• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
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    • 专利摘要:
    A turbomachine turbine (1) comprising a casing (4) and a turbine distributor stage (2), the turbine distributor stage (2) (1) comprising an external metal ferrule (9) integral with the casing (4), an inner metal shell (5), and a plurality of ring-shaped ceramic matrix composite material ring sectors (20) extending between the outer metal shell (9) and the inner metal shell (5) and having a inner shell and an outer shell, each ring sector (20) having an inner platform (24) forming a portion of the inner shell, an outer platform (26) forming a portion of the outer shell, and at least one blade ( 28) extending between the outer platform (26) and the inner platform (24) and integral therewith. Each sector (20) is attached to the outer metal ferrule using at least one assembly comprising a screw and a nut, the screw passing through the outer platform (26) of the sector (20) and the outer metal ferrule.
    公开号:FR3080146A1
    申请号:FR1853345
    申请日:2018-04-17
    公开日:2019-10-18
    发明作者:Lucien Henri Jacques QUENNEHEN；Antoine Claude Michel Etienne Danis；Clement Jean Pierre DUFFAU；Clement Jarrossay；Nicolas Paul TABLEAU
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Invention background
    The invention relates to turbomachines, in particular aeronautical turboshaft engines or industrial turbines, and more particularly a turbine distributor stage made of composite material with ceramic matrix or matrix at least partially made of ceramic, hereinafter referred to as CMC material.
    The field of application of the invention is in particular that of aeronautical gas turbine engines. The invention is however applicable to other turbomachinery, for example industrial turbines.
    Improving the performance of turbomachinery and reducing their polluting emissions leads to consider increasingly higher operating temperatures.
    For elements of hot parts of turbomachinery, it has therefore been proposed to use composite materials with a ceramic matrix denoted CMC thereafter.
    CMC materials are typically formed from a fibrous reinforcement of refractory fibers, such as carbon or ceramic fibers, densified by a ceramic matrix or at least partially ceramic.
    These materials have remarkable thermo-structural properties, that is to say mechanical properties which make them capable of constituting structural elements and the ability to maintain these properties at high temperatures. In addition, CMC materials have a density much lower than that of metallic materials traditionally used for elements of hot parts of turbomachines.
    Thus, the documents WO 2010/061140, WO 2010/116066 and WO 2011/080443 describe the production of blades of movable wheels of turbomachines in CMC with integrated platform and heel. The use of CMC materials for turbine distributors has also been proposed, in particular in documents WO 2010/146288, FR 2 979 662 and EP 2 443 318.
    A traditional metal turbine distributor stage has a crown shape made up of several assembled sectors, each sector comprising an interior platform, an exterior platform and a plurality of blades extending between the interior and exterior platforms and integral with them. The juxtaposed interior platforms form an interior ferrule and the juxtaposed exterior platforms form an exterior ferrule. The interior and exterior ferrules delimit the gas flow stream in the distributor stage.
    Introducing a distributor stage, for example a high pressure distributor stage, in CMC makes it possible to increase the maximum tolerated temperature compared to a metallic distributor stage, and thus to decrease the amount of cooling air used. This thus makes it possible to increase the performance of the turbomachine.
    However, CMC, by its very different properties from metal, is more sensitive to certain mechanical stresses. In fact, the CMC has greater rigidity and lower expansion. It behaves better in compression, but its admissible tensile stresses are lower than those of metal.
    In addition, the integration in a metallic environment of a CMC part is delicate because of the differential thermal expansions between the CMC and the metal. This is all the more delicate in a turbomachine, and more particularly in a high-pressure part of the turbomachine, because the environment is very hot, which increases the differences in coefficients of thermal expansion between the materials, the aerodynamic forces undergone by a high pressure distributor stage being also very high in this turbine zone.
    CMC distributor stages are known, such as for example a turbine distributor stage comprising an external support ferrule secured to a casing, an internal support ferrule, and a plurality of CMC ring sectors forming a crown extending between the external support ring and the internal support ring. Each ring sector is supported on the internal and external support ferrules and comprises an interior platform, an exterior platform, and at least one blade extending between the exterior platform and the interior platform and integral with these.
    However, there is a need to improve the known solutions with regard to the deterministic connection of the ring sector in CMC with the internal ferrule, in particular in terms of at least axial maintenance of the ring sector and in terms of recovery of the aerodynamic forces.
    Furthermore, a large pressure differential is exerted on the casing under the distributor stage in the radial direction. This housing is used to create a seal between the rotor and the stator. This pressure difference is the source of a force which, if it were exerted on the CMC, would be too high taking into account the admissible materials.
    There is also known a distributor stage as described above and further comprising a reinforcing mast extending radially inside the blades between the two platforms.
    However, such a solution takes up both the efforts relating to the pressure differential under the distributor stage via the mast and the aerodynamic efforts on the crown in CMC. There is therefore a need to improve the deterministic maintenance of the CMC part of this solution.
    Subject and summary of the invention
    The invention aims to overcome the drawbacks mentioned above and to overcome the difficulties mentioned above by proposing a turbomachine turbine comprising a turbine distributor stage at least partly in CMC, the mounting of which is simplified and adapted to maintain the ring sectors in a deterministic way while allowing the ring sector to deform independently of the metallic parts at the interface.
    An object of the invention provides a turbomachine turbine comprising a casing and a turbine distributor stage, the turbine distributor stage comprising an external metal support ring and integral with the housing, an internal metal support ring, and a plurality of ring sectors of composite material with a ceramic matrix forming a crown extending between the external support ring and the internal support ring and having an internal ring and an external ring forming between them a fluid flow stream, the crown defining an axial direction and a radial direction. Each ring sector has an interior platform forming a part of the interior shell, an exterior platform forming a portion of the exterior shell, and at least one blade extending between the exterior platform and the interior platform, said at least one blade being integral with the exterior and interior platforms. The external platform of each sector comprises a first portion provided with an internal face forming the external surface of the fluid flow stream, and a second portion radially distant and external to the first portion, the second portion of the external platform being fixed to the external support ring.
    According to a general characteristic of the invention, the interior platform comprises a first tab extending in the radial direction projecting inwardly from an axial end upstream of the interior platform, and the internal support ferrule comprises a shoulder s' extending projecting in the radial direction outward, the shoulder being positioned upstream of the first tab and abutting in the axial direction against said first tab.
    The attachment of the CMC ring sector to the external metal support ring enables the efforts of gases exerted on the blade and the platforms to be taken up. This system, which thus comprises a radial fixing of the ring sector in CMC to an external metallic ferrule for support as well as an axial support to an element of the support structure comprising the external ferrule and the internal ferrule, thus makes it possible to have a deterministic hold of the distributor on the casing, which allows better control of positioning and movements, and therefore, the clearances, crucial for engine performance.
    In a first aspect of the turbine, the turbine may further comprise at least one reinforcement disposed in the radial direction between the first portion and the second portion of the external platform, said at least one reinforcement comprising a first wall bearing against a face radially outer of the first portion and a second wall bearing against a radially inner face of the second portion, at least one reinforcement being fixed to the outer support ring with the second portion of the outer platform.
    The region extending radially between the first portion and the second portion is the most mechanically stressed, the lever arm of the pressure forces being maximum there. The reinforcement forms a thickening of the platform in this region which allows it to stiffen and lower the stresses which are exerted there.
    In a second aspect of the turbine, the second portion of the external platform can be fixed to the external support ring using at least one assembly comprising a screw and a nut, the screw passing through the external platform of the sector and the external support ring
    In a third aspect of the turbine, the second portion of the external platform of each sector can comprise at least one element of rotation stop and the external support ferrule can comprise at least one complementary element of rotation stop configured to cooperate with a stop element in rotation of the external platform.
    The rotational stop thus makes it possible to facilitate the positioning and the assembly of the distributor stage and to resume the moment around the radial axis.
    The rotational stop can be formed by an orifice in the second portion of the external platform of each sector and, for each external platform orifice, a centering lug extending radially projecting inwards from the external metal ferrule, the centering pins being configured to cooperate each with an external platform orifice to maintain the sector in position in an axial direction and a circumferential direction of the distributor stage.
    Alternatively, the rotational stop may be formed by a notch provided in the second portion of the outer platform of each ring sector and a stop extending radially projecting inward from the outer metal ferrule and configured for cooperate with one of said notches.
    In a fourth aspect of the turbine, the first portion of the outer platform may include a portion projecting outward in the radial direction from an upstream end of the outer platform.
    Said radial part thus makes it possible to improve the tightness of the fluid flow stream.
    In a fifth aspect of the turbine, said at least one blade of each ring sector has a hollow profile defining an internal housing extending between the inner platform and the outer platform, the inner and outer platforms of each ring sector each have an orifice communicating with said internal housing of said at least one blade, and each ring sector of the distributor stage comprises at least one mast passing through said platform orifices and the internal housing of said at least one blade, said mast being fixed to said casing and in connection with said ring sector and said internal support ferrule, the connection being able to be direct or indirect.
    As mentioned above, an additional difficulty is generated by the pressure differential between the upstream and downstream of the interior platform of the distributor stage and of the casing which is attached to it. This housing is used to create a seal between the rotor and the stator. The pressure difference can reach a value between 2 to 50 bars. This creates a significant effort which is a source of significant stress, especially in the grip area, by generating a moment via the lever arm that is the blade. This pressure difference is the source of a force which, if it were exerted on the CMC, would be too high taking into account the admissible materials.
    The mast makes it possible to provide a means of fixing a ring sector of a distributor stage in CMC from above, that is to say to the casing, while minimizing the bending moment, insofar as the bending length is reduced by about half by the mast passing through the annular sector, the force being already greatly reduced by the fact that the distributor stage according to the invention does not take up the force linked to the pressure difference on the internal shell.
    Each ring sector of the distributor stage is thus maintained in a deterministic manner, that is to say so as to avoid the ring sector starting to vibrate and controlling its position, and this while allowing the ring sector to deform under the effects of temperature and pressure inter alia independently of the metallic parts in interface.
    The turbine according to the invention thus makes it possible to have a distributor stage taking up the pressure differential forces in the vein on the blade not by the CMC elements, but by the metal mast which benefits from a better admissible than the elements in CMC.
    In a sixth aspect of the turbine, the mast may include at least one projecting portion extending in a plane transverse to the radial direction in which the mast extends and in connection with the blade to maintain the blade in position.
    The sleeve defines a ball joint making it possible to minimize the force due to the aerodynamic moment without modifying the integration of the ring sector in the turbine. Indeed, the ball thus formed inside the blade leaves the blade free to move around the axis defined by the mast.
    In a seventh aspect of the turbine, the interior platform of each sector may further include a second radial lug projecting in the radial direction inward from a downstream end of the interior platform, the interior platform being attached to the internal support ferrule by pinching the first and second radial lugs of the internal platform in the axial direction between said shoulder of the internal support ferrule and a clamp comprising two jaws extending in the radial direction outwards and held in place constraint towards each other against the second radial leg of the interior platform.
    In a variant, the internal support ferrule may comprise a perforated crown comprising orifices for receiving one end of the mast, and a retaining ring on which the crown is mounted.
    In an eighth aspect of the turbine, the mast may be hollow and include perforations over its entire height to deliver a flow of cooling air, the air flow being routed inside the mast from the casing.
    The mast may be made of metallic material so as to offer good mechanical strength, the mast taking up all the aerodynamic forces to transfer them to the casing.
    The mast can be made of any other material.
    Each ring sector can include a plurality of blades, at least one of which includes a mast.
    In a ninth aspect of the turbine, the second portion of the outer platform, the blade and the first tab of the inner platform are formed in one and the same weaving piece of composite material with a ceramic matrix, which makes it possible to strengthen the structure of the ring area.
    The invention also relates to a turbomachine comprising at least one turbomachine turbine as defined above.
    Another subject of the invention is also an aircraft comprising at least one turbomachine as defined above.
    Brief description of the drawings.
    The invention will be better understood on reading the following, for information but not limitation, with reference to the accompanying drawings in which:
    - Figure 1 is a schematic view of a ring sector of a distributor stage in a plane defined by the radial direction and the axial direction of the ring according to a first embodiment of the invention;
    - Figure 2 shows a sectional view of the ring sector of Figure 1 in a plane defined by the axial direction and the circumferential direction of the distributor stage;
    - Figure 3 shows a schematic sectional view of the ring sector of Figure 1 in a plane defined by the radial direction and the axial direction;
    - Figure 4 is an exploded schematic view of the ring sector of Figure 1;
    - Figure 5 is a schematic view of a ring sector of a distributor stage in a plane defined by the radial direction and the axial direction of the ring according to a second embodiment of the invention;
    - Figure 6 shows a sectional view of the ring sector of Figure 5 in a plane defined by the axial direction and the circumferential direction of the distributor stage;
    - Figure 7 shows a schematic sectional view of the ring sector of Figure 5 in a plane defined by the radial direction and the axial direction;
    FIG. 8 is an exploded schematic view of the ring sector of FIG. 5.
    Detailed description of embodiments
    FIG. 1 illustrates a schematic view of a ring sector of a distributor stage in a plane defined by the radial direction and the axial direction of the distributor stage according to a first embodiment of the invention.
    Figures 2 to 4 respectively show a sectional view in a plane defined by the axial direction and the circumferential direction, a schematic sectional view in a plane defined by the radial direction and the axial direction and an exploded schematic view of the sector of Figure 1 ring.
    A high pressure turbine 1 of a turbomachine, for example an aeronautical turbine engine, as shown partially in FIG. 1, comprises a plurality of fixed distributor stages 2 which alternate with wheels movable in the flow direction, indicated by a arrow in FIG. 1, of the gas flow F in the turbine 1 and which are mounted in a turbine casing 4.
    Each movable wheel comprises a plurality of vanes having an inner ferrule, and at least one blade extending from the inner ferrule and linked thereto. On the inner side of the inner shell, the blade is extended by a foot engaged in a housing for a disc. On the outside, the tips of the blades face an abradable material carried by a ring to seal the tips of the blades.
    Throughout the present text, the terms “interior” or “internal” and “exterior” or “external” are used with reference to the position or the orientation relative to the axis of rotation of the turbine 1 which defines the direction axial D A of the turbine 1.
    The blades of the movable wheel can be traditional metal blades or blades made of CMC material obtained for example as described in documents WO 2010/061140, WO 2010/116066, WO 2011/080443.
    At least one of the distributor stages 2 of the turbine 1 is formed by joining several ring sectors 20 of CMC material to form a complete ring. The arrow D A indicates the axial direction of the distributor stage 2 while the arrow Dr indicates the radial direction of the distributor stage 2.
    Each ring sector 20 of the distributor stage 2 comprises an interior platform 24, an exterior platform 26 and a blade 28 extending between the interior and exterior platforms 24 and 26 and integral with these. As a variant, several blades could extend between the interior and exterior platforms of the same distributor sector. Once assembled with the casing 4 of the turbine 1, the sectors 20 form a single ring of distributors 2 having an inner ferrule formed by the juxtaposition of the inner platforms 24 of the sectors 20 and an outer ferrule formed by the juxtaposition of the outer platforms 26 of the sectors 20.
    The inner ferrule and the outer ferrule form between them a fluid flow stream 45 inside which the gas flow F flows during operation of the turbine 1.
    Throughout the text, the terms “upstream” and “downstream” are used with reference to the direction of flow of gas flow F in the stream 45 indicated by an arrow.
    The interior platforms 24 forming the interior ferrule of the distributor stage 2 each comprise a first portion 241 and a second portion 242 in contact with one another and integral with the ring sector 20. The first and second portions 241 and 242 can be molded together or else woven together or joined together differently during gas consolidation or during the so-called "Melt Infiltration" infiltration operation in English of the ring sector and corresponding to a rise of silicon by liquid through capillarity within the textile.
    The interior platforms 24 each have an exterior surface 24e intended to be in contact with the gas flow F and formed by the surface of the first portion 241 of the interior platforms 24 oriented radially outward, and therefore disposed radially opposite the exterior platforms 26 forming the outer shell. The interior platforms 24 also have an interior surface 24i disposed opposite the axis of rotation of the turbine 1, and formed by the surface of the second portion 242 of the interior platforms 24 oriented radially inward.
    The outer platforms 26 each comprise a first portion 261 and a second portion 262 secured to the ring sector 20. The first and second portions 261 and 262 of the outer platforms 26 can be molded or woven or else secured to the ring sector 20 during its conception. The outer platforms 26 each have an outer surface 26e disposed opposite the casing 4 and formed by the surface of the second portion 262 of the outer platforms 26 oriented radially outward. The external platforms 26 also have an internal surface 26i intended to be in contact with the gas flow F and formed by the surface of the first portion 261 of the external platforms 26 oriented radially inwards, and therefore disposed radially opposite the platforms 24 forming the inner ring and facing the axis of rotation of the turbine 1.
    The sectors 20 forming the distributor stage 2, the inner platform 24 of each sector 20 therefore has a portion of the outer surface and a portion of the inner surface of the outer shell, and the outer platform 26 of each sector 20 also has a portion of the outer surface and a portion of the inner surface of the inner shell. The blade 28 of each sector 20 extends between the outer surface 24e of the inner platform 24 of the ring sector 20 and the inner surface 26i of the outer platform 26 of the ring sector 20, and an extension 280 of the blade 28 also extends between the first portion 261 and the second portion 262 of the external platform 26.
    The rectifier stage 2 further comprises an internal metallic ferrule 5 and an external metallic ferrule 9 between which extends the crown formed by the assembly of the ring sectors 20 of the distributor stage 2. The internal metallic ferrule 5 is secured to the housing 4.
    The internal metallic ferrule 5 has an annular portion extending in the axial direction D A and in the circumferential direction D c and comprising at each end 51 and 52 in the axial direction D a , that is to say at one end upstream 51 and a downstream end 52, an upstream hooking lug 53 and a downstream hooking lug 54 extending in the radial direction Dr outward, that is to say towards the interior platform 24, and more particularly its internal surface 24i, of the ring sector of the ring 20, and towards the external metallic shell 9.
    The second portion 242 of the inner platform 24 of the ring sector 20 has, in the axial direction D A , an upstream end 2421 and a downstream end 2422 each having a tab 243 and 244 projecting in the radial direction Dr towards the inside.
    The upstream hooking lug 53 has an upstream surface 530 and a downstream surface 535, the downstream surface 535 bears against the upstream end 2421 of the second portion 242 of the inner platform 24 of the ring sector 20, and more particularly against an upstream surface 2430 of the upstream tab 243 projecting from the upstream end 241 of the interior platform 24.
    The internal metallic ferrule 5 further comprises a portion 55 projecting in the radial direction Dr inward in the extension of the downstream hooking lug 54. The projecting portion 55 and the downstream latching tab 54 are in the same radial plane defined by the radial direction Dr and the circumferential direction D c .
    The downstream hooking lug 54 has an upstream surface 540 and a downstream surface 545. The downstream surface 545 bears against the downstream lug 244 formed at the downstream end 242 of the inner platform 24 of the ring sector 20.
    To keep the internal platform 24 in position, the internal metallic ferrule 5 further comprises a locking ring 56 which can be produced in one piece or be circumferentially sectored. The locking ring 56 includes a flat surface extending in the radial direction Dr. The locking ring 56 is fixed using screws 57 and nuts 58, the screws 55 passing through the locking ring 56 and the protruding portion 55 radially inward of the internal metallic ferrule 5 via two coaxial holes made respectively in the locking ring 56 and in the protruding portion 55 radially inward of the internal metallic ferrule 5.
    The internal metallic ferrule 5 is configured so that the tightening of the locking ring 56 against the projecting portion 55 radially inward of the internal metallic ferrule 5 via the nut 58 and the screw 57 make it possible to grip the downstream tab 244 projecting radially from the downstream end 242 of the inner platform 24 of the ring sector 20 between two jaws formed by the downstream hooking tab 54, on the one hand, and the locking ring 56 somewhere else.
    The internal platform 24, and more particularly its second portion 242, is thus taken in a vice in the axial direction D A using an axial clamp of the internal metallic ferrule of support 5 formed by the upstream hooking lug 53 and the assembly formed by the downstream hooking lug 54 and the locking ring 56. This configuration makes it possible to apply axial stress downstream to each ring sector 20 in order to axially maintain the sectors of ring 20.
    In addition, in the first embodiment illustrated in FIGS. 1 to 4, the internal metallic ferrule 5 comprises an annular seal 70 shaped to be inserted between the downstream hooking lug 54 and the downstream lug 244, between the downstream lug 244 and the locking ring 56, and between the portion 55 projecting radially inwards and the locking ring 56.
    The external metallic ferrule 9 comprises a lug 90 for centering each ring sector 20. The lug 90 is in the form of a fixed pin, or integral with the external metallic ferrule 9. The external metallic ferrule 9 has an inner surface 91 and an outer surface 92 in the radial direction Dr. The lug 90 extends from the inner surface 91 in the radial direction Dr inward.
    The second portion 262 of the external platform 26 of the ring sector 20 comprises a first orifice 263 configured to cooperate with a lug 90 for centering the external metallic ferrule 9. When the rectifier stage 2 is assembled, the external surface 26e of the external platform 26 of the ring sector 20 is in abutment against the internal surface 91 of the external metallic ferrule 9 and the centering lug 90 crosses the corresponding orifice of the external metallic ferrule 9 and the first orifice 263 of the second portion 262 of the outer platform 26.
    In addition, to secure the ring sector 20 to the external metal ring 9, the second portion 262 of the external platform 26 of the ring sector comprises a second orifice 264 intended to cooperate with a screw 95 passing through the external metal ring 9 through a first orifice 93 of the external metallic ferrule 9 and the second orifice 264 of the second portion 262 of the external platform 26 of the ring sector 20. The screw 95 cooperates with a nut 96 to secure the external metallic ferrule 9 and the ring sector 20 together.
    The screw 95 and the lug 90 of the same ring sector 20 are arranged on either side of the extension 280 of the blade 28 of the ring sector 20 to improve the blocking of the ring sector around a radial axis. Likewise, the second orifice 264 and the first orifice 263 of the second portion 262 of the interior platform 26 are disposed on either side of the extension 280 of the blade 28 of the ring sector 20.
    As illustrated in FIG. 2, each blade 28 has a hollow profile having an interior housing 285 extending over the entire height of the blade 28, that is to say between the interior platform 24 and the exterior platform 26 of the ring sector 20. The internal platform 24 of each ring sector 20 comprises an orifice 245 whose shape corresponds to the section of the internal housing 285 in the plane in which the internal platform 24 extends. Similarly, the external platform 26 of each ring sector 20 comprises an orifice 265 whose shape corresponds to the section of the internal housing 285 in the plane in which the internal platform extends 26. The orifices 245 and 265 of the internal platforms 24 and external 26 are made in the extension of the interior housing 285 of the blade 28.
    The interior housing 285 of the blade 28 and the orifices 245 and 265 of the interior 24 and exterior 26 platforms can be connected to a cooling system delivering a flow of cooling air from the casing 4 to the blade 28 and the interior platforms. 24 and exterior 26.
    As illustrated in FIGS. 1 to 4, the turbine 1 further comprises, for each ring sector 20, a mast 6 extending in the radial direction Dr. The mast 6 comprises a mast head 61 bearing on the surface 92 of the external metal shell 9, and a rod 62 projecting from the head 61 in the radial direction Dr towards the inside and configured to pass through the external metal shell 9, the internal housing 285 of the blade 28 and the orifices 245 and 265 of the internal 24 and external 26 platforms being aligned with the internal housing 285 of the blade 28.
    The mast 6 further comprises a projecting portion 63 extending in a plane transverse to the radial direction Dr in which the mast 6 extends. In the illustrated embodiment, the protruding portion 63 of the mast 6 forms an annular shoulder extending over a portion of the mast 6 intended to be in the internal housing 285 of the blade 28. The protruding portion 63 of the mast 6 forms a protuberance at least part of which is in contact with the blade 28 to maintain the blade 28 in position.
    In addition, the internal support ferrule 5 comprises orifices 500 configured to receive the masts 6. The mast 6 makes it possible to provide a means of fixing the sector 20 of the CMC ring from above, that is to say at the casing 4, while minimizing the bending moment, insofar as the bending length is reduced by about half by the mast 6 crossing the annular sector. Each ring sector 20 of the distributor stage is thus held in a deterministic manner, that is to say so as to prevent the ring sector 20 from vibrating and controlling its position, and this while allowing the ring sector 20 to deform under the effects of temperature and pressure, among other things independently of the metal parts at the interface.
    In the case where each ring sector included several blades, the turbine would comprise, at most, a corresponding number of masts for each distributor ring sector.
    In the embodiment illustrated in FIGS. 1 to 4, the external platform 26 of the ring sector 20 further comprises first and second reinforcements 266 and 267 arranged on either side of the extension 280 of blade 28 and radially between the first portion 261 and the second portion 262 of the external platform 26. Each of the two reinforcements 266 and 267 comprises a first wall, respectively 2662 and 2672, bearing against a radially external face of the first portion 261 of the platform outer 26, that is to say the face of the first portion 261 opposite the second portion 262 of the outer platform 26, and a second wall, respectively 2664 and 2674, bearing against a radially inner face of the second portion 261 of the external platform 26, that is to say say the face of the second portion 262 opposite the first portion 261 of the external platform 26.
    The second wall 2664 of the first reinforcement 266 comprises an orifice 2666 intended to be coaxial with the first orifice 263 of the second portion 262 of the external platform 26 and crossed by the centering lug 90. The second wall 2674 of the second reinforcement 267 comprises an orifice 2676 intended to be coaxial with the second orifice 264 of the second portion 262 of the external platform 26 and traversed by the screw 95, the nut 96 coming to bear on a radially internal surface of the second wall 2674 of the second reinforcement 267 .
    The first and second reinforcements 266 and 267 can be added during the gaseous consolidation phase or during the "Melt Infiltration" operation and thus secured to the ring sector 20.
    In the first embodiment illustrated in FIGS. 1 to 4, the ring sector 20 further comprises a notch 29 produced in the second portion 262 of the external platform 26 and in the second wall 2664 of the first reinforcement 266, and the external metallic ferrule 9 comprises, for each ring sector 20, a stop 94 configured to cooperate with the notch 29 of the external platform 26 of the ring sector 20. The notch 29 extends in a plane comprising the direction axial D A and the circumferential direction D c and the stop 94 extends in a plane comprising the axial direction D A and the radial direction Dr.
    In addition, the first portion 261 of the external platform 26 comprises a main portion 2610 defining an external wall of the flow stream 45 for the flow of the gas flow F and a radial portion 265 projecting in the radial direction Dr towards the outside from an upstream axial end 2611 of the first portion 261.
    FIG. 5 illustrates a schematic view of a ring sector of a distributor stage in a plane defined by the radial direction and the axial direction of the ring according to a second embodiment of the invention.
    Figures 6 to 8 respectively show a sectional view in a plane defined by the axial direction and the circumferential direction, a schematic sectional view in a plane defined by the radial direction and the axial direction and a schematic exploded view of the sector of Figure 5 ring.
    The elements identical to the second embodiment illustrated in FIGS. 1 to 4 bear the same numerical references.
    The second embodiment differs from the first embodiment in that the internal support ring 5 comprises a support ring 50 and a holding ring 59 arranged around the support ring 50.
    The retaining ring 59 comprises orifices 590 configured to receive the masts 6. The retaining ring 59 further comprises an upstream hooking lug 53 extending in the radial direction Dr outward from an upstream axial end 591 of the retaining ring 59, that is to say towards the internal platform 24, and more particularly its internal surface 24i, of the ring sector crown 20, and towards the external metallic ring 9. The downstream surface 535 of the upstream hooking lug 53 bears against the upstream end 2421 of the second portion 242 of the inner platform 24 of the ring sector 20, and more particularly against an upstream surface 2430 of the upstream lug 243 projecting from the upstream end 241 of the interior platform 24.
    The retaining ring 59 also comprises an upstream radial retaining flange 536 extending in the radial direction Dr inwards from the upstream end 591 of the retaining ring. The upstream radial retaining flange 536 bears in the axial direction D a against a shoulder 505 extending in the radial direction Dr outward from an upstream axial end 501 of the support ring 50.
    The invention thus provides a turbomachine turbine comprising a turbine distributor stage in CMC, the assembly of which is simplified and adapted to maintain the ring sectors in a deterministic manner while allowing the ring sector to deform independently of the metal parts in interface.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Turbine (1) of a turbomachine comprising a casing (4) and a turbine distributor stage (2), the turbine distributor stage (2) (1) comprising an external support ring (9) made of metal and integral with the casing (4), an internal support ferrule (5) made of metal, and a plurality of ring sectors (20) of composite material with ceramic matrix forming a crown and extending between the external support ferrule (9) and the internal support ring (5), the ring sectors (20) defining an axial direction (D A ) and a radial direction (Dr), and each ring sector (20) having an internal platform (24) and an outer platform (26) which delimits a fluid flow stream (F), and at least one blade (28) extending between the outer platform (26) and the inner platform (24) and fixed to these, the external platform (26) of each sector (20) comprising a first portion (261) provided with an internal face (26i) which del mimics the flow stream (45) of fluid flow (F), and a second portion (262) radially distant and external to the first portion (261), the second portion (262) of the external platform (26) being fixed to the external support ring (9), the internal platform (24) comprising a first tab (243) extending in the radial direction (Dr) projecting inwards from an upstream axial end (241) of the internal platform (24), and the internal support ring (5) comprising a shoulder (53) projecting in the radial direction (Dr) outwards, the shoulder being positioned upstream of the first tab (243) and in abutment in the axial direction (D A ) against said first tab (243).
    [2" id="c-fr-0002]
    2. Turbine (1) according to claim 1, comprising at least one reinforcement (266, 267) disposed in the radial direction (Dr) between the first portion (261) and the second portion (262) of the outer platform (26) , said at least one reinforcement (266, 267) comprising a first wall (2662, 2672) bearing against a radially external face of the first portion (261) of the external platform (26) and a second wall (2664, 2674) resting against a radially internal face of the second portion (261) of the external platform (26), at least one reinforcement (266, 267) being fixed to the external support ring (9) with the second portion (262) of the outer platform (26).
    [3" id="c-fr-0003]
    3. Turbine (1) according to one of claims 1 or 2, in which the second portion (262) of the external platform (26) is fixed to the external support ring (9) using at least an assembly comprising a screw (95) and a nut, the screw (95) passing through the external platform (26) of the sector (20) and the external support ring (9).
    [4" id="c-fr-0004]
    4. Turbine (1) according to one of claims 1 to 3, in which the second portion (262) of the external platform (26) of each sector (20) comprises at least one element of rotation stop (263, 29 ) and the external support ring (9) comprises at least one complementary rotational stop element (90, 94) configured to cooperate with a rotational stop element (263, 29) of the external platform (26).
    [5" id="c-fr-0005]
    5. Turbine (1) according to one of claims 1 to 4, wherein the first portion (261) of the outer platform (26) comprises a portion (2615) projecting outwardly in the radial direction (Dr) from an upstream end (2611) of the external platform (26).
    [6" id="c-fr-0006]
    6. Turbine (1) according to one of claims 1 to 5, wherein said at least one blade (28) of each ring sector (20) has a hollow profile defining an internal housing (285) extending between the interior platform (24) and the exterior platform (26), the interior and exterior platforms (24, 26) of each ring sector (20) each have an orifice (245, 265) communicating with said internal housing (285) of said at least one blade (28), and each ring sector (20) of the distributor stage (2) comprises at least one mast (6) passing through said orifices (245, 265) of the platforms (24, 26) and the internal housing (285) of said at least one blade (28), said mast (6) being fixed to said casing (4) and in connection with said sector (20) and said internal support ring (5).
    [7" id="c-fr-0007]
    7. Turbine (1) according to claim 6, wherein the mast (6) comprises at least one portion (63) projecting in the axial direction in connection with the blade (28) to maintain the blade (28) in position.
    [8" id="c-fr-0008]
    8. Turbine (1) according to one of claims 1 to 7, wherein the inner platform (24) of each sector (20) further comprises a second radial tab (244) projecting in the radial direction ( Dr) inwards from a downstream end of the interior platform (24), the interior platform (24) being fixed to the internal support ring (5) by pinching the first and second radial lugs (243, 244) of the inner platform (24) in the axial direction (D A ) between said shoulder (51) of the internal support ring (5) and a clamp comprising two jaws (54, 56) extending in the radial direction (Dr) towards outside and held towards each other against the second radial tab (244) of the inner platform (24).
    [9" id="c-fr-0009]
    9. Turbine (1) according to one of claims 6 or 7, in which the internal support ring (5) comprises a perforated ring (59) comprising orifices (590) for receiving one end of the mast (6) , and a retaining ring (50) on which the crown (59) is mounted.
    [10" id="c-fr-0010]
    10. Turbine (1) according to one of claims 6 to 9, wherein the mast (6) is hollow and includes perforations over its entire height to deliver a flow of cooling air, the air flow being routed inside the mast (6) from the housing (4).
    [11" id="c-fr-0011]
    11. Turbine (1) according to one of claims 1 to 10, in which the second portion (262) of the outer platform (26), the blade (28) and the first tab (243) of the inner platform (24 ) are formed in a single weaving piece of ceramic matrix composite material.
    [12" id="c-fr-0012]
    12. Turbomachine comprising at least one turbomachine turbine (1) according to one of claims 1 to 11.
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    同族专利:
    公开号 | 公开日
    WO2019202259A2|2019-10-24|
    US20210172330A1|2021-06-10|
    FR3080146B1|2021-04-02|
    CN111989462A|2020-11-24|
    WO2019202259A3|2020-01-09|
    EP3781793A2|2021-02-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2973435A1|2011-03-30|2012-10-05|Snecma|CMC TURBINE DISPENSER ADAPTED TO THE SUPPORT OF AN INTERNAL METAL TURBINE CASTER BY AXIAL CONTACT|
    WO2012146875A1|2011-04-28|2012-11-01|Snecma|Turbine engine comprising a metal protector for a composite part|
    WO2013079859A1|2011-12-01|2013-06-06|Herakles|Hollow-blade turbine vane made from composite material, turbine or compressor including a nozzle or guide vane assembly formed by such blades, and turbomachine comprising same|
    EP3009601A1|2014-09-30|2016-04-20|United Technologies Corporation|Airfoil assembly with spacer and tie-spar|WO2021084203A1|2019-10-31|2021-05-06|Safran Aircraft Engines|Turbomachine turbine having a cmc nozzle with load spreading|
    WO2021224565A1|2020-05-06|2021-11-11|Safran Aircraft Engines|Improved cmc guide vane for a turbomachine turbine|
    EP3960986A1|2020-09-01|2022-03-02|Solar Turbines Incorporated|Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine|FR2939129B1|2008-11-28|2014-08-22|Snecma Propulsion Solide|TURBOMACHINE TURBINE IN COMPOSITE MATERIAL AND PROCESS FOR MANUFACTURING THE SAME.|
    FR2943942B1|2009-04-06|2016-01-29|Snecma|PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE OF COMPOSITE MATERIAL|
    FR2946999B1|2009-06-18|2019-08-09|Safran Aircraft Engines|CMC TURBINE DISPENSER ELEMENT, PROCESS FOR MANUFACTURING SAME, AND DISPENSER AND GAS TURBINE INCORPORATING SAME.|
    FR2953885B1|2009-12-14|2012-02-10|Snecma|TURBOMACHINE DRAFT IN COMPOSITE MATERIAL AND METHOD FOR MANUFACTURING THE SAME|
    FR2979662B1|2011-09-07|2013-09-27|Snecma|PROCESS FOR MANUFACTURING TURBINE DISPENSER SECTOR OR COMPRESSOR RECTIFIER OF COMPOSITE MATERIAL FOR TURBOMACHINE AND TURBINE OR COMPRESSOR INCORPORATING A DISPENSER OR RECTIFIER FORMED OF SUCH SECTORS|FR3076578B1|2018-01-09|2020-01-31|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    法律状态:
    2019-03-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-10-18| PLSC| Search report ready|Effective date: 20191018 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1853345A|FR3080146B1|2018-04-17|2018-04-17|CMC DISTRIBUTOR WITH EFFORT RELIEF|
    FR1853345|2018-04-17|FR1853345A| FR3080146B1|2018-04-17|2018-04-17|CMC DISTRIBUTOR WITH EFFORT RELIEF|
    US17/047,224| US20210172330A1|2018-04-17|2019-04-17|Load-bearing cmc nozzle diaphragm|
    PCT/FR2019/050914| WO2019202259A2|2018-04-17|2019-04-17|Load-bearing cmc nozzle diaphragm|
    EP19772778.7A| EP3781793A2|2018-04-17|2019-04-17|Load-bearing cmc nozzle diaphragm|
    CN201980026082.8A| CN111989462A|2018-04-17|2019-04-17|Load bearing CMC nozzle diaphragm|
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