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    • 专利摘要:
    A turbine ring assembly comprising a plurality of ring sectors (10) forming a turbine ring (1) and a ring support structure (3) comprising an upstream annular flange (32) and a downstream annular flange (36), each ring sector (10) comprising a first horizontal sealing tongue (21), an upstream vertical sealing tongue (22) and a first downstream vertical sealing tongue (23). Each ring sector (10) further comprises a second horizontal sealing tongue (20) above the first horizontal sealing tongue (21) in the radial direction of the ring. A first bent sealing element (24) is housed both in a vertical groove (42) in the upstream lug (14) and in a second horizontal groove (40) while a second bent sealing element ( 25) is housed in both a first horizontal groove (41) and a first vertical groove (43) in the downstream leg (16).
    公开号:FR3041993A1
    申请号:FR1559457
    申请日:2015-10-05
    公开日:2017-04-07
    发明作者:Lucien Henri Jacques Quennehen；Sebastien Serge Francis Congratel；Clement Jean Pierre Duffau；Matthieu Simon
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION The invention relates to a turbine ring assembly for a turbomachine, which assembly comprises a plurality of one-piece ring sectors of ceramic matrix or metal material composite material and a structure of ring support.
    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 for their good mechanical properties that make them suitable for constituting structural elements, and for their ability to retain these properties at high temperatures.
    In aeronautical gas turbine engines, improving efficiency and reducing polluting 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 high temperature flows. 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. The use of CMC for various hot parts of such engines has already been considered, especially since CMCs have a 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, the seal between the gaseous flow vein on the inner side of the ring sectors and the outer side of the ring sectors remains a problem, and more particularly when the ring sectors have a shape of Pi (π ) reversed. Indeed, this type of ring sector does not have a bath, which does not allow to install a double horizontal seal at or above the supports between the ring sectors and the support structure of these sectors. .
    This sealing problem also arises for metal ring sectors that do not have a bath but whose manufacture is greatly simplified thereby.
    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 made of ceramic matrix or metal material composite material forming a ring of turbine and a ring support structure having an upstream annular flange and a downstream annular flange, each ring sector having a first annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which radially extend an upstream leg and a downstream leg, the upstream and downstream legs of each ring sector being held between the two upstream and downstream annular flanges of the ring support structure, each sector of ring comprising a first horizontal sealing tongue extending along the annular base, the first horizontal sealing tongue being a log in a first horizontal groove present in the annular base, an upstream vertical sealing strip extending along the upstream leg, the upstream vertical sealing tongue being housed in a vertical groove present in the upstream leg and a first downstream vertical sealing tab extending along the downstream leg, the first downstream vertical sealing tongue being housed in a first vertical groove in the downstream leg, characterized in that each ring sector further comprises a second horizontal sealing tab extending over a portion of the annular base above the first horizontal sealing tongue, the second horizontal sealing tongue being housed in a second horizontal groove in the annular base, and a first angled sealing element is housed both in the vertical groove present in the upstream head and in the second horizontal groove while a second bent sealing element is housed both in the first horizontal groove and in the first vertical groove present in the downstream leg, the first vertical groove opening into the first horizontal groove , or while a second bent sealing element is housed both in the second horizontal groove and in the first vertical groove in the downstream leg, the first vertical groove opening into the second horizontal groove.
    With two horizontal sealing tongues superimposed in the radial direction, a double seal is made at the base of the ring which reinforces the inter-sector sealing in the ring, thereby putting the leakage sections in series, and this while ensuring a redirection of the air flowing from the outer side of the ring upstream, that is to say in the movable wheel formed by the rotating blades inside the ring. Moreover, the use of bent sealing elements makes it possible to plug the leaks that may occur at the contact portions between the sealing tabs, that is to say at the orthogonal junctions of the grooves. In the example described here, the first bent sealing element prevents leakage at the contact portion between the first horizontal tongue and the upstream vertical tongue while the second bent sealing element prevents leakage at the level of the contact portion between the first or second horizontal tongue and the downstream vertical tongue.
    According to one embodiment of the turbine ring assembly of the invention, each ring sector further comprises a second downstream vertical sealing tab extending along the downstream leg, the second tab of downstream vertical seal being housed in a second vertical groove present in the downstream leg, the second downstream vertical sealing tab being in contact at one of its ends with the second horizontal sealing tongue, the second vertical groove in the downstream tab opening into the second horizontal groove, the second angled sealing element being housed both in the second horizontal groove and in the second vertical groove present in the downstream tab.
    By adding a second vertical downstream sealing strip, the sealing efficiency is further improved, a first pressure loss being achieved by one of the two downstream vertical tabs before the other downstream vertical sealing tab. The reinforcement of the downstream seal by the use of two vertical tongues is advantageous because the pressure difference between the cavity of the ring and the downstream portion of the vein is high, which increases the suction force of the between these two volumes and, consequently, the risk of leaks.
    According to a particular feature of the turbine ring assembly of the invention, a third angled sealing element is accommodated both in the first horizontal groove and in the first vertical groove in the downstream leg. Leakage is further reduced at the contact portions between the downstream sealing tabs in the ring.
    According to another embodiment of the turbine ring assembly of the invention, each ring sector further comprises a second downstream vertical sealing tab extending along the downstream leg, the second tab downstream vertical sealing strip being housed in a second vertical groove present in the downstream leg, the second downstream vertical sealing tab being in contact with the second horizontal sealing tongue, the second vertical groove present in the downstream tab opening into the first and second horizontal grooves, the second angled sealing element being housed both in the first horizontal groove and in the first vertical groove in the downstream leg.
    By adding a second vertical downstream sealing strip, the sealing efficiency is further improved, a first pressure loss being achieved by one of the two downstream vertical tabs before the other downstream vertical sealing tab.
    According to another embodiment of the turbine ring assembly of the invention, the upstream annular flange comprises a lip in contact with the upstream leg of each ring sector while the downstream annular flange comprises a lip in contact with the downstream leg of each ring sector, the vertical groove present in the upstream leg of each ring sector extending in a direction oblique to the axis of the upstream leg, said vertical groove opening on the outer face of the upstream leg at the lip of the upstream annular flange while the vertical groove in the downstream leg of each ring sector extends in a direction oblique to the axis of the downstream leg, said vertical groove opening on the outer face of the downstream tab at the lip of the downstream annular flange.
    With upstream and downstream vertical grooves extending obliquely in the tabs of each ring sector so as to open at the bearing portions with the annular flanges of the ring support structure, the internal leakage is reduced. areas at these support portions.
    According to a particular characteristic of the turbine ring assembly of the invention, the two annular flanges of the ring support structure exert a stress on the legs of the ring sectors and in that at least one of flanges of the ring support structure is elastically deformable in the axial direction of the ring.
    Due to the presence of at least one elastically deformable flange, the contact between the flanges of the ring support structure and the tabs of the ring sectors can be maintained independently of temperature variations.
    According to another particular feature of the turbine ring assembly of 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 make it possible to block the possible rotation of the ring sectors in the ring support structure and to hold them radially in said structure. the ring support structure and maintain them radially in said structure.
    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 radial half-sectional view showing an embodiment of a set turbine ring according to the invention; Figs. 2A and 2B are partial schematic perspective views showing the positioning of sealing tabs in a ring sector of the turbine ring assembly of Fig. 1; - Figures 3 to 6 are radial half-sectional views each showing another embodiment of a turbine ring assembly according to the invention.
    Detailed description of embodiments
    FIG. 1 shows a high-pressure turbine ring assembly comprising a turbine ring 1, here made of ceramic matrix composite material (CMC), and a metal ring support structure 3. The turbine ring 1 surrounds a rotary blade assembly 5. The turbine ring 1 is formed of a plurality of ring sectors 10, Figure 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.
    Each ring sector 10 has a substantially P-shaped section (π) inverted with an annular base 12 whose inner face coated with a layer 13 of abradable material and / or a thermal barrier defines the flow vein gas flow 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 comprising annular downstream radial flange 36 having a lip 38 on its opposite side of the downstream tabs 16 of the ring sectors 10 , the lip 38 being supported on the outer face 16a of the downstream tabs 16.
    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 "cold", that is to say at room temperature about 20 ° C, but also at all operating temperatures of the turbine, a stress on the legs 14 and 16 and thus a tightening sectors by the flanges. This constraint is maintained at all temperatures at which the ring assembly can be subjected during operation of the turbine and is controlled, that is to say without over-constraining the ring sectors, thanks to the presence of at least one elastically deformable flange as explained above. In addition, conventionally, ventilation holes 32a formed in the flange 32 make it possible to supply cooling air to the outside of the turbine ring 10. The ring sectors 10 are mounted one after the other. others by spacing the annular downstream radial flange 36 by pulling it through a hook 39 in the axial direction Da to increase the spacing between the flanges 32 and 36 and allow the insertion of the tabs 14 and 16 between the flanges 32 and 36 without risk of damage.
    Furthermore, in the example described here, the ring sectors 10 are further maintained by blocking pins. More precisely and as illustrated in FIG. 1, pins 50 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 50 each pass respectively 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 assembly of the ring sectors 10 on the support structure Likewise, pins 51 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 51 each respectively pass 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 assembly of the ring sectors 10 on the ring support structure 3.
    According to the invention, the sealing of the ring is provided by sealing tabs and bent joints. More specifically, as shown in Figures 1, 2A and 2B, each ring sector 10 is provided with a first horizontal sealing tongue 21 which extends over almost the entire length of the annular base 12 between the legs upstream and downstream 14 and 16, a second horizontal sealing tab 20 disposed above the first horizontal tongue and extending over a portion of the length of the annular base 12, a sealing tab vertical upstream 22 which extends along the upstream leg 14 and a downstream vertical sealing tab 23 which extends along the downstream leg 16.
    Each sealing tongue is housed in grooves facing each other in the opposite edges of two neighboring ring sectors. For this purpose, each ring sector 10 comprises a first horizontal groove 41 formed in the annular base 12 and in which is housed the first horizontal sealing tongue 21, a second horizontal groove 40 formed in the annular base 12 above groove 41 and in which is housed the second horizontal sealing tongue 20, an upstream vertical groove 42 formed in the upstream lug 14 in which is housed the upstream vertical sealing tongue 22 and a downstream vertical groove 43 formed in the downstream leg 16 in which is housed the downstream vertical sealing strip 23. The second horizontal groove 40 opens on one side in the lower part of the upstream vertical groove 42 and on the other side in the lower part of the vertical groove downstream 43. Thus, the second horizontal sealing tab 20 is in contact at one end 20a with the verti upstream block 22 and in contact at the other end 20b with the downstream vertical tongue 23. In addition, the downstream vertical groove 43 opens into the first horizontal groove 41 so that the lower end 23b of the vertical downstream sealing tab 23 is in contact with the first horizontal sealing tongue 21. Concerning the first horizontal groove 41, it is preferably made closer to the inner face of the ring sector so that the first sealing tongue 21 find closer to the vein. This reduces inter-sector play and its impact on the top of the blades.
    FIGS. 1, 2A and 2B illustrate a single ring sector 10 in which the tongues 20, 21, 22 and 23 are partially inserted respectively in the grooves 40, 41, 42 and 43. The portion of the tongues 20, 21, 22 and 23 protruding from ring sector 10 (FIG. 2B) are introduced into corresponding grooves in the neighboring ring sector (not shown in FIGS. 1, 2A and 2B).
    The tongues 20, 21, 22 and 23 are for example metallic and are preferably mounted with cold play in the grooves 40, 41, 42 and 43 to ensure the sealing function at the temperatures encountered in service. By way of non-limiting examples, the sealing tabs may be made of cobalt-based alloy such as alloys HA 188 or HS 25, made of high-performance metal material (high melting point), molybdenum, tungsten, or made of CMC composite material.
    In addition, a first sealing element or elbow joint 24 is housed in both the upstream vertical groove 42 and in the second horizontal groove 40 while a second sealing element or elbow joint 25 is housed both in the first horizontal groove 41 and the downstream vertical groove 43. The bent joints 24 and 25 may be formed from folded metal sheets. By way of nonlimiting examples, the bent joints may be made of cobalt-based alloy such as alloys HA 188 or HS 25, made of high-performance metal material (high melting point), molybdenum, tungsten, or material CMC composite. Optionally, a third sealing element or elbow joint can be used, here the sealing element or elbow joint 27 housed both in the second horizontal groove 40 and in the first vertical groove 43 against the second elbow joint 25.
    As for the sealing tongues 20, 21, 22 and 23, the bent joints 24, 25 and 27 are partially introduced respectively into the grooves 42 and 40, into the grooves 41 and 43 and into the grooves 40 and 43. The portion of the bent joints 24 and 25 protruding from the ring sector 10 (FIG. 2B) are introduced into corresponding grooves in the neighboring ring sector (not shown in FIGS. 1, 2A and 2B).
    With two horizontal sealing tongues superimposed in the radial direction Dr, a double seal is made at the base of the ring which reinforces the inter-sector sealing in the ring while ensuring a redirection of the circulating air the outer side of the ring upstream, that is to say in the movable wheel formed by the rotating blades inside the ring. Moreover, the use of the bent joints 24 and 25 makes it possible to block the leaks that may occur at the level of the contact portions between the sealing tongues, that is to say at the level of the orthogonal junctions of the grooves. In the example described here, the elbow 24 prevents leakage at the contact portion between the second horizontal tongue 20 and the upstream vertical tongue 22 while the elbow 25 prevents leakage at the contact portion between the first horizontal tongue 21 and the downstream vertical tongue 23.
    Figure 3 illustrates a high pressure turbine ring assembly according to another embodiment of the invention. In the ring assembly of FIG. 3, the ring support metal structure is identical to the ring support metal structure 3 previously described in connection with FIGS. 1, 2A and 2B and will not be described in FIG. again for the sake of simplification. The ring assembly of FIG. 3 differs from that described above in connection with FIGS. 1, 2A and 2B in that a second downstream vertical sealing tab is present in the downstream leg of each ring sector.
    More specifically, as shown in Figure 3, each ring sector 100 is provided with a first horizontal sealing tab 121 which extends over almost the entire length of the annular base 112 between the upstream and downstream legs 114 and 116, a second horizontal sealing tab 120 disposed above the first horizontal tab and extending over a portion of the length of the annular base 112, an upstream vertical sealing tab 122 which extends along the upstream tab 114, a first downstream vertical sealing tab 123 which extends along the downstream tab 116 and a second downstream vertical sealing tab 126 which extends along the downstream tab 116 upstream of the first tab 123.
    Each sealing tongue is housed in grooves facing each other in the opposite edges of two neighboring ring sectors. For this purpose, each ring sector 100 comprises a first horizontal groove 141 formed in the annular base 112 and in which is housed the first horizontal sealing tongue 121, a second horizontal groove 140 formed in the annular base 112 above groove 141 and in which is housed the second horizontal sealing tongue 120, an upstream vertical groove 142 formed in the upstream lug 114 in which is housed the upstream vertical sealing tongue 122, a first downstream vertical groove 143 formed in the downstream leg 116 in which is housed the first downstream vertical sealing tab 123 and a second downstream vertical groove 146 formed in the downstream leg 116 in which is housed the second downstream vertical sealing tab 126. The second horizontal groove 140 opens on one side in the lower part of the upstream vertical groove 142 and on the other side in the lower part of the second downstream vertical groove 146. Thus, the second horizontal sealing tongue 120 is in contact at one end 120a with the upstream vertical sealing tongue 122 and in contact at the other end 120b with the second tongue downstream vertical 126. In addition, the first downstream vertical groove 143 opens into the first horizontal groove 141 so that the lower end 123b of the downstream vertical sealing tab 123 is in contact with the first horizontal sealing tongue 121.
    A tab 127 is further added between the upper ends of the vertical tabs 123 and 126 to provide continuity in the seal formed by these two vertical tabs. The tongue 127 is housed in a horizontal groove 147 opening into the upper part of the vertical grooves 143 and 146.
    In addition, a first elbow joint 124 is housed both in the upstream vertical groove 142 and in the second horizontal groove 140 while a second elbow joint 125 is housed both in the second horizontal groove 140 and in the second groove downstream vertical 146. The bent joints 124 and 125 may be formed from folded metal sheets. Other materials such as those mentioned above are also conceivable. Optionally, a third sealing element or bent joint (not shown in FIG. 3) can be housed both in the first horizontal groove 141 and in the first vertical groove 143.
    With two horizontal sealing tongues superimposed in the radial direction Dr, a double seal is made at the base of the ring which reinforces the inter-sector sealing in the ring while ensuring a redirection of the circulating air the outer side of the ring upstream, that is to say in the movable wheel formed by the rotating blades inside the ring. Moreover, the use of elbow joints 124 and 125 makes it possible to block the leaks that may occur at the contact portions between the sealing tongues and thus to put the leakage sections downstream in series. In the example described here, the bent joint 124 prevents leakage at the contact portion between the second horizontal tongue 120 and the upstream vertical tongue 122 while the bent joint 125 prevents leakage at the contact portion between the second horizontal tongue 120 and the downstream vertical tongue 126. Finally, adding a second vertical downstream sealing tongue, the sealing efficiency is further improved, a first pressure loss being achieved by the second downstream vertical tongue 126 before the first downstream vertical sealing tab 123.
    FIG. 4 illustrates a high pressure turbine ring assembly according to another embodiment of the invention which differs from that of FIG. 3 in that the second elbow joint is placed at a different position. In the ring assembly of FIG. 4, the ring support metal structure is identical to the ring support metal structure 3 described above in connection with FIGS. 1, 2A and 2B and will not be described in FIG. again for the sake of simplification.
    More specifically, as shown in FIG. 4, each ring sector 200 comprises: a first horizontal sealing tab 221 housed in a first horizontal groove 241 which extends over almost the entire length of the annular base 212; a second horizontal sealing tab 220 housed in a second horizontal groove 240 which extends over a portion of the annular base 212, - an upstream vertical sealing tab 222 housed in an upstream vertical groove 242 which extends along the upstream tab 214, a first downstream vertical sealing tab 223 housed in a first downstream vertical groove 243 which extends along the downstream tab 216, and a second downstream vertical sealing tab 226 housed in a second downstream vertical groove 246 extending along the downstream leg 216 upstream of the first tongue 223.
    The second horizontal groove 240 opens on one side in the lower part of the upstream vertical groove 242 and on the other side in the lower part of the second downstream vertical groove 246. Thus, the second horizontal sealing tongue 220 is in contact at one end 220a with the upstream vertical sealing tongue 222 and in contact at the other end 220b with the second downstream vertical tongue 226. In addition, the first downstream vertical groove 243 opens into the first horizontal groove 241 so that the lower end 223b of the downstream vertical sealing tongue 223 is opposite the first horizontal sealing tongue 221. Similarly, the second downstream vertical groove 246 opens into the first horizontal groove 241 so that the lower end 226b of the downstream vertical sealing tab 226 is opposite the first horizontal sealing tab 221.
    A tab 227 is further added between the upper ends of the vertical tongues 223 and 226 to provide continuity in the seal formed by these two vertical tabs. The tongue 227 is housed in a horizontal groove 247 opening into the upper part of the vertical grooves 243 and 246.
    In addition, a first elbow joint 224 is housed both in the upstream vertical groove 242 and in the second horizontal groove 240 while a second elbow joint 225 is housed both in the first horizontal groove 241 and in the first groove Downstream vertical 243. The bent joints 224 and 225 may be formed from folded metal sheets. Other materials such as those mentioned above are also conceivable. Optionally, a third or angled gasket (not shown in FIG. 4) can be accommodated both in the second horizontal groove 240 and in the second vertical groove 246.
    With two horizontal sealing tongues superimposed in the radial direction Dr, a double seal is made at the base of the ring which reinforces the inter-sector sealing in the ring while ensuring a redirection of the circulating air the outer side of the ring upstream, that is to say in the movable wheel formed by the rotating blades inside the ring. Moreover, the use of the bent joints 224 and 225 makes it possible to plug the leaks that may occur at the contact portions between the sealing tongues and thus to put the leakage sections downstream in series. In the example described here, the bent gasket 224 prevents leakage at the contact portion between the second horizontal tongue 220 and the upstream vertical tongue 222 while the bent gasket 225 prevents leakage at the contact portion between the first horizontal tab 221 and the first downstream vertical tab 243. Finally, adding a second vertical downstream sealing tab, further improves the effectiveness of the seal.
    FIG. 5 illustrates a high pressure turbine ring assembly according to another embodiment of the invention which differs from that of FIGS. 3 and 4 in that a third bent joint is further placed downstream in the sectors of FIG. 'ring. In the ring assembly of FIG. 5, the metal ring support structure is identical to the ring support metal structure 3 previously described in connection with FIGS. 1, 2A and 2B and will not be described in FIG. again for the sake of simplification.
    More specifically, as shown in FIG. 5, each ring sector 300 comprises: a first horizontal sealing tongue 321 housed in a first horizontal groove 341 which extends over almost the entire length of the annular base 312; a second horizontal sealing tongue 320 housed in a second horizontal groove 340 which extends over a portion of the length of the annular base 312; - an upstream vertical sealing tongue 322 housed in an upstream vertical groove 342 which extends along the upstream leg 314, a first downstream vertical sealing tongue 323 housed in a first downstream vertical groove 343 which extends along the downstream leg 316, and a second downstream vertical sealing tongue 326. housed in a second downstream vertical groove 346 which extends along the downstream leg 316 upstream of the first tongue 323.
    The second horizontal groove 340 opens on one side in the lower part of the upstream vertical groove 342 and on the other side in the lower part of the second downstream vertical groove 346. Thus, the second horizontal sealing tongue 320 is in position. contact at one end 320a with the upstream vertical sealing tongue 322 and in contact at the other end 320b with the second downstream vertical tongue 326. In addition, the first downstream vertical groove 343 opens into the first horizontal groove 341 so that the lower end 323b of the downstream vertical sealing tongue 323 is opposite the first horizontal sealing tongue 321.
    A tongue 327 is further added between the upper ends of the vertical tongues 323 and 326 to ensure continuity in the seal formed by these two vertical tongues. The tongue 327 is housed in a horizontal groove 347 opening into the upper part of the vertical grooves 343 and 346.
    A first bent gasket 324 is housed both in the upstream vertical groove 342 and in the second horizontal groove 340. A second bent gasket 325 is housed in both the first horizontal groove 240 and the second downstream vertical groove 346. A Third angled joint 327 is housed in both the first horizontal groove 341 and the first downstream vertical groove 343. The bent joints 324, 325 and 327 may be formed from folded metal sheets. Other materials such as those mentioned above are also conceivable.
    With two horizontal sealing tongues superimposed in the radial direction Dr, a double seal is made at the base of the ring which reinforces the inter-sector sealing in the ring while ensuring a redirection of the circulating air the outer side of the ring upstream, that is to say in the movable wheel formed by the rotating blades inside the ring. Moreover, the use of the bent joints 324, 325 and 327 makes it possible to plug the leaks that may occur at the contact portions between the sealing tongues and thus to put the leakage sections downstream in series. In the example described here, the bent joint 324 prevents leakage at the contact portion between the first horizontal tongue 320 and the upstream vertical tongue 322. The bent joint 325 prevents leakage at the contact portion between the second horizontal tongue 320 and the second vertical tongue downstream 346. Finally, the elbow 327 prevents leakage at the contact portion between the first horizontal tongue 321 and the first downstream vertical tongue 343. Finally, adding a second tongue of Vertical sealing downstream, it further improves the effectiveness of the seal.
    FIG. 6 illustrates a high pressure turbine ring assembly according to another embodiment of the invention which differs from that of FIGS. 1, 2A and 2B in that the upstream and downstream vertical tongues extend in an oblique direction. in the upstream and downstream legs of each ring sector. In the ring assembly of FIG. 6, the metal ring support structure is identical to the ring support metal structure 3 described above in connection with FIGS. 1, 2A and 2B and will not be described in FIG. again for the sake of simplification.
    More specifically, as shown in FIG. 6, each ring sector 400 comprises: a first horizontal sealing tab 421 housed in a first horizontal groove 441 which extends over almost the entire length of the annular base 412; a second horizontal sealing tongue 420 housed in a second horizontal groove 440 which also extends over a portion of the length of the annular base 412; - an upstream vertical sealing tongue 422 housed in an upstream vertical groove 442 which extends along the upstream leg 414, and - a downstream vertical sealing tab 423 housed in a downstream vertical groove 443 which extends along the downstream leg 416.
    The second horizontal groove 440 opens on one side in the lower part of the upstream vertical groove 442 and on the other side in the lower part of the downstream vertical groove 443. Thus, the second horizontal sealing tongue 420 is in contact at one end 420a with the upstream vertical sealing tongue 422 and in contact at the other end 420b with the downstream vertical tongue 423. In addition, the downstream vertical groove 443 opens into the first horizontal groove 441 so that the end lower 423b of the downstream vertical sealing tab 423 is in contact with the first horizontal sealing tab 421.
    A first sealing element or elbow joint 424 is housed both in the upstream vertical groove 442 and in the second horizontal groove 440. A second sealing element or elbow joint 425 is housed in both the first horizontal groove 441. and in the downstream vertical groove 443. The bent joints 424 and 425 may be formed from folded metal sheets. Other materials such as those mentioned above are also conceivable. Optionally, a third or angled gasket member (not shown in FIG. 6) can be housed in both the second horizontal groove 440 and the downstream vertical groove 443.
    The upstream vertical groove 442 present in the upstream leg 414 of each ring sector 400 extends in a direction oblique with respect to the axis of the upstream leg 414. The upstream vertical groove opens on the outer face 414a of the leg upstream 414 at the lip 34 of the upstream annular flange 32 of the ring support metal structure 3. The downstream vertical groove 443 in the downstream leg 416 of each ring sector 400 extends in an oblique direction relative to the axis of the downstream leg 416. The downstream vertical groove 443 opens on the outer face 416a of the downstream leg 416 at the lip 38 of the downstream annular flange 36 of the metal ring support structure 3 In this configuration, the vertical upstream and downstream grooves open at the level of the support with the upstream and downstream annular flanges of the metal ring support structure. This decreases the distance between the upper end of the upstream and downstream vertical tongues and the bearing portions of the upstream and downstream annular flanges of the metal ring support structure.
    With two horizontal sealing tongues superimposed in the radial direction Dr, a double seal is made at the base of the ring which reinforces the inter-sector sealing in the ring while ensuring a redirection of the circulating air the outer side of the ring upstream, that is to say in the movable wheel formed by the rotating blades inside the ring. Moreover, the use of the bent joints 424 and 425 makes it possible to plug the leaks that may occur at the contact portions between the sealing tongues and thus to put the leakage sections downstream in series. In the example described here, the bent joint 424 prevents leakage at the contact portion between the second horizontal tongue 420 and the upstream vertical tongue 422. The bent joint 425 prevents leakage at the contact portion between the first horizontal tongue 421 and the downstream vertical tongue 443. Finally, with upstream and downstream vertical grooves extending obliquely in the tabs of each ring sector so as to open at the level of the bearing portions with the annular flanges of the ring support structure, inter-sector leakage is reduced at these support portions.
    The ring sectors described above are made of ceramic matrix composite material. However, the present invention also applies to a turbine ring assembly comprising a plurality of ring sectors of metallic material, the ring sectors having similar geometries to those previously described.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    A turbine ring assembly comprising a plurality of ring sectors (10) forming a turbine ring (1) and a ring support structure (3) comprising an upstream annular flange (32) and an annular flange downstream (36), each ring sector (10) having a first 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 an upstream lug (14) and a downstream lug (16), the upstream and downstream lugs (14, 16) of each ring sector (10) being held between the two upstream and downstream annular flanges (32, 36) of the ring support structure (3), each ring sector (10) comprising a first horizontal sealing tongue (21) extending along the annular base, the first horizontal sealing tongue (21). ) being housed in a first horizontal groove (41) present in the annular base (12), a tongue of upstream vertical ncheity (22) extending along the upstream leg (14), the upstream vertical sealing tongue (22) being housed in a vertical groove (42) present in the upstream lug (14) and a first tongue vertical downstream sealing strip (23) extending along the downstream leg (16), the first downstream vertical sealing tongue (23) being housed in a first vertical groove (43) present in the downstream leg (16) characterized in that each ring sector (10) further comprises a second horizontal sealing tongue (20) extending over a portion of the annular base above the first horizontal sealing tongue (21) in the radial direction of the ring, the second horizontal sealing tongue (20) being housed in a second horizontal groove (40) in the annular base (12), and in that a first elbow sealing element (24) is housed both in the groove vertically (42) in the upstream lug (14) and in the second horizontal groove (40) while a second bent sealing element (25) is accommodated both in the first horizontal groove (41) and in the first vertical groove (43) present in the downstream lug (16), the first vertical groove (43) opening into the first horizontal groove (41), or while a second bent sealing element is housed both in the second horizontal groove (40) and in the first vertical groove (43) in the downstream leg (16), the first vertical groove (43) opening into the second horizontal groove (40).
    [2" id="c-fr-0002]
    Turbine ring assembly according to claim 1, characterized in that each ring sector (100) further comprises a second downstream vertical sealing tab (126) extending along the downstream leg (116). ), the second downstream vertical sealing tab (126) being housed in a second vertical groove (146) in the downstream tab (16), the second downstream vertical sealing tab (126) being in contact with one another its ends with the second horizontal sealing tongue (120), the second vertical groove (146) having in the downstream leg (116) opening into the second horizontal groove (140), the second elbow sealing element (125) being housed in both the second horizontal groove (140) and the second vertical groove (146) in the downstream leg (116).
    [3" id="c-fr-0003]
    Turbine ring assembly according to claim 2, characterized in that a third bent sealing element (327) is accommodated both in the first horizontal groove (341) and in the first vertical groove (343). present in the downstream leg (316).
    [4" id="c-fr-0004]
    The turbine ring assembly according to claim 1, characterized in that each ring sector (210) further comprises a second downstream vertical sealing tab (226) extending along the downstream leg (216). ), the second downstream vertical sealing tab (226) being housed in a second vertical groove (246) present in the downstream tab (216), the second downstream vertical sealing tab (226) being in contact with the second tab horizontal sealing ring (220), the second vertical groove (246) in the downstream lug (216) opening into the first and second horizontal grooves (241, 240), the second bent sealing element (225) being housed at both in the first horizontal groove (241) and in the first vertical groove (243) in the downstream leg (216).
    [5" id="c-fr-0005]
    A turbine ring assembly according to claim 1, characterized in that the upstream annular flange (32) has a lip (34) in contact with the upstream leg of each ring sector (10) while the annular flange downstream (36) has a lip (38) in contact with the downstream leg of each ring sector (10), and in that the vertical groove (442) in the upstream leg (414) of each ring sector (410) extends in a direction oblique to the axis of the upstream leg, said vertical groove (442) opening on the outer face of the upstream leg (414) at the lip (34) of the flange upstream annulus (32) while the vertical groove (443) in the downstream leg (416) of each ring sector (410) extends in a direction oblique to the axis of the downstream leg, said groove vertical (443) opening on the outer face of the downstream tab (416) at the lip (38) of the downstream annular flange (36).
    [6" id="c-fr-0006]
    Turbine ring assembly according to claim 5, characterized in that the second bent sealing element (425) is accommodated both in the first horizontal groove (441) and in the first vertical groove (443) present in the downstream leg (416).
    [7" id="c-fr-0007]
    A turbine ring assembly according to any one of claims 1 to 6, characterized in that the two annular flanges (32, 36) of the ring support structure (3) exert a stress on the tabs (14, 16) of the ring sectors (10) and in that at least one (36) of the flanges of the ring support structure (3) is elastically deformable in the axial direction of the ring .
    [8" id="c-fr-0008]
    The turbine ring assembly according to any one of claims 1 to 7, characterized in that it further comprises a plurality of pins (50; 51) engaged in at least one of the annular flanges (32). 36) of the ring support structure (3) and the tabs (14; 16) of the ring sectors (10) facing said at least one annular flange (32; 36).
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    同族专利:
    公开号 | 公开日
    FR3041993B1|2019-06-21|
    EP3359779A1|2018-08-15|
    CN108138576A|2018-06-08|
    CN108138576B|2021-01-29|
    EP3359779B1|2020-11-25|
    US10787924B2|2020-09-29|
    US20190040758A1|2019-02-07|
    WO2017060604A1|2017-04-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPH11343809A|1998-06-02|1999-12-14|Ishikawajima Harima Heavy Ind Co Ltd|Sealing structure of turbine shroud part for gas turbine|
    JP2009203948A|2008-02-29|2009-09-10|Hitachi Ltd|Seal device, seal method and gas turbine having seal device|
    GB2481481A|2010-06-23|2011-12-28|Gen Electric|Turbine shroud sealing arrangement|FR3087825A1|2018-10-29|2020-05-01|Safran Aircraft Engines|TURBINE RING SECTOR WITH COOLED SEALING TONGS|
    US10934872B2|2017-10-23|2021-03-02|Safran Aircraft Engines|Turbomachine case comprising a central part projecting from two lateral portions in a junction region|
    FR3107549A1|2020-02-24|2021-08-27|Safran Ceramics|Sealing of a turbine|US5088888A|1990-12-03|1992-02-18|General Electric Company|Shroud seal|
    US6821085B2|2002-09-30|2004-11-23|General Electric Company|Turbine engine axially sealing assembly including an axially floating shroud, and assembly method|
    US20040219011A1|2003-05-02|2004-11-04|General Electric Company|High pressure turbine elastic clearance control system and method|
    FR2869943B1|2004-05-04|2006-07-28|Snecma Moteurs Sa|FIXED RING ASSEMBLY OF A GAS TURBINE|
    FR2869944B1|2004-05-04|2006-08-11|Snecma Moteurs Sa|COOLING DEVICE FOR FIXED RING OF GAS TURBINE|
    US7494317B2|2005-06-23|2009-02-24|Siemens Energy, Inc.|Ring seal attachment system|
    FR2923525B1|2007-11-13|2009-12-18|Snecma|SEALING A ROTOR RING IN A TURBINE FLOOR|
    ES2398727T3|2009-03-09|2013-03-21|Snecma|Turbine ring set|
    FR2954400B1|2009-12-18|2012-03-09|Snecma|TURBINE STAGE IN A TURBOMACHINE|
    US8998573B2|2010-10-29|2015-04-07|General Electric Company|Resilient mounting apparatus for low-ductility turbine shroud|
    FR2968030B1|2010-11-30|2013-01-11|Snecma|LOW-AIR TURBINE ENGINE PRESSURE TURBINE, COMPRISING A SECTORIZED DISTRIBUTOR|
    US8834105B2|2010-12-30|2014-09-16|General Electric Company|Structural low-ductility turbine shroud apparatus|
    US9810086B2|2011-11-06|2017-11-07|General Electric Company|Asymmetric radial spline seal for a gas turbine engine|
    FR2989724B1|2012-04-20|2015-12-25|Snecma|TURBINE STAGE FOR A TURBOMACHINE|
    US9874105B2|2015-01-26|2018-01-23|United Technologies Corporation|Active clearance control systems|
    US9874104B2|2015-02-27|2018-01-23|General Electric Company|Method and system for a ceramic matrix composite shroud hanger assembly|FR3080142B1|2018-04-16|2020-05-01|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH INTER-SECTOR SEAL|
    FR3086327B1|2018-09-25|2020-12-04|Safran Aircraft Engines|SET FOR A TURBOMACHINE TURBINE|
    US11187094B2|2019-08-26|2021-11-30|General Electric Company|Spline for a turbine engine|
    US11215075B2|2019-11-19|2022-01-04|Rolls-Royce North American Technologies Inc.|Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring|
    US11066947B2|2019-12-18|2021-07-20|Rolls-Royce Corporation|Turbine shroud assembly with sealed pin mounting arrangement|
    FR3113696A1|2020-09-03|2022-03-04|Safran Aircraft Engines|Turbomachine part with connecting edge made of composite material with a ceramic matrix and short fibers and method of manufacturing the same|
    US11255210B1|2020-10-28|2022-02-22|Rolls-Royce Corporation|Ceramic matrix composite turbine shroud assembly with joined cover plate|
    法律状态:
    2016-10-06| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-07| PLSC| Publication of the preliminary search report|Effective date: 20170407 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559457|2015-10-05|
    FR1559457A|FR3041993B1|2015-10-05|2015-10-05|TURBINE RING ASSEMBLY WITH AXIAL RETENTION|FR1559457A| FR3041993B1|2015-10-05|2015-10-05|TURBINE RING ASSEMBLY WITH AXIAL RETENTION|
    US15/764,919| US10787924B2|2015-10-05|2016-10-04|Turbine ring assembly with axial retention|
    CN201680057661.5A| CN108138576B|2015-10-05|2016-10-04|Turbine ring assembly with axial retention|
    PCT/FR2016/052538| WO2017060604A1|2015-10-05|2016-10-04|Turbine ring assembly with axial retention|
    EP16787501.2A| EP3359779B1|2015-10-05|2016-10-04|Turbine ring assembly with axial retention|
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