalisation de l'ensemble d'anneau de turbine se poursuit par le montage des secteurs d'anneau 10 sur la structure de support d'anneau 3. Comme illustré sur la figure 2, l'écartement E entre la bride radiale amont annulaire 32 et la bride radiale aval annulaire 36 au « repos », c'est-à-dire lorsqu'aucun secteur d'anneau est monté entre les brides, est inférieur à la distance D présente entre les faces externes 14a et 16a des pattes amont et aval 14 et 16 des secteurs d'anneau. Dans l'exemple décrit ici, l'écartement E est mesuré entre les lèvres 34 et 38 présentes respectivement à l'extrémité des brides annulaires 32 et 36. Dans les modes de réalisation de l'ensemble d'anneau de turbine de l'invention dans lesquels les brides annulaires ne comportent pas de lèvres, l'écartement est mesuré entre les faces internes des brides qui seront en contact avec la surface externe des pattes des secteurs d'anneau.The production of the turbine ring assembly continues with the mounting of the ring sectors 10 on the ring support structure 3. As illustrated in figure 2 , the distance E between the annular upstream radial flange 32 and the annular downstream radial flange 36 at "rest", that is to say when no ring sector is fitted between the flanges, is less than the distance D present between the external faces 14a and 16a of upstream and downstream legs 14 and 16 of the ring sectors. In the example described here, the distance E is measured between the lips 34 and 38 present respectively at the end of the annular flanges 32 and 36. In the embodiments of the turbine ring assembly of the invention in which the annular flanges do not have lips, the distance is measured between the internal faces of the flanges which will be in contact with the external surface of the tabs of the ring sectors.

En définissant un écartement E entre les brides de la structure de support d'anneau inférieur à la distance D entre les faces externes des pattes de chaque secteur d'anneau, il est possible de monter les secteurs d'anneau en précontrainte entre les brides de la structure de support d'anneau. Toutefois, afin de ne pas endommager les pattes des secteurs d'anneau en CMC lors du montage et conformément à l'invention, la structure de support d'anneau comprend au moins une bride annulaire qui est élastiquement déformable dans la direction axiale DA de l'anneau. Dans l'exemple décrit ici, c'est la bride radiale aval annulaire 36 qui est élastiquement déformable. En effet, la bride radiale aval annulaire 36 de la structure de support d'anneau 3 présente une épaisseur réduite par rapport à la bride radiale amont annulaire 32, ce qui lui confère une certaine élasticité.By defining a distance E between the flanges of the ring support structure less than the distance D between the outer faces of the legs of each ring sector, it is possible to mount the ring sectors in prestressing between the flanges of the ring support structure. However, in order not to damage the tabs of the CMC ring sectors during assembly and in accordance with the invention, the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction D A of the ring. In the example described here, it is the annular downstream radial flange 36 which is elastically deformable. Indeed, the annular downstream radial flange 36 of the ring support structure 3 has a reduced thickness compared to the annular upstream radial flange 32, which gives it a certain elasticity.

Lors du montage d'un secteur d'anneau 10, la bride radiale aval annulaire 36 est tirée dans la direction DA comme montré sur les figures 3 et 4 afin d'augmenter l'écartement entre les brides 32 et 36 et permettre l'insertion des pattes 14 et 16 entre les brides 32 et 36 sans risque d'endommagement. Une fois les pattes 14 et 16 d'un secteur d'anneau 10 insérées entre les brides 14 et 16 et positionnées de manière à ligner les orifices 33 et 15, d'une part, et 17 et 37 d'autre part, la bride 36 est relâchée, les lèvres 34 et 38 respectivement des brides 32 et 36 exerçant alors une contrainte de maintien sur les pattes 14 et 16 du secteur d'anneau. Afin de faciliter l'écartement par traction de la bride radiale aval annulaire 36, celle-ci comporte une pluralité de crochets 39 répartis sur sa face 36a, face qui est opposée à la face 36b de la bride 36 en regard des pattes aval 16 des secteurs d'anneau 10 (figure 4). La traction dans la direction axiale DA de l'anneau exercée sur la bride 36 élastiquement déformable est ici réalisée au moyen d'un outil 50 comprenant au moins un bras 51 dont l'extrémité comporte un crochet 510 qui est engagé dans un crochet 39 présent sur la face externe 36a de la bride 36.When mounting a ring sector 10, the annular downstream radial flange 36 is pulled in the direction D A as shown in the figures 3 and 4 in order to increase the spacing between the flanges 32 and 36 and allow the insertion of the tabs 14 and 16 between the flanges 32 and 36 without risk of damage. Once the tabs 14 and 16 of a ring sector 10 have been inserted between the flanges 14 and 16 and positioned so as to line up the holes 33 and 15, on the one hand, and 17 and 37 on the other hand, the flange 36 is released, the lips 34 and 38 respectively of the flanges 32 and 36 then exerting a holding constraint on the tabs 14 and 16 of the ring sector. In order to facilitate the pulling apart of the annular downstream radial flange 36, the latter comprises a plurality of hooks 39 distributed over its face 36a, which face is opposite to the face 36b of the flange 36 opposite the downstream tabs 16 of the ring sectors 10 ( figure 4 ). The traction in the axial direction D A of the ring exerted on the elastically deformable flange 36 is here carried out by means of a tool 50 comprising at least an arm 51, the end of which comprises a hook 510 which is engaged in a hook 39 present on the outer face 36a of the flange 36.

Le nombre de crochets 39 répartis sur la face 36a de la bride 36 est défini en fonction du nombre de points de traction que l'on souhaite avoir sur la bride 36. Ce nombre dépend principalement du caractère élastique de la bride. D'autres formes et dispositions de moyens permettant d'exercer une traction dans la direction axiale DA sur une des brides de la structure de support d'anneau peuvent bien entendu être envisagées dans le cadre de la présente invention.The number of hooks 39 distributed over the face 36a of the flange 36 is defined as a function of the number of traction points that one wishes to have on the flange 36. This number depends mainly on the elastic nature of the flange. Other shapes and arrangements of means making it possible to exert traction in the axial direction D A on one of the flanges of the ring support structure can of course be envisaged within the framework of the present invention.

Une fois le secteur d'anneau 10 inséré et positionné entre les brides 32 et 36, des pions 40 sont engagés dans les orifices alignés 33 et 15 ménagés respectivement dans la bride radiale amont annulaire 32 et dans la patte amont 14, et des pions 41 sont engagés dans les orifices alignés 37 et 17 ménagés respectivement dans la bride radiale aval annulaire 36 et dans la patte aval 16. Chaque patte 14 ou 16 de secteur d'anneau peut comporter un ou plusieurs orifice pour le passage d'un pion de blocage.Once the ring sector 10 has been inserted and positioned between the flanges 32 and 36, pins 40 are engaged in the aligned orifices 33 and 15 formed respectively in the annular upstream radial flange 32 and in the upstream lug 14, and pins 41 are engaged in the aligned orifices 37 and 17 formed respectively in the annular downstream radial flange 36 and in the downstream tab 16. Each tab 14 or 16 of the ring sector may include one or more orifices for the passage of a locking pin .

La forme et l'orientation des crochets peuvent varier. La figure 5 montre une bride radiale aval annulaire 136 comportant une pluralité de crochets 139 qui s'ouvrent dans la direction circonférentielle de la bride et dans lesquels une patte 151 d'un outillage de traction est introduite. La figure 6 montre une bride radiale aval annulaire 236 comportant une pluralité de crochets 239 qui s'ouvrent dans la direction radiale et vers le bas de la bride et dans lesquels une patte 251 d'un outillage de traction est introduite.The shape and orientation of the hooks may vary. The figure 5 shows an annular downstream radial flange 136 comprising a plurality of hooks 139 which open in the circumferential direction of the flange and into which a tab 151 of a traction tool is inserted. The figure 6 shows an annular downstream radial flange 236 comprising a plurality of hooks 239 which open in the radial direction and towards the bottom of the flange and into which a tab 251 of a traction tool is inserted.

Claims (6)

  1. A turbine ring assembly comprising both a plurality of ring sectors (10) forming a turbine ring (1) and also a ring support structure (3) having two annular flanges (32, 36), each ring sector (10) having a first portion (12) forming an annular base with an inner face defining the inside face of the turbine ring (1) and an outer face from which two tabs (14, 16) extend radially, the tabs (14, 16) of each ring sector (10) being held between the two annular flanges (32, 36) of the ring support structure (3), the two annular flanges (32, 36) of the ring support structure (3) exerting stress on the tabs (14, 16) of the ring sectors (10), one of the flanges (36) of the ring support structure (3) being elastically deformable in the axial direction (DA) of the turbine ring (1), the turbine ring assembly being characterized in that each ring sector (10) is made of ceramic matrix composite material and in that it further comprises a plurality of pegs (40; 41) engaged both in at least one of the annular flanges (32; 36) of the ring support structure (3) and in the tabs (14; 16) of the ring sectors (10) facing said at least one annular flange (32; 36), and
    in that the elastically deformable flange (36) of the ring support structure (3) presents a thickness that is less than the thickness of the other flange (32) of said ring support structure (3).
  2. A turbine ring assembly according to claim 1, characterized in that at least one of the annular flanges (32; 36) of the ring support structure includes a lip (34; 38) on its face facing the tabs (14; 16) of the ring sectors (10).
  3. A turbine ring assembly according to claim 1 or claim 2, characterized in that the elastically deformable flange (36) of the ring support structure (3) has a plurality of hooks (39) distributed over its face (36a) opposite from its face (36b) facing the tabs (16) of the ring sectors (10).
  4. A method of making a turbine ring assembly, the method comprising:
    - fabricating a plurality of ring sectors (10), each ring sector (10) having a first portion (12) forming an annular base with an inner face defining the inside face of a turbine ring (1) and an outer face from which two tabs (14, 16) extend radially;
    - fabricating a ring support structure (3) having two annular flanges (32, 36); and
    - mounting each ring sector (10) between the two annular flanges (32, 36) of the ring support structure (3), the spacing (E) between the two flanges (32, 36) of the ring support structure (3) being smaller than the distance (D) between the outer faces (14a, 16a) of the tabs (14, 16) of each ring sector (10), one of the flanges (36) of the ring support structure (3) being elastically deformable in the axial direction (DA) of the turbine ring (1);
    the method being characterized in that each ring sector (10) is made of ceramic matrix composite material, in that during mounting of each ring sector (10), traction is exerted in the axial direction (DA) of the turbine ring (1) on said elastically deformable flange (36) so as to increase the spacing between the two flanges (32, 36) and engage the tabs (14, 16) of the ring sector between the two flanges of the ring support structure (3), and in that the method further comprises engaging a plurality of pegs (40; 41) both in at least one of the annular flanges (32; 36) of the ring support structure (3) and in the tabs (14; 16) of the ring sec tors (10) facing said at least one annular flange (32; 36), and in that the elastically deformable flange (36) of the ring support structure (3) presents thickness that is less than the thickness of the other flange (32) of said ring support structure (3).
  5. A method according to claim 4, characterized in that at least one of the annular flanges (32; 36) of the ring support structure (3) includes a lip (34; 38) on its face facing the tabs (14; 16) of the ring sectors (10).
  6. A method according to claim 4 or claim 5, characterized in that the elastically deformable flange (36) of the ring support structure (3) includes a plurality of hooks (39) distributed over its face (36a) opposite from its face (36b) facing the tabs (16) of the ring sectors (10), traction being exerted in the axial direction (DA) of the ring (1) on said elastically deformable flange by a tool (50) engaged in one or more hooks (39).
EP16726365.6A 2015-05-22 2016-05-12 Turbine ring assembly with axial retention Active EP3298244B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1554604A FR3036432B1 (en) 2015-05-22 2015-05-22 TURBINE RING ASSEMBLY WITH AXIAL RETENTION
PCT/FR2016/051123 WO2016189215A1 (en) 2015-05-22 2016-05-12 Turbine ring assembly with axial retention

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EP3298244A1 EP3298244A1 (en) 2018-03-28
EP3298244B1 true EP3298244B1 (en) 2020-11-11

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US (1) US10690007B2 (en)
EP (1) EP3298244B1 (en)
JP (1) JP6689290B2 (en)
CN (1) CN107709708B (en)
FR (1) FR3036432B1 (en)
WO (1) WO2016189215A1 (en)

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Publication number Publication date
JP2018519458A (en) 2018-07-19
CN107709708A (en) 2018-02-16
EP3298244A1 (en) 2018-03-28
US20180156069A1 (en) 2018-06-07
US10690007B2 (en) 2020-06-23
JP6689290B2 (en) 2020-04-28
CN107709708B (en) 2020-04-28
WO2016189215A1 (en) 2016-12-01
FR3036432A1 (en) 2016-11-25
FR3036432B1 (en) 2019-04-19

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