• 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 includes a plurality of ceramic matrix composite ring forming sectors (10) forming a turbine ring (1) and a ring supporting structure (3) having two annular flanges (32, 36), each ring sector (10) having two tabs (14, 16) held respectively between the two annular flanges (32, 36) of the ring support structure (3). The two annular flanges (32, 36) of the ring support structure (3) stress the tabs (14, 16) of the ring sectors (10). One (36) of the flanges of the ring support structure (3) is elastically deformable in the axial direction (DA) of the turbine ring (1).
    公开号:FR3036432A1
    申请号:FR1554604
    申请日:2015-05-22
    公开日:2016-11-25
    发明作者:Lucien Henri Jacques Quennehen；Sebastien Serge Francis Congratel
    申请人:SNECMA SAS；Herakles SA；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to a turbine ring assembly for a turbomachine, which assembly comprises a plurality of one-piece ring segments of ceramic matrix composite material and a support structure of ring. 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 aviation gas turbine engines, improved efficiency and reduced 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 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 nevertheless make it possible to improve the performance of the aeronautical 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 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. 3036432 2 The use of ring segments in CMC significantly reduces the ventilation needed 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. Indeed, in order to ensure a good seal, it must be possible to ensure good contact between the legs of the CMC ring sectors and the metal flanges of the ring support structure. However, the differential expansions between the metal of the ring support structure and the CMC of the ring sectors complicates the maintenance of the seal between these elements. Thus, during differential expansions and depending on the mounting geometry of the ring sectors on the ring support structure, the flanges of the ring support structure may no longer be in contact with the legs of the sectors or, at contrary, exert too much stress on the legs of the sectors, which can damage them. Furthermore, as described in US 2012/0027572, the maintenance of the ring sectors on the ring support structure requires the use of a U-section clamp, which complicates the assembly of the sectors and increases the cost of the whole.
    [0002] 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 ring and a support structure. ring having two annular flanges, each ring sector having a first annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which radially extend two legs, the tabs of each ring sector being held between the two annular flanges of the ring support structure, characterized in that 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 the flanges of the ring support structure is elastically deformable in the axial direction of the ring.
    [0003] Thanks to the presence of at least one elastically deformable flange, the contact between the flanges of the ring support structure and the tabs of the ring sectors can be maintained independently of temperature variations. Indeed, the ring sectors can be mounted between the flanges with a "cold" prestressing, so that the contact between the ring sectors and the flanges is assured regardless of the temperature conditions. The flexibility of at least one of the flanges of the ring support structure allows by its deformation to accommodate the differential thermal expansion between the ring sectors and the flanges so as to avoid exerting too much stress on the ring support structure. the ring areas. According to a first aspect of the turbine ring assembly according to the invention, at least one of the annular flanges of the ring support structure has a lip on its face facing the lugs of the ring sectors. The presence of a lip on a flange facilitates the definition of the contact portion between the flange of the ring support structure and the tabs of the ring sectors facing it. According to a second aspect of the turbine ring assembly 20 according to the invention, it further comprises a plurality of pins engaged both in 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. According to a third 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 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 a fourth aspect of the turbine ring assembly according to the invention, each elastically deformable flange of the ring support structure has a thickness less than that of the other flange of said ring support structure. .
    [0004] The present invention also relates to a method of making a turbine ring assembly comprising: - making a plurality of ceramic matrix composite material ring sectors, each ring sector having a first annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which two legs extend radially, - the manufacture of a ring support structure having two annular flanges Mounting of each ring sector between the two annular flanges of the ring support structure, characterized in that the spacing between the two flanges of the ring structure is less than the distance between the faces. external of the tabs of each ring sector, at least one of the flanges of the ring support structure being elastically deformable in the axial direction of the ring and in that In each ring sector, traction in the axial direction of the ring is exerted on said elastically deformable flange so as to increase the spacing between the two flanges and engage the tabs of the ring sector between the two flanges. of the ring support structure. Thanks to the traction exerted on the elastically deformable tab, it is possible to insert the tabs of the ring sectors between the flanges of the ring support structure without having to force on said tabs which are then held axially with a stress between the flanges after loosening of the tension exerted on the elastically deformable flange. According to a first aspect of the method for producing a turbine ring assembly according to the invention, at least one of the annular flanges of the ring support structure comprises a lip on its face opposite the legs of the sectors of the ring. 'ring. According to a second aspect of the method of making a turbine ring assembly according to the invention, it further comprises engaging a plurality of pins in both at least one of the annular flanges of the invention. ring support structure and the legs of the ring sectors facing said at least annular flange.
    [0005] According to a third aspect of the method of producing a turbine ring assembly according to the invention, the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that opposite. tabs of the ring sectors, traction in the axial direction of the ring exerted on said elastically deformable flange being performed by a tool engaged in one or more hooks. According to a fourth aspect of the method of producing a turbine ring assembly according to the invention, the elastically deformable flange of the ring support structure has a thickness less than that of the other flange of said ring structure. ring holder 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 schematic perspective view showing an alternative embodiment of the hooks present on an elastically deformable ring support structure flange; Figure 6 is a schematic perspective view showing another alternative embodiment of the hooks present on an elastically deformable ring support structure flange. DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 of ceramic matrix composite material (CMC) and a metal ring support structure 3. The ring of Turbine 1 surrounds a set of rotary blades 5. 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 3036432 6 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 shaped section. Inverted with an annular base 12 whose inner face 5 coated with a layer 13 of abradable material and / or a thermal barrier defines the flow stream of 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 DR. The terms "upstream" and "downstream" are used herein with reference to the flow direction of the gas stream 10 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 lip 34 on its face opposite the upstream lugs 14 of the ring sectors 10, the lip 34 being in bearing on the external face 14a of the upstream tabs 14. On the downstream side, the ring support structure comprises an annular downstream radial flange 36 having a lip 38 on its face opposite the downstream tabs 16 of the ring sectors 10, the lip 38 being supported on the outer face 16a of the downstream tabs 16. As explained below in detail, the tabs 14 and 16 of each ring sector 10 are preloaded between the annular flanges 32 and 54 the flanges exert, at least at "cold", that is to say at an ambient temperature of about 20 ° C, but also at all operating temperatures of the turbine, a stress on the legs 14 and 16 and therefore a tightening of the 25 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.
    [0006] 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 leg 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. A this effect, the pins 41 each pass respectively through an orifice 37 formed in the annular downstream radial flange 36 and an orifice 17 provided for each downstream lug 16, the orifices 37 and 17 being aligned during the assembly of the ring sectors 10 on the structure of annea support u3. 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 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. 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.
    [0007] The clearance-free assembly of the tabs 14, 16 of the CMC ring sector with metal parts of the ring support structure is made possible despite the difference in coefficient of thermal expansion because: is made at a distance from the hot face of the annular base 12 exposed to the gaseous flow, - the lugs 14, 16 advantageously have in radial section a relatively large length relative to their average thickness so that an effective thermal decoupling is obtained between the annular base 12 and the ends of the tabs 14, 16, and 30 - one of the flanges of the ring structure is elastically deformable, which makes it possible to compensate for the differential expansions between the tabs of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the stress exerted "cold" by the flanges on the legs of the ring sectors.
    [0008] In addition, conventionally, ventilation orifices 32a formed in the flange 32 make it possible to supply cooling air to the outside of the turbine ring 10. A method of producing a turbine is described below. turbine ring assembly corresponding to that shown in Figure 1. Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape similar to that ring sector and densification of the ring sector by a ceramic matrix.
    [0009] For the production of 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 provision of debonding zones to separate the preform portions corresponding to the tabs 14 and 16 of the sectors 10. The weaving may be interlock type, as illustrated. Other three-dimensional weave or multilayer weaves may be used such as multi-web or multi-satin weaves. Reference can be made to WO 2006/136755. After weaving, the blank may 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) or a MI process. ("Melt Infiltrated", liquid silicon introduced into the fibrous preform by capillarity, the preform being previously consolidated by a CVI phase) which are well known per se. 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 inconel, the C263 superalloy or Waspaloy®. 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 spacing E between the radial flange 3036432 9 annular upstream 32 and the annular downstream radial flange 36 at "rest", that is to say when no ring sector is mounted between the flanges, is less than the distance D present between the outer faces 14a and 16a of the upstream and downstream legs 14 and 16 of the ring sectors. In the example 5 described here, the gap E is measured between the lips 34 and 38 present respectively at the end of the annular flanges 32 and 36. In the embodiments of the turbine ring assembly of the In which the annular flanges do not comprise lips, the spacing is measured between the inner faces of the flanges which will be in contact with the outer surface of the legs of the ring sectors. By defining a gap E between the flanges of the lower ring support structure at the distance D between the outer faces of the tabs of each ring sector, it is possible to mount the ring segments prestressed between the flanges of the ring. 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. When mounting a ring sector 10, the annular downstream radial flange 36 is pulled in the direction DA as shown in FIGS. 3 and 4 in order to increase the spacing between the flanges 32 and 36 and to allow the insertion of the tabs 14 and 16 between the flanges 32 and 36 without risk of damage. Once the tabs 14 and 16 of a ring sector 10 are inserted between the flanges 14 and 16 and positioned to line the orifices 33 and 15, on the one hand, and 17 and 37 on the other hand, the flange 36 is released, the lips 34 and 38 respectively of the flanges 32 and 36 then exerting a holding stress on the tabs 14 and 16 of the ring sector. In order to facilitate pulling apart the annular radial downstream flange 36, the latter comprises a plurality of hooks 39 distributed on its face 36a, which face is opposite to the face 36b of the flange 36 facing the downstream tabs. ring sectors 10 (FIG. 4). 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.
    [0010] 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 15 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 openings for the passage of a pion of blocking.
    [0011] The shape and orientation of the hooks may vary. Figure 5 shows an annular downstream radial flange 136 having a plurality of hooks 139 which open in the circumferential direction of the flange and in which a lug 151 of a traction tool is introduced. Figure 6 shows an annular downstream radial flange 236 having a plurality of hooks 239 which open in the radial and downward direction of the flange and in which a lug 251 of a pulling tool is introduced. 30
    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 two annular flanges (32, 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 extend radially. two tabs (14, 16), the tabs (14, 16) of each ring sector (10) being held between the two annular flanges (32, 36) of the ring support structure (3), characterized in that the two annular flanges (32, 36) of the ring support structure (3) stress 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 (DA) of the turbine ring (1).
    [0002]
    A turbine ring assembly according to claim 1, characterized in that at least one of the annular flanges (32; 36) of the ring support structure has a lip (34; 38) on its face. looking at the tabs (14; 16) of the ring sectors (10).
    [0003]
    A turbine ring assembly according to claim 1 or 2, characterized in that it further comprises a plurality of pins (40; 41) engaged in at least one of the annular flanges (32; 36). the ring support structure (3) and the tabs (14; 16) of the ring sectors (10) facing said at least one annular flange (32; 36). 30
    [0004]
    Turbine ring assembly according to one of Claims 1 to 3, characterized in that the elastically deformable flange (36) of the ring support structure (3) has a plurality of distributed hooks (39). on its face (36a) opposite that (36b) facing the lugs (16) of the ring sectors (10). 35 3036432 12
    [0005]
    Turbine ring assembly according to any one of claims 1 to 4, characterized in that each elastically deformable flange (36) of the ring support structure (3) has a thickness less than that of the another flange (32) of said ring support structure (3).
    [0006]
    A method of making a turbine ring assembly comprising: producing a plurality of ring sectors (10) of ceramic matrix composite material, each ring sector (10) having a first portion ( 12) forming an annular base with an internal face defining the inner face of a turbine ring (1) and an outer face from which two lugs (14, 16) radially extend, - the manufacture of a structure of ring support (3) comprising two annular flanges (32, 36), - mounting of each ring sector (10) between the two annular flanges (32, 36) of the ring support structure (3). ), characterized in that the spacing (E) between the two flanges (32, 36) of the ring structure (3) is smaller than the distance (D) between the outer faces (14a, 16a) of the legs (14, 16) of each ring sector (10), at least one (36) of the flanges of the ring support structure (3) being elastically deformable in the axial direction (DA) of the turbine ring (1) and in that, during the assembly of each ring sector (10), a traction in the axial direction (DA) of the turbine ring (1) ) is exerted on said elastically deformable flange (36) so as to increase the spacing between the two flanges (32, 36) and engage the lugs (14, 16) of the ring sector between the two flanges of the support structure ring (3). 30
    [0007]
    7. Method according to claim 6, characterized in that at least one of the annular flanges (32; 36) of the ring support structure (3) comprises a lip (34; 38) on its face opposite the legs. (14; 16) ring sectors (10). 35
    [0008]
    8. A method according to claim 6 or 7, characterized in that it further comprises the engagement of a plurality of pins (40; 41) to the 3036432 13 times in at least one of the annular flanges (32; 36). the ring support structure (3) and the tabs (14; 16) of the ring sectors (10) facing said at least one annular flange (32; 36). 5
    [0009]
    9. Method according to any one of claims 6 to 8, characterized in that the elastically deformable flange (36) of the ring support structure (3) comprises a plurality of hooks (39) distributed on its opposite face ( 36a) to that (36b) opposite the lugs (16) of the ring sectors (10), the traction in the axial direction (DA) of the ring (1) exerted on said elastically deformable flange being carried out by a tool (50) engaged in one or more hooks (39).
    [0010]
    Method according to one of claims 6 to 9, characterized in that the elastically deformable flange (36) of the ring support structure (3) has a thickness which is smaller than that of the other flange (32). of said ring support structure (3).
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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 |
    2017-04-13| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-25| CD| Change of name or company name|Owner name: HERAKLES, FR Effective date: 20170725 Owner name: SNECMA, FR Effective date: 20170725 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20170719 Owner name: SAFRAN AIRCRAFT ENGINES, 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
    FR1554604A|FR3036432B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY WITH AXIAL RETENTION|
    FR1554604|2015-05-22|FR1554604A| FR3036432B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY WITH AXIAL RETENTION|
    PCT/FR2016/051123| WO2016189215A1|2015-05-22|2016-05-12|Turbine ring assembly with axial retention|
    US15/576,014| US10690007B2|2015-05-22|2016-05-12|Turbine ring assembly with axial retention|
    CN201680032748.7A| CN107709708B|2015-05-22|2016-05-12|Axial-flow turbine ring assembly|
    EP16726365.6A| EP3298244B1|2015-05-22|2016-05-12|Turbine ring assembly with axial retention|
    JP2017560690A| JP6689290B2|2015-05-22|2016-05-12|Turbine ring assembly with axial retainer|
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