• 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:
    The invention relates to a turbine ring assembly comprising a plurality of one-piece ring sectors (1) of ceramic matrix composite material for mounting on a ring support structure (3), the structure ring carrier comprising two tabs (32,34) extending radially to a flow stream of the gas stream, each ring sector having a first annular base portion (12) with a radially inner face defining the face inner ring of the turbine ring and an outer face from which extend two leg portions (14, 16), the ring sectors having a substantially π-shaped section. The tabs of each ring sector are able to axially grip the tabs of the ring support structure, and to be held thereon by means of pins (40) passing right through holes (14a). 14b, 14c, 16b) formed in the legs of each ring sector and lodged in the legs of the ring support structure, the holes of the legs of each ring sector having a larger size than the diameter of the ring pins to form a clearance between the ring sector and the ring support structure.
    公开号:FR3033825A1
    申请号:FR1552145
    申请日:2015-03-16
    公开日:2016-09-23
    发明作者:Lucien Henri Jacques Quennehen；Gael Frederic Claude Cyrille Evain；David Mathieu Paul Marsal；Thierry Guy Xavier Tesson
    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, this assembly comprising a plurality of one-piece ring segments of ceramic matrix composite material (CMC). ) and a ring support structure. 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. In aviation gas turbine engines, improving efficiency and reducing polluting emissions lead to reducing the mass of parts constituting the engine and to operate at ever higher temperatures.
    [0002] Composite matrix ceramic (CMC) materials, known for their good mechanical properties which make them suitable for constituting structural elements and for retaining these properties at high temperatures, constitute a viable alternative to traditional metal parts.
    [0003] The use of CMC parts in the hot parts of such engines has already been considered for the aforementioned reasons. In particular, WO 2010/103213 discloses a turbine ring assembly for a turbomachine, comprising a plurality of one-piece CMC ring sectors, each ring sector having a first annular base portion. with an inner face defining the internal face of the turbine ring and an outer face from which extend two leg portions whose ends are engaged in housings of the ring carrier structure, the sectors of ring having a substantially T-shaped section and the ends of the tabs are held without radial play by the ring support structure. In this document, the ring support structure is metallic and is close to the flow path of hot gases so that it undergoes a significant increase in temperature. The metal structures are therefore likely to be damaged by the high temperature of the vein gases.
    [0004] In addition, the CMC ring sectors have a very low allowable stress, high stiffness, and much less expansion than the metal ring support structure. Therefore, since the ring sectors are maintained without radial clearance in the aforementioned document, they are weakened as soon as they are subjected to very high temperatures because of the mechanical stresses imposed by the difference of expansion with the structure of ring support. OBJECT AND SUMMARY OF THE INVENTION The main object of the present invention is therefore to overcome such disadvantages by proposing a turbine ring assembly which compensates for the differential expansion between the CMC ring sectors and the ring support structure. in metal, protecting the ring support structure from hot gases from the vein and reducing the stresses imposed on ring areas at high temperature. This object is achieved by a turbine ring assembly comprising a plurality of one-piece ceramic matrix composite material ring segments for mounting on a ring support structure, the support structure of ring comprising two tabs extending radially towards a flow stream of the gas stream, each ring sector having a first annular base portion with a radially inner face defining the inner face of the turbine ring and an outer face to from which two leg portions extend, the ring sectors having a substantially TC-shaped section. According to the invention the tabs of each ring sector are able to axially grip the tabs of the ring support structure, and to be held thereon by means of pins passing right through holes formed in the legs of each ring sector and being housed in the legs of the ring support structure, the holes of the legs of each ring sector having a size greater than the diameter of the pins so as to form a game between the ring sector and the ring support structure. The presence of a clearance between the ring sector and the ring support structure provides compensation for the differential expansion existing between CMC and metal. Specifically, the metal expanding more than the CMC, the holes formed in the legs of each ring sector being larger in size than the pins, they compensate for this expansion and s' ensure that the CMC ring sectors are effectively maintained without being too tightly constrained at high temperature. In addition, the differential expansion becomes advantageous because it provides the seal between each ring sector and the ring support structure. Indeed, the metal tabs of the ring support structure will expand axially (that is to say in the direction of flow of the gas stream in the turbomachine) and exert a slight pressure on the legs of each ring sector which enclose them, thus ensuring this tightness. Also, since the ring support structure is sealed with the tabs of each CMC ring sector, it is protected from the hot gases of the vein since the CMC is heat resistant and forms a thermal barrier. This arrangement makes it possible to reduce the cooling of the ring support structure and thus to reduce the consumption of the motor due to the withdrawal of air necessary to effect this cooling.
    [0005] Preferably, at least one tab of each ring sector has at least one elongated hole extending in a circumferential direction so as to form a clearance between the ring sector and the ring support structure. The presence of these oblong holes extending in a circumferential direction advantageously makes it possible to compensate for the expansion of the ring support structure in the circumferential direction. More preferably, at least one tab of each ring sector has at least one elongated hole extending in a radial direction so as to form a clearance between the ring sector and the ring support structure. In the same way as before, the oblong holes extending in a radial direction compensate the expansion of the ring support structure in the radial direction. In addition, in the case where a radial clearance remains hot between the ring support structure 35 and the ring sectors, the pressure difference 3033825 4 between the outer face and the inner face of the ring sectors maintains them plated against the flow vein. According to a first embodiment of the invention, the tabs of each ring sector each comprise at least one oblong hole 5 extending in a radial direction and at least two oblong holes extending in a circumferential direction so as to forming a clearance between the ring sector and the ring support structure. The expansion of the ring support structure is thus compensated in both stress directions (radial and circumferential), which advantageously limits the fragility of each ring sector and allows a more efficient maintenance thereof. According to a second embodiment of the invention, a tab of each ring sector has at least two oblong holes extending in one circumferential direction, and the other leg of each ring sector has at least one hole. oblong extending in a radial direction so as to form a clearance between the ring sector and the ring support structure. Preferably, each peg has a head at an end opposite to that housed in the lug of the ring support structure.
    [0006] The presence of these heads on the pins makes it easier to mount and disassemble the ring sectors on the ring support structure. More preferably, the pins are housed in non-through holes formed in the ring support structure. Thus, the pins are held axially by means of the abutment formed by the non-opening holes in the ring support structure which ensures an effective maintenance of the ring sectors, while avoiding forming a passage for the hot gases of the ring. vein inward of the ring support structure. The inner face of each ring sector may be covered with an abradable coating. The pions are preferably made of metal. In this way, they will be able to lodge in the ring support structure without significant play and be able to expand in the same manner as the ring support structure, while maintaining the CMC ring sectors.
    [0007] The invention also relates to a turbomachine comprising a set of ring sectors such as that described previously. BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate embodiments having no limiting character. In the figures: FIG. 1 is a schematic perspective view of a turbine ring sector mounted on a ring support structure according to a first embodiment of the invention, FIG. a view along direction II of the ring sector of FIG. 1, and FIGS. 3A and 3B are views respectively from upstream and downstream of a turbine ring sector mounted on a structure ring support according to a second embodiment of the invention. DETAILED DESCRIPTION OF THE INVENTION FIG. 1 shows a CMC turbine ring sector 1 and a metal ring support structure 3 according to a first embodiment of the invention. In a manner known per se, a set of ring sectors 1 is assembled so as to form a turbine ring which surrounds a set of rotating blades (not shown).
    [0008] Each ring sector 1 has a substantially y-shaped section with an annular base 12 whose inner face is coated with a layer 13 of abradable material and which defines the flow vein of the gas stream in the turbine. Lugs 14, 16 of substantially straight meridian section extend from the outer face 30 of the annular base 12 over the entire length thereof. A plurality of piercing holes 20 are provided in the outer wall of the ring support structure 3 so as to allow fluid communication in the direction of the annular enclosure formed by the inner wall of the ring support structure 3 , the outer wall of the annular base 12, and the walls 32b, 34b of the tabs 32, 34, in order to cool the annular base 12 by means of air drawn for example upstream of the chamber of combustion of the turbomachine. In a manner known per se, each ring sector 1 is made of CMC, for example, by forming a fibrous preform having a shape close to that of the ring sector, and densifying the ring sector by a matrix. ceramic. For the production of the fiber preform, it is possible to use, for example, ceramic fiber threads, for example SiC fiber threads. The fiber preform is produced for example by three-dimensional weaving or multilayer weaving with the provision of debonding zones enabling the parts of preforms corresponding to the lugs 14 and 16 of the preform part corresponding to the base 12 to be spaced apart. manufacture of a ring sector in CMC is described more precisely in the document WO 2010/103213.
    [0009] The upstream lug 14 (upstream and downstream being defined as a function of the direction of flow of the gaseous flow in the turbine) is pierced by an oblong central 14b-shaped through hole extending in a substantially radial direction and two oblong holes 14a, 14c opening extending in a substantially circumferential direction on either side of the hole 14b, so that the hole 14c is the image of the hole 14a by axial symmetry of radial axis I (FIG. ) passing through hole 14b. The tab 16 comprises, identically to the tab 14, two oblong holes opening extending in a substantially circumferential direction (not visible in the figures) and an oblong hole 16b 25 extending in a substantially radial direction. A chamfer 18 may be machined on the upstream side of the end of the downstream tab 34 of each ring sector 1 to facilitate assembly of the ring sectors on the ring support structure 3.
    [0010] The ring support structure 3 which is integral with the turbine casing comprises two tabs 32, 34 extending inwardly of the flow stream of the gas stream. The upstream leg 32 of the ring support structure 3 has an upstream face 32a which is in contact with a projection 31 at the end of the upstream leg 14 of the ring sector 1. The downstream face 32b of the leg Upstream 32 of the ring support structure 3 has a projection 33 over the entire circumference of the ring support structure. At the projection 33, the thickness of the upstream leg is greater. Likewise, the downstream leg 34 of the ring support structure 3 has a downstream face 34a which is in contact with a projection (not visible in the figures) at the end of the downstream leg 16 of the sector of support. ring 1. The upstream face 34b of the downstream leg 34 of the ring support structure 3 has a projection 35 all around the circumference of the ring support structure. At the projection 35, the thickness 10 of the downstream leg is greater. The projections 31 make it possible to precisely control the contact zone between the ring sector 1 and the ring support structure 3, while ensuring a good seal between these two elements. Each tab 32, 34 of the ring support structure is pierced with non-through holes 36, 38, located at the projection 33, 35, and uniformly distributed on the circumference of the ring support structure so as to face the oblong holes 14a, 14b, 14c, 16b of the ring sectors once mounted. The tabs 32, 34 of the ring support structure are arranged so that the tabs 14, 16 of the ring sector 1 can axially grip them substantially without axial play. Chamfers are machined on each side of the ends of the tabs 32, 34 of the ring support structure to provide easier mounting of the ring sectors.
    [0011] Metal studs 40 passing right through each through hole 14a, 14b, 14c of a ring sector ensure the maintenance of the ring sector 1 on the tabs 32, 34 of the ring support structure 3. The pins 40 have a smaller diameter than the holes 14a, 14b, 14c of each ring sector and substantially identical to the non-through holes 36, 38 of the ring support structure in which they are housed. In this way, there is a radial and circumferential clearance between the ring sectors and the ring support structure. A second embodiment of the invention is illustrated in FIGS. 3A and 3B. When not described hereinafter, the features of the second embodiment of the invention should be considered identical to the first.
    [0012] The upstream lug 14 'of the ring sector is pierced by two oblong holes opening 14'a, 14'c which extend in a substantially circumferential direction, and the downstream lug 16' of the sector. The ring is pierced by an oblong hole opening 16 'b centered which extends in a substantially radial direction. The tabs 32 ', 34' of the ring support structure 3 'are pierced with non-through holes 36' (FIG. 3A) at the projection present on each of them, so that the tabs of the ring sector can be held by means of metal pins 40 'which pass through the holes 14'a, 14'c, 16'b and are housed in the non-through holes of the ring support structure 3'. As in the first embodiment of the invention, the pins 40 'have a diameter smaller than the size of the opening holes made in the legs of the ring sectors 1' and a diameter substantially equal to that of the non-emerging holes of the ring support structure 3 ', so as to obtain a radial and circumferential clearance between each ring sector and the ring support structure. It is conceivable to invert the position of the oblong holes between the upstream tab 14 'and the downstream tab 16' (and thus non-opening holes 36 'of the tabs of the ring support structure 3'). A head may be present on the pins 40, 40 'at their end opposite to that housed in a tab of the ring support structure 3, 3' to facilitate assembly and disassembly of the ring sectors 1, 1 ' .
    [0013] The metal pins 40, 40 'may have different shapes from the cylindrical one illustrated in the figures. Alternatively, the holes 33, 35 made in the legs of the ring support structure may be opening and the head possibly present on the pins thus ensures their maintenance in one direction (upstream or downstream). In order to provide a seal between the ring sectors, sealing tabs (not shown) may be inserted between the ring sectors when mounting them to the ring support structure. 35
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A turbine ring assembly comprising a plurality of one-piece ceramic matrix composite material ring sectors (1, 1 ') for mounting on a ring carrier structure (3, 3'), the ring support structure comprising two tabs (32,34) extending radially to a flow stream of the gas stream, each ring sector having a first annular base portion (12) with a radially inner face defining the inner face of the turbine ring and an outer face from which two leg portions (14, 16, 14 ', 16') extend, the ring sectors having a substantially shaped cross section characterized in that the tabs of each ring sector are capable of axially gripping the legs of the ring support structure, and to be held thereon by means of pins (40, 40 ') passing right through holes (14a, 14b, 14c, 16b, 14'a, 14'c, 16'b) practiced in the tabs of each ring sector and being housed in the legs of the ring support structure, the holes of the legs of each ring sector having a size greater than the diameter of the pins so as to form a clearance between the ring sector and ring support structure.
    [0002]
    Turbine ring assembly according to claim 1, characterized in that at least one leg of each ring sector has at least one oblong hole (14a, 14c, 14'a, 14'c) extending in a circumferential direction so as to form a clearance between the ring sector and the ring support structure.
    [0003]
    3. Turbine ring assembly according to any one of claims 1 or 2, characterized in that at least one leg of each ring sector comprises at least one oblong hole (14b, 16b, 16'b) s extending in a radial direction so as to form a clearance between the ring sector and the ring support structure
    [0004]
    Turbine ring assembly according to one of Claims 1 to 3, characterized in that the tabs of each ring sector each comprise at least one oblong hole (14b, 16b). extending in a radial direction and at least two oblong holes (14a, 14c) extending in a circumferential direction so as to form a clearance between the ring sector and the ring support structure.
    [0005]
    A turbine ring assembly according to any one of claims 1 to 3, characterized in that a tab of each ring sector has at least two oblong holes extending in a circumferential direction (14a). , 14'c), and in that the other leg of each ring sector has at least one oblong hole (16'b) extending in a radial direction so as to form a clearance between the ring sector and the ring support structure. 15
    [0006]
    Turbine ring assembly according to any one of claims 1 to 5, characterized in that each pin (40, 40 ') has a head at one end opposite to that housed in the leg of the ring support. 20
    [0007]
    A turbine ring assembly according to any one of claims 1 to 6, characterized in that the pins are housed in non-through holes (36, 38, 36 ') formed in the ring support structure. 25
    [0008]
    8. turbine ring assembly according to any one of claims 1 to 7, characterized in that the inner face of each ring sector is covered with an abradable coating (13).
    [0009]
    9. Turbine ring assembly according to any one of claims 1 to 8, characterized in that the pins (40, 40 ') are made of metal.
    [0010]
    10. A turbomachine comprising a turbine ring assembly according to any one of claims 1 to 9.
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    法律状态:
    2016-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-23| PLSC| Publication of the preliminary search report|Effective date: 20160923 |
    2017-03-15| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-05-15| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20200409 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200409 |
    2020-06-05| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20200424 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200424 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552145A|FR3033825B1|2015-03-16|2015-03-16|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    FR1552145|2015-03-16|FR1552145A| FR3033825B1|2015-03-16|2015-03-16|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    US15/558,856| US10590803B2|2015-03-16|2016-03-15|Turbine ring assembly made from ceramic matrix composite material|
    GB1714846.1A| GB2552608B|2015-03-16|2016-03-15|Turbine ring assembly made from ceramic matrix composite material|
    PCT/FR2016/050567| WO2016146932A1|2015-03-16|2016-03-15|Turbine ring assembly made from ceramic matrix composite material|
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