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    • 专利摘要:
    A turbine ring assembly comprises ring sectors (10) of ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3) having a first and a second annular flange ( 32, 36), each ring sector having first and second tabs (14, 16) held between the two annular flanges (32, 36) of the ring support structure (3). First and second holding members (40, 41) integral with the first annular flange (32) being accommodated in first and second openings (142, 143) of the first leg (14) while first and second holding members secured to the second annular flange (36) are housed in first and second openings of the second lug (16). A radial clearance is being present cold between the openings and the portion of the holding elements present in said openings. The first and second annular flanges (32, 34) comprise on their opposite side of the first and second lugs (14, 16) a plurality of bearing portions (34, 38) distributed circumferentially on the flanges, the end (141, 161) of the first and second legs (14, 16) of each ring sector being cold in contact with two bearing portions (34, 36).
    公开号:FR3049003A1
    申请号:FR1652392
    申请日:2016-03-21
    公开日:2017-09-22
    发明作者:Gilles Lepretre；Thierry Tesson；Adele Lyprendi；Thomas Revel
    申请人:SNECMA SAS；Herakles SA；
    IPC主号:
    专利说明:

    Background of the invention
    The field of application of the invention is in particular that of aeronautical gas turbine engines. The invention is however applicable to other turbomachines, for example industrial turbines.
    Ceramic matrix composite materials, or CMCs, are known to retain their mechanical properties at high temperatures, which makes them suitable for constituting hot structural elements.
    In aeronautical gas turbine engines, improving efficiency and reducing certain pollutant emissions lead to the search for operation at ever higher temperatures. In the case of all-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 very hot flows, typically higher than the temperature bearable by the metallic material. This cooling has a significant impact on the engine performance 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 turbine, which would however improve the performance of aircraft engines.
    Furthermore, a set of metal turbine ring deforms under the effect of heat flow, which changes the clearance at the flow path and, therefore, the performance of the turbine. This is why the use of CMC for different hot parts of the engines has already been considered, especially since CMCs have the additional advantage of lower density than refractory metals traditionally used.
    Thus, the realization of turbine ring sectors in one piece CMC is described in particular in document US 2012/0027572. The ring sectors comprise an annular base whose inner face defines the inner face of the turbine ring and an outer face from which extend two leg portions whose ends are engaged in housings of a structure. metal ring support. The use of ring segments in CMC significantly reduces the ventilation required to cool the turbine ring. However, maintaining the ring sectors in position remains a problem in particular with respect to the differential expansions that can occur between the metal support structure and the CMC ring sectors. This is why it is necessary to provide a minimum clearance between the assembled parts. However, such a game does not allow good control of the shape of the vein nor a good behavior of the ring sectors in case of touch with the top of the blades of the turbine. In addition, the presence of such a game causes vibrational problems.
    OBJECT AND SUMMARY OF THE INVENTION The object of the invention is to avoid such drawbacks and proposes for this purpose a turbine ring assembly comprising a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a structure. ring carrier having a first and a second annular flange, each ring sector having an annular base portion with, in a radial direction of the turbine ring, an inner face defining the inner face of the annular ring. turbine and an outer face from which extend first and second legs, the tabs of each ring sector being held between the two annular flanges of the ring support structure. The first leg of each ring sector has first and second openings in which are housed a portion respectively of a first and a second holding members integral with the first annular flange, a radial clearance being present cold between the first and second openings of the first leg and the portion of the holding members present in said first and second openings. The holding members are of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, the first opening having an oblong shape extending in the circumferential direction of the ring. of turbine. The second leg of each ring sector comprises first and second openings in which are housed a portion of a third and a fourth holding members integral with the second annular flange respectively, a radial clearance being present cold between the first and second openings of the second leg and the portion of the holding members in said first and second openings. The holding members are of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, the first opening having an oblong shape extending in the circumferential direction of the ring. turbine, the first and second openings of the first tab being aligned axially with the first and second openings of the second tab. The first annular flange comprises on its face facing the first leg of each ring sector a plurality of bearing portions distributed circumferentially on the first flange, the end of the first leg of each ring sector being cold in contact with two support portions. The second annular flange comprises on its face facing the second leg of each ring sector a plurality of support portions distributed circumferentially on the second flange, the end of the second leg of each ring sector being cold in contact with two support portions.
    Due to the plurality of bearing portions on the annular flanges of the ring support structure, it is possible to keep the ring sectors free of play at their cold mounting on the ring support structure. the ring sectors being maintained, on the one hand, by the contact between the integral holding members of the annular flanges of the ring support structure and the openings in the legs of the ring sectors and, on the other hand, by the contact between the support portions present on the annular flanges of the ring support structure and the tabs of the ring sectors. The turbine ring assembly of the invention is furthermore remarkable in that it allows, however, to provide a static cold clearance between the integral holding members of the annular flanges of the ring support structure and the openings present in the legs of the ring sectors at an area of the holding elements different from that in contact with the openings. It is thus possible to take up the loss of hot holding of the support portions due to the expansion of the ring support structure by the expansion of the holding elements in the openings of the legs of the ring sectors which reduce the play. static present cold.
    According to a particular characteristic of the turbine ring assembly of the invention, the first and second holding members are respectively formed by first and second pins integral with the first annular flange and in that the third and fourth elements of maintenance are respectively formed by third and fourth pins integral with the second annular flange.
    According to a first particular aspect of the turbine ring assembly of the invention, the bearing portions on the first and second annular flanges are spaced from each other by a recessed portion extending in a circumferential direction. This recess makes it easier to mount the ring sectors on the ring support structure.
    According to a second particular aspect of the turbine ring assembly of the invention, it comprises a plurality of eccentric adjustable clamping members, each clamping member comprising a flange eccentrically attached to the clamp member. clamping, each flange forming a bearing portion on the first and second annular flanges. By using the eccentric clamping elements, it is possible to adjust the cold supports between the ring sectors and the ring support structure.
    According to a third particular aspect of the turbine ring assembly of the invention, the first leg of each ring sector comprises two bearing surfaces in contact respectively with two bearing portions of the first annular flange, the two bearing surfaces extending in the same first bearing plane, the upper edge of the first oblong opening being aligned with the first bearing plane, the upper part of the second opening being tangent to said first plane of contact; 'support. Similarly, the second leg of each ring sector comprises two bearing surfaces in contact respectively with two bearing portions of the second annular flange, the two bearing surfaces extending along the same second bearing plane , the upper edge of the first oblong opening being aligned with the second support plane, the upper part of the second opening being tangent to said second support plane. This alignment of the contact zones on a support plane makes it possible to avoid any relative movement related to the radial expansion of thermal expansion coefficient and to keep the same contact zones both cold and hot.
    According to a fourth particular aspect of the turbine ring assembly of the invention, the second opening of the first leg of each ring sector has an oblong shape, the upper edge of the second oblong opening being aligned with the first support plane, and wherein the second opening of the second leg of each ring sector has an oblong shape, the upper edge of the second oblong opening being aligned with the second support plane, the end of the first leg of each ring sector comprising a recess located between the two bearing surfaces and in which is housed a centering element integral with the first annular flange, the end of the second leg of each sector of ring comprising a recess located between the two bearing surfaces and wherein is housed a centering element integral with the second annular flange. By using two oblong apertures in each leg of the ring sectors, the relative displacement between the ring support structure and the ring sectors is symmetrized. This maintains a good coincidence between the median axis of each ring sector and the equivalent radius on the ring support structure. The centering element makes it possible to avoid off-centering of the ring sectors during thermal expansions.
    According to a fifth particular aspect of the turbine ring assembly of the invention, the first and second integral holding members of the first radial flange and the third and fourth integral holding members of the second radial flange are each formed by an eccentric adjustable clamping element. By using eccentric clamping elements for each holding element, the radial height adjustment capability of the ring sectors with respect to the ring support structure is further increased and, therefore, the clearance adjustment between ring sectors.
    Brief description of the drawings. The invention will be better understood on reading the following, by way of indication but not limitation, with reference to the accompanying drawings in which: - Figure 1 is a first schematic perspective view of an embodiment of a set turbine ring according to the invention; FIG. 2 is a second schematic perspective view of the turbine ring assembly of FIG. 1; - Figure 3 is a sectional view of the assembly of the turbine ring of Figure 1 along the sectional plane III shown in Figure 1; - Figure 4 is a sectional view of the assembly of the turbine ring of Figure 2 according to the sectional plane VI indicated in Figure 2; FIG. 5 schematically shows the mounting of a ring sector in the ring support structure of the ring assembly of FIGS. 1 to 4; FIG. 6 is a first schematic perspective view of another embodiment of a turbine ring assembly according to the invention; FIG. 7 is a second schematic perspective view of the turbine ring assembly of FIG. 6; - Figure 8 is a sectional view of the assembly of the turbine ring of Figure 7 along the sectional plane VIII shown in Figure 7; FIG. 9 is a sectional view of a ring sector of the entire turbine ring of FIGS. 6 and 7; FIG. 10 is a first schematic perspective view of another embodiment of a turbine ring assembly according to the invention; Fig. 11 is a second schematic perspective view of the turbine ring assembly of Fig. 10; Figure 12 is a schematic perspective view of a ring sector of the turbine assembly of Figures 10 and 11; FIG. 13 is a sectional view of the assembly of the turbine ring of FIG. 11 along the section plane XIII indicated in FIG. FIG. 14 is a sectional view of a ring sector of the entire turbine ring of FIGS. 10 and 11.
    Detailed description of embodiments
    FIGS. 1 and 2 show a high pressure turbine ring assembly comprising a turbine ring 1 made of ceramic matrix composite material (CMC) and a metal ring support structure 3. The turbine ring 1 surrounds a set rotary blades (not shown). The turbine ring 1 is formed of a plurality of ring sectors 10, with Figures 1 and 2 being radial sectional views. The arrow Da indicates the axial direction of the turbine ring 1 while the arrow Dr indicates the radial direction of the turbine ring 1.
    Each ring sector 10 has, in a plane defined by the axial axis Da radial direction Dr, a substantially P-shaped section or inverted π. Each ring sector 10 comprises an annular base 12 with, in the radial direction Dr of the ring, an inner face coated with a layer 13 of abradable material defining the gas flow 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. The terms "upstream" and "downstream" are used herein with reference to the direction of flow of the gas stream. in the turbine (arrow F).
    The ring support structure 3 which is integral with a turbine casing 30 comprises an annular upstream radial flange 32 having on its face 32a opposite the upstream tab 14 of the ring sectors 10 a plurality of bearing portions. 34 distributed circumferentially on the flange. The end 141 of the upstream leg 14 of each ring sector 10 is in cold contact with two bearing portions 34 of the annular upstream radial flange 32. By "cold" is meant in the present invention, the temperature at which the ring assembly is located when the turbine is not operating, that is to say at an ambient temperature which may be for example about 25 ° C. In the example described here the end 141 of each lug 14 comprises a first and a second bearing surface 1410 and 1411 respectively in contact with two bearing portions 34. A recessed portion 1412 being present between the two surfaces of FIG. support 1410 and 1411 to facilitate mounting of the ring sectors 10 between the flanges of the ring support structure 3.
    On the downstream side, the ring support structure comprises an annular downstream radial flange 36 having on its face 36a opposite the downstream tab 16 of the ring sectors 10 a plurality of bearing portions 38 distributed circumferentially on the flange. The end 161 of the downstream tab 16 of each ring sector 10 is in cold contact with two bearing portions 38 of the annular downstream radial flange 36. In the example described here, the end 161 of each leg 16 comprises a first and a second bearing surface 1610 and 1611 respectively in contact with two bearing portions 38. A recessed portion 1612 is present between the two bearing surfaces 1610 and 1611 in order to facilitate the mounting of the bearing sectors. ring 10 between the flanges 32 and 36 of the ring support structure 3.
    The upstream leg 14 of each ring sector 10 has a first opening 142 in which is housed a portion of a first holding member, here a pin 40, integral with the annular upstream radial flange 32 and a second opening 143 in which is housed a portion of a second holding member, here a pin 41, integral with the annular upstream radial flange 32. The pins 40 and 41 are respectively mounted in orifices 320 and 321 present on the annular upstream radial flange 32 (FIG. 5). The pins 40 and 41 are hooped in the orifices 320 and 321 of the annular upstream radial flange 32 by known metal assemblies such as H6-P6 adjustments or other strength arrangements that allow the holding of these elements cold.
    A radial clearance J1 is present cold between the first and second openings 142, 143 of the upstream leg 14 and the portion of the pins 40, 41 present in said first and second openings, the clearance J1 being present in the lower part of the openings 142. and 143 in the radial direction Dr (FIG. 3). The pins 40 and 41 are in contact with the upper part respectively of the openings 142 and 143 in the radial direction Dr, that is to say in an area radially opposite to that where the clearance J1 is present. It is thus possible to keep the ring sectors free of play in their cold mounting on the ring support structure while providing a static cold play between the holding elements integral with the annular flanges of the support structure. ring and the apertures present in the tabs of the ring sectors at the portion of the holding elements opposite to that in contact with the openings so as to accommodate the differential expansions of the holding elements with respect to the ring sectors. .
    In the embodiment described here, the first opening 142 has an oblong shape extending in the circumferential direction of the turbine ring while the second opening 143 has a cylindrical shape.
    The pins 40 and 41 are made of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors. The expansion of the pins 40 and 41 respectively in the first and second openings 142 and 143 contributes to the hot maintenance of the ring sectors 10 on the ring support structure 3, the game J1 being reduced or filled by the expansion of the pieces 40 and 41. "Hot" means here the temperatures to which the ring assembly is subjected during operation of the turbine, these temperatures being between 600 ° C and 900 ° C.
    The downstream tab 16 of each ring sector 10 has a first opening 162 in which is housed a portion of a third holding member, here a pin 50, integral with the annular downstream radial flange 36 and a second opening 163 in which is housed a part of a fourth holding member, here a pin 51, integral with the annular downstream radial flange 36. The pins 50 and 51 are respectively mounted in orifices 360 and 361 present on the annular downstream radial flange 36. The pins 50 and 51 are hooped in the orifices 360 and 361 of the annular downstream radial flange 36 by known metal assemblies such as H6-P6 adjustments or other strength fixtures that allow the holding of these elements cold.
    A radial clearance J2 is present cold between the first and second openings 162, 163 of the downstream tab 16 and the portion of the pins 50, 51 present in said first and second openings, the clearance J2 being present in the lower part of the openings 162. and 163 in the radial direction Dr (Figure 4). The pins 50 and 51 are in contact with the upper part respectively of the openings 162 and 163 in the radial direction Dr, that is to say in an area radially opposite to that where the clearance J2 is present. It is thus possible to keep the ring sectors free of play in their cold mounting on the ring support structure while providing a static cold play between the holding elements integral with the annular flanges of the support structure. ring and the apertures present in the tabs of the ring sectors at the portion of the holding elements opposite to that in contact with the openings so as to accommodate the differential expansions of the holding elements with respect to the ring sectors. .
    In the embodiment described herein, the first opening 162 has an oblong shape extending in the circumferential direction of the turbine ring while the second opening 163 has a cylindrical shape.
    The pins 50 and 51 are made of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors. The expansion of the pins 50 and 51 respectively in the first and second openings 162 and 163 contributes to the hot maintenance of the ring sectors 10 on the ring support structure 3, the game J2 being reduced or filled by the expansion of the pieces. 50 and 51.
    The first oblong openings 142 and 162 respectively on the tabs 14 and 16 are axially aligned with respect to the axis of the turbine ring 1 which is parallel to the axial direction Da. Similarly, the second openings 163 and 163 present respectively on the tabs 14 and 16 are aligned axially with respect to the axis of the turbine ring 1.
    In addition, the inter-sector sealing is provided by sealing tabs housed in grooves facing in the opposite edges of two neighboring ring sectors. A tongue 22a extends over almost the entire length of the annular base 12 in the middle portion thereof. Another tab 22b extends along the tab 14 and on 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 to ensure the sealing function at the temperatures encountered in service.
    Conventionally, ventilation orifices 33 formed in the flange 32 make it possible to supply cooling air to the outside of the turbine ring 10.
    A method of making a turbine ring assembly corresponding to that shown in FIGS. 1 and 2 is now described.
    Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix .
    For the production of the fiber preform, it is possible to use ceramic fiber yarns, for example SiC fiber yarns, such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon", or carbon fiber yarns.
    The fiber preform is advantageously made by three-dimensional weaving, or multilayer weaving with development of debonding zones to separate the preform portions corresponding to the tabs 14 and 16 of the sectors 10.
    The weave can be interlock type, as illustrated. Other weaves of three-dimensional weave or multilayer can be used as for example multi-web or multi-satin weaves. Reference can be made to WO 2006/136755.
    After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification can be achieved in particular by chemical vapor infiltration (CVI) which is well known in itself.
    A detailed example of manufacture of ring sectors in CMC is described in particular in document US 2012/0027572.
    The ring support structure 3 is made of a metallic material such as a Waspaloy® or inconel 718 alloy.
    The realization of the turbine ring assembly is continued by mounting the ring sectors 10 on the ring support structure 3. As illustrated in FIG. 5, the tabs 14 and 16 of each ring sector 10 are positioned between the upstream and downstream annular radial flanges 32 and 36 so as to place the two bearing surfaces 1410 and 1411 present on the end of the lug 14 in contact with the bearing portions 34 of the upstream radial flange annular 32 and the two bearing surfaces 1610 and 1611 present on the end of the lug 16 in contact with the bearing portions 38 of the annular downstream radial flange 36. Each ring sector 10 is also positioned so as to align, on the one hand, the openings 142 and 143 of the lug 14 respectively with the orifices 320 and 321 of the annular upstream radial flange 32 and, on the other hand, the openings 162 and 163 of the lug 16 respectively with the orifices 360 and 361 of the downstream radial flange annul Area 36. The pins 40, 41, 50, 51 are then respectively engaged in the openings and orifices thus aligned, the pins 40, 41, 50, 51 being each respectively shrunk in the orifices 320, 321, 360 and 361. A cold , the ring sectors 10 are held, on the one hand, by the support portions 34 and 38 of the flanges 32 and 36 of the ring support structure 3 which are respectively in contact with the ends 141 and 161 of the tabs 14 and 16 and, on the other hand, by the pins 40,41, 50, 51 each respectively in contact with the upper part of the orifices 320, 321, 360 and 361. These two contact zones (bearing portions and pions) on the ring sectors keep them cold on the ring support structure without mounting clearance, that is to say without the possibility for the ring sectors to have a relative displacement by relative to the ring support structure. When hot, the expansion of the flanges of the ring support structure no longer makes it possible to maintain the ring sectors at the support portions 34 and 36. The hot hold is ensured both by the expansion of the pins 40 and 41 in the openings 142 and 143 of the lug 14 which reduces the clearance Jl and by the expansion of the pins 50 and 51 in the openings 162 and 163 of the lug 16 which reduces the clearance J2.
    Figures 6 to 9 show another embodiment of a high pressure turbine ring assembly of the invention which differs from that described above in relation to Figures 1 to 5 in that the bearing portions fixed at the flanges of the ring support structure are replaced by eccentric clamping elements and that the contact areas between the tabs of the ring sectors and the flanges of the ring support structure are coplanar, these two differences can be implemented separately or combined in the same set of turbine ring, and this in combination with the embodiments already described above.
    More precisely, as illustrated in FIGS. 6 and 7, the annular upstream radial flange 32 'of the ring support structure 3' comprises on its face 32a 'opposite the upstream lug 14' of the ring sectors 10 ' a plurality of flanges 61 and 71 respectively belonging to eccentric clamping elements 60 and 70 and corresponding to support portions of the flanges on the ring sectors. Each eccentric clamping member 60, 70, respectively, comprises a threaded shank 62, 72 respectively, which is placed in an orifice 322, 323 respectively, present on the flange 32 '. The flange 61, respectively 71, here in the form of a cylindrical pin, is eccentrically fixed to the threaded rod 62, respectively 72. The flange 61, respectively 71, has the side of the face 32a 'opposite the leg upstream 14 ', is held in a determined position by clamping a nut 63, 73 respectively, on the threaded rod 62, respectively 72.
    Support surfaces 1413 and 1414 present on the upstream tab 14 'are respectively in cold contact with the two flanges 61 and 71 present on the face 32a' of the flange 32 'opposite the upstream leg 14' of each sector ring 10 '.
    On the downstream side, the annular downstream radial flange 36 'of the ring support structure 3' comprises on its face 36a 'facing the downstream tab 16' of the ring sectors 10 'a plurality of flanges 81 and 91 belonging to respectively to eccentric clamping elements 80 and 90 and corresponding to support portions of the flanges on the ring sectors. Each eccentric clamping member 80, respectively 90, comprises a threaded rod 82, 92 respectively, which is placed in an orifice 362, respectively 363, present on the flange 36 '. The flange 81, respectively 91, here in the form of a cylindrical pin, is eccentrically fixed on the threaded rod 82, respectively 92. The flange 81, respectively 91, has the side of the face 36a 'opposite the leg downstream 16 ', is held in a determined position by clamping a nut 83, 93 respectively, on the threaded rod 82, 92 respectively.
    Support surfaces 1613 and 1614 present on the downstream tab 16 'are respectively in cold contact with the two flanges 81 and 91 present on the face 36a' of the flange 36 'opposite the downstream tab 16' of each sector ring 10 '.
    By using the eccentric clamping elements 60, 70, 80 and 90, it is possible to adjust the cold bearings between the ring sectors and the ring support structure. The eccentric clamping elements may have other shapes than that described above. The flange of these elements may for example consist of a pad (part having a flat) rather than a cylindrical member.
    As for the high-pressure turbine ring assembly described above with reference to FIGS. 1 to 5, the upstream tab 14 'of each ring sector 10' has a first opening 142 'in which a part a first holding member, here a pin 40 ', integral with the annular upstream radial flange 32' and a second opening 143 'in which is housed a portion of a second holding member, here a pin 4Γ, integral with the annular upstream radial flange 32 '. The pins 40 'and 41' are respectively mounted in orifices 320 'and 321' present on the annular upstream radial flange 32 '.
    A radial clearance is present cold between the first and second openings 142 ', 143' of the upstream leg 14 'and the portion of the pins 40', 41 'present in said first and second openings, the clearance being present in the lower part openings 142 'and 143' in the radial direction Dr (not shown in Figures 6 to 9). The pins 40 'and 41' are in contact with the upper part respectively of the openings 142 'and 143' in the radial direction Dr, that is to say in an area radially opposite to that where the game is present. In the embodiment described here, the first opening 142 'has an oblong shape extending in the circumferential direction of the turbine ring while the second opening 143' has a cylindrical shape.
    The pins 40 'and 4Γ are made of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors. The expansion of the pins 40 'and 41' respectively in the first and second openings 142 'and 143' participates in the hot maintenance of the ring sectors 10 'on the ring support structure 3', the clearance being reduced or filled by the expansion of the pawns 40 'and 41'.
    The downstream leg 16 'of each ring sector 10' has a first opening 162 'in which is housed a portion of a third holding member, here a pin 50' integral with the annular downstream radial flange 36 'and a second opening 163 'in which is housed a portion of a fourth holding member, here a pin 5Γ integral with the annular downstream radial flange 36'. The pins 50 'and 51' are respectively mounted in orifices 360 'and 361' present on the annular downstream radial flange 36 '.
    A radial clearance 32 'is present cold between the first and second openings 162', 163 'of the downstream tab 16' and the part of the pins 50 ', 51' present in said first and second openings, the set J2 'being present in the lower part of the openings 162 'and 163' in the radial direction Dr (FIG. 8). The pins 50 'and 51' are in contact with the upper part respectively of the openings 162 'and 163' in the radial direction Dr, that is to say in an area radially opposite to the one where the game is present. It is thus possible to keep the ring sectors free of play in their cold mounting on the ring support structure while providing a static cold play between the holding elements integral with the annular flanges of the support structure. ring and the apertures present in the tabs of the ring sectors at the portion of the holding elements opposite to that in contact with the openings so as to accommodate the differential expansions of the holding elements with respect to the ring sectors. .
    In the embodiment described here, the first opening 162 'has an oblong shape extending in the circumferential direction of the turbine ring while the second opening 163' has a cylindrical shape.
    The pins 50 'and 51' are made of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors. The expansion of the pins 50 'and 51' respectively in the first and second openings 162 'and 163' participates in the hot maintenance of the ring sectors 10 'on the ring support structure 3', the clearance J2 'being reduced or filled by the expansion of the pins 50 'and 51'.
    As illustrated in FIG. 9, the two bearing surfaces 1613 and 1614 present on the downstream tab 16 'extend along the same first bearing plane PA. The upper edge of the first oblong opening 162 'present on the downstream tab 16' is aligned with the first support plane PA while the upper part of the second opening 163 'present on the downstream tab 16' is tangent to the first support plan PA. Thus, all the zones or points of support of the annular downstream radial flange 36 'constituted by the flanges 81 and 91, on the one hand, and the pins 50' and 51 ', on the other hand, on the downstream flap 16 of each ring sector 10 'are aligned on the same support plane PA. This alignment of the contact zones on a support plane makes it possible to avoid any relative movement related to the radial expansion coefficient variations of thermal expansion and to keep the same contact zones both cold and hot (the positioning cold and hot areas of contact between the bearing points of the annular downstream radial flange and the downstream leg being respectively shown in solid lines and hatched in Figure 9).
    Similarly, the two bearing surfaces 1413 and 1414 present on the upstream leg 14 'extend along the same second bearing plane (not shown in Figures 6 to 9). The upper edge of the first oblong opening 142 'present on the upstream tab 14' is aligned with the second support plane while the upper part of the second opening 143 'present on the upstream tab 14' is tangent to the second support plan. Thus, all the zones or points of support of the annular upstream radial flange 32 'constituted by the flanges 61 and 71, on the one hand, and the pins 40' and 41 ', on the other hand, on the upstream leg 14 of each ring sector 10 'are aligned on the same support plane. This alignment of the contact zones on a support plane makes it possible to avoid any relative movement related to the radial expansion of thermal expansion coefficient and to keep the same contact zones both cold and hot.
    FIGS. 10 to 14 show another embodiment of a high pressure turbine ring assembly of the invention which differs from that described above in relation with FIGS. 6 to 9 in that, on the one hand, the apertures present in each ring sector lug and intended to receive a portion of a holding member integral with the annular flanges of the ring support structure are all oblong in shape, each ring segment lug comprising in addition, a housing for a centering element which is also integral with the annular flanges of the ring structure, and in that, on the other hand, the holding elements, part of which is intended to be present in the openings in the legs of the ring structure. each ring sector are eccentric clamping elements. These two differences can be implemented separately or combined in the same set of turbine ring, and this in combination with the embodiments already described above.
    More specifically, the upstream leg 14 "of each ring sector 10" has a first opening 142 "of oblong shape in which is housed a portion of a first holding member, here an eccentric clamping member 100, integral with the annular upstream radial flange 32 "and a second opening 143" also oblong in which is housed a portion of a second holding member, here an eccentric clamping element 110, integral with the annular upstream radial flange 32 ". Each eccentric clamping element 100, respectively 110, comprises a threaded rod 102, 112 respectively, which is placed in an orifice 324, respectively 325, present on the flange 32 ", the orifice 324, respectively 325, having a cooperating tapping. with the threading of the rod 102, respectively of the rod 112. A flange 101, 111 respectively, here in the form of a cylindrical pin, is fixed eccentrically on the threaded rod 102, respectively 112. The flange 101, respectively 111 , present in the first opening 142 ", respectively in the second opening 143", is placed in a determined position by screwing the threaded rod 102, respectively 112, in the orifice 324, respectively 325, and held in this position by clamping against a nut 103, respectively 113, on the threaded rod 102, respectively 112.
    A radial clearance is present cold between the first and second openings 142 ", 143" of the upstream leg 14 "and the flanges 101, 111 present in said first and second openings (not shown in Figures 10 to 14). 101 and 111 are in contact with a portion respectively of the openings 142 "and 143" in the radial direction DR, that is to say in an area where the game is not present.It is thus possible to maintain the sectors of ring without play in their cold mounting on the ring support structure while providing a static cold play between the integral holding members of the annular flanges of the ring support structure and the openings present in the ring support structure. the legs of the ring areas.
    In the embodiment described herein, the first and second openings 142 "and 143" each have an oblong shape extending in the circumferential direction of the turbine ring.
    The eccentric clamping members 100 and 110 are of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors. The expansion of the flanges 101 and 111 in the first and second openings 142 "and 143" participates in the hot maintenance of the ring sectors 10 "on the ring support structure 3", the clearance being reduced or filled by the expansion flanges 101 and 111.
    The upstream leg 14 "of each ring sector 10" further comprises a housing, here a cutout 144, in which is placed a centering element, here a pin 120, integral with the annular upstream radial flange 32 ".
    The downstream leg 16 "of each ring sector 10" has a first opening 162 "of oblong shape in which is housed a portion of a third holding member, here an eccentric clamping member 130, integral with the radial flange annular downstream 34 "and a second opening 163" also oblong in which is housed a portion of a fourth holding member, here an eccentric clamping member 170 integral with the annular downstream radial flange 34 ". Each eccentric clamping member 130, 170 respectively, comprises a threaded rod 132, 172 respectively, which is placed in an orifice 364, respectively 365, present on the flange 36 ", the orifice 364, respectively 365, having a cooperating tapping. with the threading of the rod 132, respectively of the rod 172. A flange 131, respectively 171, here in the form of a cylindrical pin, is eccentrically fixed on the threaded rod 132, respectively 172. The flange 131, respectively 171 , present in the first opening 162 ", respectively in the second opening 163", is placed in a determined position by screwing the threaded rod 132, 172 respectively, in the orifice 364, respectively 365, and held in this position by clamping counter-nut 133, respectively 173, on the threaded rod 102, respectively 112.
    A radial clearance J2 "is present cold between the first and second openings 162", 163 "of the downstream tab 16" and the flanges 131, 171 present in said first and second openings (Figure 13). The flanges 131 and 171 are in contact with a portion respectively of the openings 162 "and 163" in an area where play is not present. It is thus possible to keep the ring sectors free of play in their cold mounting on the ring support structure while providing a static cold play between the holding elements integral with the annular flanges of the support structure. ring and the openings present in the legs of the ring sectors.
    In the embodiment described herein, the first and second openings 162 "and 163" each have an oblong shape extending in the circumferential direction of the turbine ring. The eccentric clamping members 130 and 170 are of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors. The expansion of the flanges 131 and 171 in the first and second openings 162 "and 163" participates in the hot maintenance of the ring sectors 10 "on the ring support structure 3", the set J 2 "being reduced or filled by dilation of the flanges 131 and 171.
    The downstream leg 16 "of each ring sector 10" further comprises a housing, here a cutout 164, in which is placed a centering element, here a pin 150, integral with the annular downstream radial flange 36 ".
    By using two oblong apertures in each leg of the ring sectors, the relative displacement between the ring support structure and the ring sectors is symmetrized. This maintains a good coincidence between the median axis of each ring sector and the equivalent radius on the ring support structure. The centering element makes it possible to avoid off-centering of the ring sectors during thermal expansions.
    Furthermore, by using eccentric clamping elements for each holding member, the radial height adjustment capability of the ring sectors with respect to the ring support structure is further increased and, therefore, game between the ring areas.
    As for the high pressure turbine ring assembly described above in connection with FIGS. 6 to 9 and as illustrated in FIGS. 10 and 11, the annular upstream radial flange 32 "of the ring support structure 3 "comprises on its face 32a" opposite the upstream tab 14 "ring sectors 10" a plurality of flanges 61 "and 71" respectively belonging to eccentric clamping elements 60 "and 70" and corresponding to portions The eccentric clamping members 60 ", 70" respectively comprise a threaded shank 62 ", respectively 72", which is placed in a hole 322 ", respectively 323", present in the ring sectors. on the flange 32 ". A flange 61 ", respectively 71", here in the form of a cylindrical pin, is eccentrically fixed to the threaded rod 62 ", respectively 72". The flange 61 ", respectively 71", has the side of the face 32a "next to the upstream tab 14", is maintained in a determined position by clamping a nut 63 ", respectively 73", on the threaded rod 62 ", respectively 72".
    Support surfaces 1413 "and 1414" present on the upstream lug 14 "are respectively in cold contact with the two flanges 61" and 71 "present on the face 32a" of the flange 32 "opposite the upstream lug 14 "of each ring sector 10".
    On the downstream side, the annular downstream radial flange 36 "of the ring support structure 3" comprises on its face 36a "opposite the downstream lug 16" of the ring sectors 10 "a plurality of flanges 81" and 91 "respectively belonging to eccentric clamping elements 80" and 90 "and corresponding to support portions of the flanges on the ring sectors Each eccentric clamping element 80", respectively 90 ", comprises a threaded rod 82 ", respectively 92", which is placed in an orifice 362 ", respectively 363", present on the flange 36 ". A flange 81 ", respectively 91", here in the form of a cylindrical pin, is eccentrically fixed to the threaded rod 82 ", respectively 92". The flange 81 ", respectively 91", has the side of the face 36a "opposite the downstream tab 16", is maintained in a determined position by clamping a nut 83 ", respectively 93" on the threaded rod 82 "respectively 92".
    Support surfaces 1613 "and 1614" present on the downstream tab 16 "are respectively in cold contact with the two flanges 81" and 91 "present on the face 36a" of the flange 36 "opposite the downstream tab 16 "of each ring sector 10".
    Thanks to the use of the eccentric clamping elements 60 ", 70", 80 ", 90", 100, 110, 130 and 140, it is possible to adjust the cold bearings between the ring sectors and the structure of the ring support.
    As illustrated in FIG. 14, the two bearing surfaces 1613 "and 1614" present on the downstream tab 16 "extend along the same first bearing plane PA". The upper edge of the first oblong opening 162 "present on the downstream leg 16" is aligned with the first support plane PA "while the upper part of the second opening 163" present on the downstream leg 16 "is tangent in the first plane of support PA ". Thus, all the zones or points of support of the annular downstream radial flange 36 "constituted by the flanges 81" and 91 ", on the one hand, and the flanges 101 and 111, on the other hand, on the downstream flap 16 of each ring sector 10 "are aligned on the same support plane PA This alignment of the contact zones on a bearing plane makes it possible to avoid any relative movement related to the thermal expansion coefficient deviations in the direction radial and maintain the same contact areas both cold and hot (cold and hot positioning of the contact zones between the bearing points of the annular downstream radial flange and the downstream leg being respectively shown in phantom full and hatched in Figure 9).
    Similarly, the two bearing surfaces 1413 "and 1414" present on the upstream lug 14 "extend along the same second bearing plane (not shown in FIGS. 10 to 14) .The upper edge of the first opening of oblong shape 142 "present on the upstream leg 14" is aligned with the second support plane while the upper part of the second opening 143 "present on the upstream leg 14" is tangent to the second support plane. all the zones or points of support of the annular upstream radial flange 32 "constituted by the flanges 61" and 71 ", on the one hand, and the flanges 131 and 171, on the other hand, on the upstream leg 14" of each ring sector 10 "are aligned on the same support plane. This alignment of the contact zones on a support plane makes it possible to avoid any relative movement related to the radial expansion of thermal expansion coefficient and to keep the same contact zones both cold and hot.
    The holding elements and the support portions for each ring sector can be aligned in the radial direction as in the embodiment of FIGS. 1 to 4. The holding elements can also be placed outside. bearing portions in the circumferential direction of each ring sector as in the embodiments of FIGS. 6 to 14. Finally, the holding elements can also be placed inside the bearing portions in the circumferential direction for each ring sector
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    A turbine ring assembly comprising a plurality of ring sectors (10) of ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3) having a first and a second annular flanges (32, 36), each ring sector having an annular base portion (12) with, in a radial direction (DA) of the turbine ring, an inner face defining the inner face of the annular ring; turbine and an outer face from which extend first and second legs (14, 16), the tabs of each ring sector being held between the two annular flanges (32, 36) of the support structure of ring (3), characterized in that the first tab (14) of each ring sector (10) has a first opening (142) in which is housed a portion of a first holding member integral with the first flange ring (32) and a second opening (143) in which e is housed a portion of a second holding member integral with the first annular flange, a radial clearance (Jl) being present cold between the first and second openings (142, 143) of the first tab (14) and the part first and second holding members in said first and second openings, said holding members being of a material having a coefficient of thermal expansion greater than the thermal expansion coefficient of the ceramic matrix composite material of the ring sectors, the first opening having an oblong shape extending in the circumferential direction of the turbine ring, in that the second leg (16) of each ring sector (10) has a first opening (162) in which a portion of a third holding member secured to the second annular flange (36) and a second opening (163) in which is housed a part of a fourth sec element holding the second annular flange, a radial clearance (J2) being present cold between the first and second openings (162, 163) of the second leg (16) and the portion of the third and fourth holding elements present in said first and second openings, said holding members being of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, the first opening having an oblong shape extending into the circumferential direction of the turbine ring, the first and second openings of the first tab being axially aligned with the first and second openings of the second tab, in that the first annular flange (32) comprises on its face (32a) facing the first leg (14) of each ring sector (10) a plurality of support portions (34); circumferentially on the first flange, the end (141) of the first flap (14) of each ring sector being cold in contact with two bearing portions (34), in that the second flange (36) comprises on its face (36a) facing the second lug (16) of each ring sector (10) a plurality of bearing portions (38) distributed circumferentially on the second flange, the end (161) of the second tab (16) of each ring sector being cold in contact with two support portions (38).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the first and second holding members are formed respectively by first and second pins (40, 41) integral with the first annular flange (32) and in that the third and fourth elements of maintenance are formed respectively by third and fourth pins (50, 51) integral with the second annular flange (36).
    [3" id="c-fr-0003]
    3. The assembly of claim 1 or 2, wherein the bearing portions (34, 38) on the first and second annular flanges (32, 36) are spaced from each other by a recessed portion extending into a circumferential direction.
    [4" id="c-fr-0004]
    An assembly according to any one of claims 1 to 3, comprising a plurality of eccentric adjustable clamping elements (60, 70, 80, 90), each clamping member comprising a flange (61; 71; 81; ) fixed eccentrically to the clamping element, each flange forming a bearing portion on the first and second annular flanges (32, 36).
    [5" id="c-fr-0005]
    5. An assembly according to any one of claims 1 to 4, wherein the first tab (140 of each ring sector (100 comprises two bearing surfaces (1413, 1414) in contact respectively with two support portions of the first annular flange (320, the two bearing surfaces extending in the same first bearing plane, the upper edge of the first oblong opening (1420 being aligned with the first support plane, the upper part the second opening (1430 being tangent to said first bearing plane, and wherein the second leg (160 of each ring sector comprises two bearing surfaces (1613, 1614) in contact respectively with two bearing portions of the second annular flange (360, the two bearing surfaces extending along the same second bearing plane (PA), the upper edge of the first oblong opening (1620 being aligned with the second support plane, the upper part of the second open re (1630 being tangent to said second support plane.
    [6" id="c-fr-0006]
    6. An assembly according to any one of claims 1 to 5, wherein the second opening (143'0 of the first tab (14'0 of each ring sector (10'0 has an oblong shape, the upper edge of the second oblong opening being aligned with the first bearing plane, and wherein the second opening (163'0 of the second leg (16) of each ring sector has an oblong shape, the upper edge of the second aperture (163'0 of oblong shape being aligned with the second bearing plane (PA), the end of the first leg (14'0 of each ring sector (10'0 comprising a recess (144) located between the two bearing surfaces (1413 ", 1414") and in which is housed a centering element (120) integral with the first annular flange (32 "), the end of the second leg (16") of each sector ring comprising a recess (164) located between the two bearing surfaces (1613 ", 1614") and in which is housed a centering element (150) integral with the second annular flange (36 ").
    [7" id="c-fr-0007]
    7. An assembly according to any one of claims 1 and 3 to 6, wherein the first and second holding members integral with the first radial flange and the first and second holding member integral with the second radial flange are each formed by a eccentrically adjustable clamping element (100; 110; 130; 170).
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    同族专利:
    公开号 | 公开日
    BR112018069172A2|2019-01-29|
    WO2017162967A1|2017-09-28|
    RU2728671C2|2020-07-30|
    CN109154208B|2021-06-15|
    CA3018664A1|2017-09-28|
    RU2018136798A|2020-04-22|
    EP3433471B1|2020-01-29|
    EP3433471A1|2019-01-30|
    US10655501B2|2020-05-19|
    FR3049003B1|2018-04-06|
    CN109154208A|2019-01-04|
    US20190101027A1|2019-04-04|
    RU2018136798A3|2020-05-29|
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    法律状态:
    2017-02-10| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-22| PLSC| Publication of the preliminary search report|Effective date: 20170922 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-17| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20180717 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180717 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 6 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1652392A|FR3049003B1|2016-03-21|2016-03-21|TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET|
    FR1652392|2016-03-21|FR1652392A| FR3049003B1|2016-03-21|2016-03-21|TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET|
    CA3018664A| CA3018664A1|2016-03-21|2017-03-20|Turbine ring assembly with no cold fitting play|
    US16/086,899| US10655501B2|2016-03-21|2017-03-20|Turbine ring assembly without cold assembly clearance|
    EP17716953.9A| EP3433471B1|2016-03-21|2017-03-20|Turbine shroud seal assembly with specific support in cold conditions|
    CN201780030995.8A| CN109154208B|2016-03-21|2017-03-20|Turbine ring assembly without cold fit clearance|
    RU2018136798A| RU2728671C2|2016-03-21|2017-03-20|Turbine ring assembly without a mounting gap in a cold state|
    PCT/FR2017/050639| WO2017162967A1|2016-03-21|2017-03-20|Turbine ring assembly with no cold fitting play|
    BR112018069172A| BR112018069172A2|2016-03-21|2017-03-20|Turbine ring set.|
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