• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A turbine ring assembly comprises a plurality of ring sectors (10) of ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3) having first and second flanges rings (32, 36), each ring sector (10) having first and second legs (14, 16), the tabs (14, 16) of each ring sector (10) being held between the two flanges annular (32, 36) of the ring support structure (3). The first and second legs (14, 16) of the ring sectors (10) each have an annular groove (140; 160). The first and second annular flanges (32, 36) of the ring support structure (3) each comprise an annular projection (34; 38) respectively housed in the annular groove (140) of the first tab (14) and in the annular groove (160) of the second lug (16) of each ring sector (10). An elastic member (60; 70) is interposed between the annular projection (34) of the first flange (32) and the annular groove (140) of the first lug (14) and between the annular projection (38) of the second flange. (36) and the annular groove (160) of the second leg (16).
    公开号:FR3036436A1
    申请号:FR1554627
    申请日:2015-05-22
    公开日:2016-11-25
    发明作者:Clement Roussille；Gael Evain；Aline Planckeel；Claire Groleau
    申请人:SNECMA SAS；Herakles SA；
    IPC主号:
    专利说明:

    [0001] 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 elevated temperatures, which makes them suitable for forming hot structural elements. In aviation gas turbine engines, improved efficiency and the reduction of 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 the aeronautical engines. 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.
    [0002] Thus, the realization of one-piece CMC turbine ring sectors is described in particular in US 2012/0027572. The ring sectors comprise an annular base whose internal face defines the inner face of the turbine ring and an outer face from which two leg portions extend, the ends of which are engaged in housings of a ring support metal structure.
    [0003] 3036436 2 The use of ring segments in CMC significantly reduces the ventilation needed 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. In addition, another problem lies in the constraints generated by the imposed displacements. Furthermore, the position retention of the ring sectors must be ensured even in the event of contact between the top of a blade of a moving wheel and the inner face of the ring sectors. 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 an inner face defining the inner face of the turbine ring and an outer face from which extend radially a first and a second leg, the tabs of each ring sector being held between the two annular flanges of the ring support structure, characterized in that the first and second legs of the ring sectors each comprise a groove annular on its face facing respectively the first annular flange and the second annular flange of the ring support structure, the first and annular second flanges of the ring support structure each comprising an annular projection on its face opposite one of the ring sector tabs, the annular projection of the first flange being housed in the annular groove of the first ring lug of each ring sector while the annular projection of the second flange is housed in the annular groove of the second leg of each ring sector, and in that at least one elastic member is interposed between the annular projection of the first flange and the annular groove of the first tab and between the annular projection of the second flange and the annular groove of the second tab.
    [0004] By using the attachment geometry of the ring sectors defined above and by interposing an elastic element between the projections of the flanges and the grooves of the ring sector tabs, it ensures a position retention of the sectors of the ring. ring even in case of differential expansions between the sectors and the support structure, the latter being compensated by the elasticity of maintenance. According to one embodiment of the turbine ring assembly according to the invention, each elastic element is formed of a split annular ring mounted elastically preloaded between one of the annular projections 10 and the corresponding groove. According to another embodiment of the turbine ring assembly according to the invention, each elastic element is formed of at least one strip of a rigid material having a corrugated shape. The elastic element can be in this case formed of a corrugated sheet.
    [0005] According to one aspect of the turbine ring assembly according to the invention, each elastic element is interposed between the upper wall of the grooves present on the first tab, respectively on the second tab, of the ring sectors and the upper wall. the annular projection of the first flange, respectively of the second flange, of the ring structure. According to another aspect of the turbine ring assembly according to the invention, each elastic element is interposed between the lower wall of the grooves present on the first leg, respectively on the second leg, ring sectors and the lower wall. the annular projection of the first flange, respectively the second flange, of the ring structure. According to a particular feature of the turbine ring assembly of the invention, the projections of the two annular flanges of the ring support structure exert stress on the annular grooves of the legs of the ring sectors, one of the flanges of the ring support structure being elastically deformable in the axial direction of the turbine ring. By keeping the ring sectors between flanges exerting a constraint on the legs of the sectors via protrusions, and with one of the flanges of the ring support structure being elastically deformable, the contact is further improved and, by Therefore, the tightness between the flanges and the legs even when these elements are subjected to high temperatures. Indeed, the elasticity of one of the flanges of the ring structure makes it possible to compensate for the differential expansions between the tabs of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the stress exerted "cold" by the flanges on the legs of the ring sectors. The elastically deformable flange of the ring support structure may in particular have a thickness less than that of the other flange of said ring support structure.
    [0006] According to another aspect of the turbine ring assembly according to the invention, it further comprises a plurality of pins engaged in both at least one of the annular flanges of the ring support structure and the legs of the ring sectors facing said at least annular flange. The pins serve to block the possible rotation of the ring sectors in the ring support structure. According to another aspect of the turbine ring assembly according to the invention, the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that opposite the legs of the sectors of the invention. ring. The presence of the hooks makes it possible to facilitate the spacing of the elastically deformable flange for inserting the lugs of the ring sectors between the flanges without having to slide the lugs between the flanges in force. According to another embodiment of the turbine ring assembly according to the invention, the ring support structure comprises an annular retaining flange mounted on the turbine casing, the annular retaining flange comprising an annular flange. forming one of the flanges of the ring support structure. The flange comprises a first series of teeth distributed circumferentially on said flange while the turbine casing comprises a second series of teeth distributed circumferentially on said casing, the teeth of the first series of teeth and the teeth of the second. series of teeth forming a circumferential clutch. This connection by interconnection allows easy assembly and disassembly of ring sectors. In another aspect of the turbine ring assembly according to the invention, the turbine casing comprises an annular boss extending between a casing shell and the flange of the ring structure. This prevents upstream-downstream leakage between the housing and the flange.
    [0007] 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: FIG. 1 is a radial half-sectional view showing an embodiment of a turbine ring assembly according to the invention; Figures 2 to 4 show schematically the mounting of a ring sector in the ring support structure of the ring assembly of Figure 1; Figure 5 is a partial half-sectional view showing an alternative embodiment of the turbine ring assembly of Figure 1; FIG. 6 is a radial half-sectional view showing an embodiment of a turbine ring assembly according to the invention; Figures 7 to 11 schematically show the mounting of a ring sector in the ring support structure of the ring assembly of Figure 6; - Figure 12 is a schematic perspective view of the flange of Figures 6 and 8 to 11.
    [0008] DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows 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 ring of turbine 1 surrounds a set of rotating blades 5.
    [0009] The turbine ring 1 is formed of a plurality of ring sectors 10, FIG. 1 being a radial sectional view along a plane passing between two contiguous ring sectors. The arrow DA indicates the axial direction with respect to the turbine ring 1 while the arrow DR indicates the radial direction with respect to the turbine ring 1.
    [0010] Each ring sector 10 has a substantially Tu-shaped cross-section with an annular base 12 whose inner face 30364366 coated with a layer 13 of abradable material defines the flow stream of gaseous flow in the turbine. Upstream and downstream tabs 14, 16 extend from the outer face of the annular base 12 in the radial direction DR. The terms "upstream" and "downstream" are used herein in reference to the flow direction 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 a projection 34 on its face opposite the upstream tabs 14 of the ring sectors 10, the projection 34 being housed in an annular groove 140 10 has on the outer face 14a of the upstream tabs 14. On the downstream side, the ring support structure comprises an annular downstream radial flange 36 having a projection 38 on its face opposite the downstream tabs 16 of the sectors 10, the projection 38 being housed in an annular groove 160 on the outer face 16a of the downstream tabs 16.
    [0011] As will be explained below in detail, the lugs 14 and 16 of each ring sector 10 are preloaded between the annular flanges 32 and 36 so that the flanges exert, at least at "cold", that is, at an ambient temperature of about 25 ° C, a stress on the tabs 14 and 16.
    [0012] On the other hand, in the example described here, the ring sectors 10 are further maintained by blocking pins. More precisely and as illustrated in FIG. 1, pins 40 are engaged both in the annular upstream radial flange 32 of the ring support structure 3 and in the upstream lugs 14 of the ring sectors 10. For this purpose the pins 40 each respectively pass through an orifice 33 formed in the annular upstream radial flange 32 and an orifice 15 formed in each upstream lug 14, the orifices 33 and 15 being aligned during the assembly of the ring sectors 10 on the Likewise, pins 41 are engaged both in the annular downstream radial flange 36 of the ring support structure 3 and in the downstream legs 16 of the ring sectors 10. For this purpose , the pins 41 each pass respectively through an orifice 37 formed in the annular downstream radial flange 36 and an orifice 17 formed in each downstream lug 16, the orifices 37 and 17 being aligned during the assembly of the ring sectors 10 on the support structure of FIG. ring 3.
    [0013] In addition, inter-sector sealing is provided by sealing tabs housed in grooves facing each other in opposite edges of two adjacent 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 a portion of the annular base 12. Another tab 22c extends along the tab 16. At one end, the tab 22c abuts the tab. tongue 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.
    [0014] In a conventional manner, ventilation holes 32a formed in the flange 32 allow cooling air to be supplied to the outside of the turbine ring 10. In accordance with the present invention, at least one elastic element is interposed between each protrusion of the annular flanges of the ring support structure and each annular groove of the legs of the ring sectors. More specifically, in the embodiment described here, a split annular ring 60 is interposed between the upper wall 142 of the groove 140 on the outer face 14a of the upstream lugs 14 of the ring sectors 10 and the upper face 34c of the protrusion 34 of the annular upstream radial flange 32 while a split annular ring 70 is interposed between the upper wall 162 of the groove 160 on the outer face 16a of the downstream lugs 16 of the ring sectors 10 and the upper face 38c of the projection 38 of the annular downstream radial flange 36. The annular split rings 60 and 70 constitute elastic elements in that they have in the free state, that is to say before assembly, a radius greater than radius defined by the upper walls 142 and 162 respectively of the annular grooves 140 and 160. The annular split rings 60 and 70 may be made for example alloy known as "Rene 41". Before assembly, an elastic stress is applied to the rods 60 and 70 to tighten them on themselves and reduce their radius to insert them into the grooves 140 and 160. Once placed in the grooves 140 and 160, the rods 60 and 70 and 160 annular grooves 140 and 160. The rods 60 and 70 thus hold the ring sectors 10 in position on the ring support structure 3. More precisely , the rods 60 and 70 exert a holding force Fm on the ring sectors 10 which is directed in the radial direction DR and 3036436 8 which makes it possible to ensure a contact, on the one hand, between the lower wall 143 of the groove 140 of the upstream lug 14 and the lower face 34b of the projection 34 of the annular upstream radial flange 32, and, on the other hand, between the bottom wall 163 of the groove 160 of the upstream lug 16 and the lower face 5 38b of the projection 38 of the radial flange av al annular 36 (Figure 1). A method of making a turbine ring assembly corresponding to that shown in FIG. 1 is now described. Each ring sector 10 described above is made of ceramic matrix composite material (CMC) for a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix. For producing the fiber preform, 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, may be used. The fiber preform is advantageously made by three-dimensional weaving, or multilayer weaving with the provision of debonding zones enabling the preform portions corresponding to the lugs 14 and 16 of the sectors 10 to be spaced apart. The weaving may be of the 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.
    [0015] After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification being able to be carried out in particular by chemical vapor infiltration (CVI) which is well known in itself. A detailed example of manufacture of CMC ring sectors is described in US 2012/0027572. The ring support structure 3 is made of a metallic material such as a Waspaloy® alloy or known by the name of "inconel 718". 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. 2, the gap E between the end 34a of the annular projection 34 of the annular upstream radial flange 32 and the end 38a of the annular projection 38 of the annular downstream radial flange 36 at "rest", that is to say when no ring sector is mounted between the flanges, is smaller than the distance D between the bottoms 141 and 161 of the annular grooves 140 and 160 respectively of the upstream and downstream legs 14 and 16 of the ring sectors. By defining a spacing E between the projections of the flanges of the lower ring support structure at the distance D between the bottoms of the grooves of the legs of each ring sector, it is possible to mount the ring segments prestressed between the flanges of the ring support structure. However, in order not to damage the tabs of the CMC ring sectors during assembly and in accordance with the invention, the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction DA of the invention. 'ring. In the example described here, it is the annular downstream radial flange 36 which is elastically deformable. Indeed, the annular downstream radial flange 36 of the ring support structure 3 has a reduced thickness relative to the annular upstream radial flange 32, which gives it a certain elasticity. Before assembling the ring sectors 10 on the ring support structure 3, the split rings 60 and 70 are respectively placed against the upper walls 34c and 38c of the projections 34 and 38 of the annular radial flanges 32 and 36. The ring sectors 10 are then mounted one after the other on the ring support structure 3. When mounting a ring sector 10, the annular downstream radial flange 36 is pulled in the direction DA as shown. in Figures 3 and 4 to increase the spacing between the flanges 32 and 36 and allow the insertion of the projections 34 and 38 respectively present on the flanges 32 and 36 in the grooves 140 and 160 present on the legs 14 and 16 Without risk of damaging the ring sector 10. Once the projections 34 and 38 have flanges 14 and 16 inserted into the grooves 140 and 160 of the tabs 14 and 16 and said tabs 14 and 16 positioned to align the holes 33 and 15, on the one hand, and 17 and 37 of on the other hand, the flange 36 is released. The projections 34 and 38 respectively of the flanges 32 and 36 then exert an axial stress (direction DA) of holding on the tabs 14 and 16 of the ring sector while the rods 60 and 70 exert a radial constraint (direction DR ) on the legs 14 and 16 of the sectors. In order to facilitate pulling apart the downstream radial annular flange 36, it comprises a plurality of hooks 39 distributed on its face 36a, which face is opposite to the face 36b of the flange 36 opposite the downstream tabs 16 of the 5 ring sectors 10 (Figure 3). The traction in the axial direction DA of the ring exerted on the elastically deformable flange 36 is here carried out by means of a tool 50 comprising at least one arm 51 whose end comprises a hook 510 which is engaged in a hook 39 present on the outer face 36a of the flange 36.
    [0016] The number of hooks 39 distributed on the face 36a of the flange 36 is defined as a function of the number of tensile points that one wishes to have on the flange 36. This number depends mainly on the elastic nature of the flange. Other forms and arrangements of means for pulling in the axial direction DA on one of the flanges of the ring support structure may of course be contemplated within the scope of the present invention. Once the ring sector 10 has been inserted and positioned between the flanges 32 and 36, pins 40 are engaged in the aligned orifices 33 and 15 respectively formed in the annular upstream radial flange 32 and in the upstream leg 14, and pieces 41 are engaged in the aligned orifices 37 and 17 respectively formed in the annular downstream radial flange 36 and in the downstream lug 16. Each lug 14 or 16 of ring sector may comprise one or more orifices for the passage of a pion of blocking.
    [0017] In an alternative embodiment, the rods 60 and 70 may be placed between the lower wall of the grooves of the legs of the ring sectors and the lower face of the projection of the annular radial flanges. FIG. 5 illustrates this variant embodiment for the upstream tabs 14 of the ring sectors 10 and the annular upstream radial flange 32 of the ring support structure 3. In FIG. 5, the ring 60 is placed between the wall lower 143 of the groove 140 of the upstream tab 14 of the ring sector 10 and the lower face 34b of the projection 34 of the annular upstream radial flange 32. The ring 60 exerts a holding force Fm which is directed in the radial direction DR and which makes it possible to ensure a contact, on the one hand, between the upper wall 142 of the groove 140 of the upstream lug 14 and the upper face 34c of the projection 34 of the annular upstream radial flange 32.
    [0018] Figure 6 shows a high pressure turbine ring assembly according to another embodiment of the invention. As previously described the high pressure turbine ring assembly comprises a turbine ring 101 of ceramic matrix composite material (CMC) and a ring support metal structure 103. The turbine ring 101 surrounds a set of rotary blades 105. The turbine ring 101 is formed of a plurality of ring sectors 110, FIG. 6 being a radial sectional view along a plane passing between two contiguous ring sectors. The arrow DA indicates the axial direction with respect to the turbine ring 101 while the arrow DR indicates the radial direction with respect to the turbine ring 101. Each ring sector 110 has a substantially t-shaped section. inverted with an annular base 112 whose inner face coated with a layer 113 of abradable material defines the stream of gas flow flow in the turbine. Upstream and downstream tabs 114, 116 extend from the outer face of the annular base 112 in the radial direction DR. The terms "upstream" and "downstream" are used herein with reference to the flow direction of the gas flow in the turbine (arrow F).
    [0019] The ring support structure 103 is formed of two parts, namely a first part corresponding to an annular upstream radial flange 132 which is preferably formed integrally with a turbine casing 130 and a second part corresponding to an annular flange of Retention 150 mounted on the turbine housing 130. The annular upstream radial flange 132 has a projection 134 on its opposite side of the upstream lugs 114 of the ring sectors 110, the projection 134 is housed in an annular groove 1140 present on the external face 114a of the upstream tabs 114. On the downstream side, the flange 150 comprises an annular web 157 which forms an annular downstream radial flange 154 having a projection 155 on its face opposite the downstream lugs 116 of the ring sectors 110, the protrusion being housed in an annular groove 1160 has on the outer face 116a of the downstream lugs 116. The flange 150 comprises an annular body 151 extending axially and comprre the upstream side, the annular web 157 and, on the downstream side, a first series 35 of teeth 152 distributed circumferentially on the flange 150 and spaced apart from each other by first engagement passages 3036436 12 153 (FIGS. and 12). The turbine casing 130 has on the downstream side a second series of teeth 135 extending radially from the inner surface of the ferrule 138 of the turbine casing 130. The teeth 135 are distributed circumferentially on the inner surface 138a of the ferrule 138 and spaced from each other by second engagement passages 136 (Figure 9). The teeth 152 and 135 cooperate with each other to form a circumferential clutch. As explained in detail below, the tabs 114 and 116 of each ring sector 110 are preloaded between the annular flanges 132 and 154 so that the flanges exert, at least "cold", that is to say at an ambient temperature of about 25 ° C, a stress on the tabs 114 and 116. Moreover, in the example described here, the ring sectors 110 are further maintained by blocking pins . More specifically, and as illustrated in FIG. 6, pins 140 are engaged both in the annular upstream radial flange 132 of the ring support structure 103 and in the upstream legs 114 of the ring sectors 110. Indeed, the pins 140 each pass respectively through an orifice 133 formed in the annular upstream radial flange 132 and an orifice 115 formed in each upstream lug 114, the orifices 133 and 115 being aligned during the assembly of the ring sectors 110 on the structure. Likewise, pins 141 are engaged both in the annular downstream radial flange 154 of the flange 150 and in the downstream flaps 116 of the ring sectors 110. For this purpose, the pins 141 pass through each one. respectively an orifice 156 formed in the annular downstream radial flange 154 and an orifice 117 formed each downstream lug 116, the orifices 156 and 117 being aligned during mounting of the ring sectors 110 on the annular support structure. In addition, the inter-sector sealing is provided by sealing tabs housed in grooves facing each other in opposite edges of two adjacent ring sectors. A tongue 122a extends over almost the entire length of the annular base 112 in the middle portion thereof. Another tab 122b extends along the tab 114 and a portion of the annular base 112. Another tab 122c extends along the tab 116. At one end, the tab 122c abuts the tab. tongue 122a and on the tongue 122b. The tabs 122a, 122b, 122c are, for example, made of metal and are mounted with cold play in their housings in order to ensure the sealing function at the temperatures encountered in service. Conventionally, ventilation orifices 132a formed in the flange 132 make it possible to bring cooling air to the outside of the turbine ring 110. In addition, the seal between the upstream and the downstream The turbine ring assembly is provided by an annular boss 131 extending radially from the inner surface 138a of the shell 138 of the turbine housing 103 and having a free end in contact with the surface of the housing 151. In accordance with the present invention, at least one resilient member is interposed between each projection of the annular flanges of the ring support structure and each annular groove of the legs of the ring sectors. More specifically, in the embodiment described here, a split annular corrugated sheet 170 is interposed between the upper wall 1142 of the groove 1140 on the outer face 114a of the upstream lugs 114 of the ring sectors 110 and the upper face 134c of the projection 134 of the annular upstream radial flange 132 while a split annular corrugated sheet 20 is interposed between the upper wall 1162 of the groove 1160 present on the outer face 116a of the downstream tabs 116 of the ring sectors 110 and the face upper 155c of the projection 155 of the annular downstream radial flange 154. The annular corrugated sheets 170 and 180 constitute elastic elements. They may in particular be made of metal material such as an alloy known under the name of "René 41" or of composite material such as a material of the A500 type consisting of a carbon fiber reinforcement densified by a SiC self-healing matrix. / B. The corrugated sheets 170 and 180 are alternately in contact with the annular grooves 1140 and 1160 and the protrusions 134 and 155. The corrugated sheets 170 and 180 thus maintain the ring sectors 110 in position on the ring support structure. 103. More precisely, the corrugated sheets 170 and 180 provide elastic retention of the ring sectors 110 in the radial direction DR by alternating points of contact, on the one hand, between the upper wall 1142 of the groove 1140 of the upstream leg 114 and the upper face 134c of the projection 134 of the annular upstream radial flange 132 (for the sheet 170), and, secondly, 3036436 14 between the upper wall 1162 of the groove 1160 of the upstream lug 116 and the upper face 155c of the projection 155 of the annular downstream radial flange 154 (for the sheet 180). A method of making a turbine ring assembly corresponding to that shown in FIG. 6 is now described. Each ring sector 110 described above is made of ceramic matrix composite material (CMC) for a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix. For producing the fiber preform, 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, may be used. The fiber preform is advantageously made by three-dimensional weaving, or multilayer weaving with deliming zones arranged to separate the preform portions corresponding to the tabs 114 and 116 of the sectors 110. The weaving may be of the 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.
    [0020] A detailed example of CMC ring sector fabrication is described in US 2012/0027572. The ring support structure 103 is made of a metallic material such as a Waspaloy® alloy or known as "Inconel 718".
    [0021] The embodiment of the turbine ring assembly is continued by mounting the ring sectors 110 to the ring support structure 103. As illustrated in FIGS. 7 and 8, the ring sectors 110 are firstly fixed by their upstream leg 114 to the annular upstream radial flange 132 of the ring support structure 103 by pins 140 35 which are engaged in the aligned orifices 133 and 115 respectively formed in the annular upstream radial flange 132 and in the upstream lug 114, the annular corrugated sheet 170 having been previously placed against the upper face 134c of the projection 134 of the annular upstream radial flange 132. The projection 134 on the flange 132 is engaged in the grooves 1140 present on the 114. Once all the ring sectors 110 are thus fixed to the annular upstream radial flange 5, the annular retention flange 150 is assembled by interconnection between the turbine casing 103 and the downstream tabs 116 of the ring sectors 110. In accordance with the embodiment described herein, the gap E between the annular upstream radial flange 154 formed by the annular web 157 of the flange 150 and the outer surface 152a of the teeth 152 of said flange is greater than the distance D present between the bottom 1161 of the grooves 1160 of the downstream lugs 116 of the ring sectors and the inner face 135b of the teeth 135 present on the turbine casing 130 (FIG. 8). By defining a gap E between the annular upstream radial flange 15 and the outer surface of the teeth of the upper flange at the distance D between the bottom of the grooves of the downstream lugs of the ring sectors and the internal face of the teeth present on the turbine casing it is possible to mount the ring segments prestressed between the flanges of the ring support structure. However, in order not to damage the legs of the CMC ring sectors during assembly and in accordance with the invention, the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction DA of the ring. In the example described here, it is the annular downstream radial flange 154 present on the flange 150 which is elastically deformable. Indeed, the annular web 157 forming the annular downstream radial flange 154 of the ring support structure 103 has a reduced thickness relative to the annular upstream radial flange 132, which gives it a certain elasticity. As illustrated in FIGS. 9, 10 and 11, the flange 150 is mounted on the turbine casing 130 by placing the annular corrugated plate 180 against the upper face 155c of the projection 155 of the annular upstream radial flange 154 of the flange 150 and by engaging the protrusions 155 in the grooves 1160 present on the downstream tabs 116. In order to fix the flange 150 by interconnection, the teeth 152 present on the flange 150 are first of all positioned vis-à-vis the passages of engagement 136 formed on the turbine casing 130, the teeth 135 on said turbine casing being also placed opposite the engagement passages 153 formed between the teeth 152 on the flange 150. The spacing E being greater than the distance D, it is necessary to apply an axial force FA on the flange 150 in the direction indicated in FIG. 10 in order to engage the teeth 152 beyond the teeth 135 and to allow a rotation R of the flange suiva An angle corresponding substantially to the width of the teeth 135 and 152. After this rotation, the flange 150 is released, the latter then being maintained in axial stress between the upstream tabs 116 of the ring sectors 110 and the inner surface 135b of the teeth 135 of the turbine casing 130. Once the flange thus set up, pins 141 are engaged in the aligned orifices 156 and 117 respectively formed in the annular downstream radial flange 154 and in the downstream leg 116. Each lug 114 or 116 The ring sector may comprise one or more ports for the passage of a blocking pin. In an alternative embodiment, the corrugated sheets 170 and 180 may be placed between the lower wall of the grooves of the legs of the ring sectors and the lower face of the projections of the annular radial flanges. In this case, the corrugated sheets 170 and 180 provide elastic retention of the ring sectors 110 in the radial direction DR by alternating points of contact, on the one hand, between the lower wall 1143 of the groove 1140 of the tab upstream 114 and the lower face 134b of the projection 134 of the annular upstream radial flange 132 (for the sheet 170), and, on the other hand, between the bottom wall 1163 of the groove 1160 of the upstream lug 116 and the face lower 155b of the projection 155 of the annular downstream radial flange 154 (for the sheet 180).
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A turbine ring assembly comprising a plurality of ring sectors (10) of ceramic matrix composite material 5 forming a turbine ring (1) and a ring support structure (3) having first and second flanges rings (32, 36), each ring sector (10) having an annular base portion (12) with an inner face defining the inner face of the turbine ring (1) and an outer face from which radially extend first and second legs (14, 16), the tabs (14, 16) of each ring sector (10) being held between the two annular flanges (32, 36) of the support structure ring (3), characterized in that the first and second lugs (14, 16) of the ring sectors (10) each comprise an annular groove (140; 160) on its face (14a; 16a) facing respectively the first annular flange (32) and the second annular flange (36) of the support structure of a lamb (3), the first and second annular flanges (32, 36) of the ring support structure (3) each having an annular projection (34; 38) on its face facing one of the ring sector tabs, the annular projection (34) of the first flange (32) being housed in the annular groove (140) of the first tab (14) of each ring sector (10) while the annular projection (38) of the second flange (36) is housed in the annular groove (160) of the second leg (16) of each ring sector (10), and in that at least one elastic element is interposed between the annular projection (34) of the first flange (32) and the annular groove (140) of the first lug (14) and between the annular projection (38) of the second flange (36) and the annular groove (160) of the second leg (16). 30
    [0002]
    2. An assembly according to claim 1, characterized in that each elastic element is formed of a split annular ring (60; 70) mounted elastically preloaded between one of the annular projections (34; 38) and the corresponding groove (140; 160). . 35 3036436 18
    [0003]
    3. An assembly according to claim 1, characterized in that each elastic element is formed of at least one strip (170; 180) of a rigid material having a corrugated shape.
    [0004]
    4. An assembly according to any one of claims 1 to 3, characterized in that each elastic element is interposed between the upper wall (142) of the grooves (140) present on the first tab (14), respectively on the second tab ( 16), ring sectors (10) and the upper wall (34c) of the annular projection (34) of the first flange (32), respectively of the second flange (36), of the ring structure (3). ).
    [0005]
    5. An assembly according to any one of claims 1 to 3, characterized in that each elastic element is interposed between the bottom wall (143) of the grooves (140) present on the first leg (14), respectively on the second leg ( 16), ring sectors (10) and the bottom wall (34b) of the annular projection (34) of the first flange (32), respectively of the second flange (36), of the ring structure (3). ).
    [0006]
    An assembly according to any one of claims 1 to 5, characterized in that the projections of the two annular flanges (32, 36) of the ring support structure (3) exert stress on the annular grooves (140, 160) of the tabs (14, 16) of the ring sectors (10) and that one (36) of the flanges of the ring support structure (3) is elastically deformable in the axial direction (DA) of the turbine ring (1).
    [0007]
    A turbine ring assembly according to claim 6, characterized in that the elastically deformable flange (36) of the ring support structure (3) has a thickness smaller than that of the other flange (32). of said ring support structure (3).
    [0008]
    Turbine ring assembly according to claim 6 or 7, characterized in that the elastically deformable flange (36) of the ring support structure (3) comprises a plurality of hooks (39) 3036436 19 distributed over its face (36a) opposite that (36b) opposite the tabs (16) of the ring sectors (10).
    [0009]
    An assembly according to any one of claims 1 to 7, characterized in that the ring support structure comprises an annular retaining flange (150) mounted on the turbine casing (130), the annular retaining flange (150) having an annular web (157) forming one of the flanges (154) of the ring support structure (103) and in that the flange (150) comprises a first series of teeth (152) distributed substantially circumferentially on said flange while the turbine casing (130) comprises a second series of teeth (135) circumferentially distributed on said casing, the teeth (152) of the first set of teeth and the teeth (135) of the second set of teeth (135). series of teeth forming a circumferential clutch. 15
    [0010]
    10. An assembly according to claim 9, characterized in that the turbine casing (130) comprises an annular boss (131) extending between a shell (138) of said casing and the flange (150) of the ring structure ( 103).
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    同族专利:
    公开号 | 公开日
    RU2017144769A3|2019-10-29|
    CA2986663A1|2016-12-01|
    EP3298247A1|2018-03-28|
    JP2018520292A|2018-07-26|
    RU2720876C2|2020-05-13|
    BR112017024891A2|2018-07-31|
    CN107735549A|2018-02-23|
    RU2017144769A|2019-06-24|
    JP6760969B2|2020-09-23|
    CN107735549B|2020-11-06|
    FR3036436B1|2020-01-24|
    US10626745B2|2020-04-21|
    WO2016189224A1|2016-12-01|
    US20180149034A1|2018-05-31|
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    法律状态:
    2016-05-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-25| PLSC| Search report ready|Effective date: 20161125 |
    2017-04-26| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-25| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170725 Owner name: HERAKLES, FR Effective date: 20170725 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 Owner name: SAFRAN CERAMICS, FR Effective date: 20170719 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 4 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554627|2015-05-22|
    FR1554627A|FR3036436B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY WITH HOLDING BY FLANGES|FR1554627A| FR3036436B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY WITH HOLDING BY FLANGES|
    BR112017024891-3A| BR112017024891A2|2015-05-22|2016-05-19|turbine ring set|
    US15/575,968| US10626745B2|2015-05-22|2016-05-19|Turbine ring assembly supported by flanges|
    PCT/FR2016/051175| WO2016189224A1|2015-05-22|2016-05-19|Turbine ring assembly supported by flanges|
    CA2986663A| CA2986663A1|2015-05-22|2016-05-19|Turbine ring assembly supported by flanges|
    EP16729311.7A| EP3298247A1|2015-05-22|2016-05-19|Turbine ring assembly supported by flanges|
    JP2017560765A| JP6760969B2|2015-05-22|2016-05-19|Turbine ring assembly supported by flanges|
    RU2017144769A| RU2720876C2|2015-05-22|2016-05-19|Annular turbine unit supported by flanges|
    CN201680033388.2A| CN107735549B|2015-05-22|2016-05-19|Flange supported turbine ring assembly|
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