• 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 present invention relates to a turbine ring assembly comprising a plurality of ring sectors (1) of ceramic matrix composite material and a ring support structure (2), each ring sector (1) having a annular base portion (5) with an inner face (6) defining the inner face of the turbine ring and an outer face (8) from which at least two leg portions (9a; 9b) extend, the ring support structure (2) comprising at least two radially extending hooking tabs (11a; 11b), the tabs (9a; 9b) of each ring sector (1) enclosing the hooking tabs (11a, 11b) of the ring support structure (2) at least at the inner radial ends (14a; 14b) of said latches (11a; 11b).
    公开号:FR3033826A1
    申请号:FR1552147
    申请日:2015-03-16
    公开日:2016-09-23
    发明作者:Claire Groleau；Gilles Lepretre；Etienne Voland；Thierry 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 comprising a plurality of ceramic matrix composite ring sectors and a ring support structure. 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 the hottest 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. In an attempt to solve these problems, it has been envisaged to make turbine ring sectors of ceramic matrix composite material (CMC) in order to overcome the implementation of a metallic material. CMC materials have good mechanical properties making them suitable for constituting structural elements and advantageously retain these properties at high temperatures. The use of CMC materials has advantageously made it possible to reduce the cooling flow to be imposed during operation and thus to increase the performance of the turbomachines. In addition, the use of CMC materials advantageously makes it possible to reduce the mass of the turbomachines and to reduce the hot expansion effect encountered with the metal parts. However, the existing solutions proposed can implement an assembly of a CMC ring sector with metal attachment parts of a ring support structure, these attachment portions being subjected to the hot flow. Therefore, these assembly solutions may still require the implementation of a cooling stream at least to cool said metal latching portions. In addition, these metal hooking parts undergo hot expansion, which can lead to mechanical stressing of the CMC ring sectors and embrittlement thereof.
    [0002] There is therefore a need to improve existing turbine ring assemblies employing a CMC material to further reduce the amount of cooling gas required. There is still a need to improve existing turbine ring assemblies employing a CMC material in order to reduce the intensity of the mechanical stresses to which the CMC ring sectors are subjected during operation. OBJECT AND SUMMARY OF THE INVENTION To this end, the invention provides, in a first aspect, a turbine ring assembly comprising a plurality of ceramic matrix composite ring sectors and a support structure of ring, each ring sector having an annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which at least two leg portions extend, the support structure ring assembly comprising at least two radially extending attachment tabs, the tabs of each ring sector enclosing the attachment tabs of the ring support structure at least at the inner radial ends of said tabs of the ring support structure. hooking. The radial direction corresponds to the direction along a radius of the turbine ring (straight connecting the center of the turbine ring to its periphery). The inner radial end of a latching lug corresponds to the end of said latching lug located on the side of the flow vein of the gas flow. In the invention, the attachment tabs of the ring support structure are at least partially housed between the tabs of the ring sectors. These latching lugs are thus protected from the hot flow by the CMC ring sector which axially encloses them, which has a low thermal conductivity and thus constitutes a thermal barrier for said latching lugs. The CMC ring sector 3033826 3 thus makes it possible to obtain thermal decoupling between the internal face of the turbine ring and the fastening tabs that it encloses. The configuration according to the invention thus makes it possible to reduce the amount of gas necessary to cool the latching lugs of the ring support structure and consequently leads to an increase in the performance of the motor. Preferably, the tabs of the ring sectors have, in meridian section, inclined portions facing the attachment tabs of the ring support structure, these inclined portions forming a non-zero angle with respect to the radial direction and the axial direction. The axial direction corresponds to the direction along the axis of revolution of the turbine ring and the flow direction of the gas flow in the vein.
    [0003] The use of such inclined portions advantageously makes it possible to slide the tabs of the ring sectors onto the attachment tabs of the ring support structure in the event of differential expansion and, consequently, to compensate for the differences. dilation between the latching lugs and the legs of the ring sector as well as reducing the mechanical stresses to which the ring sectors are subjected. The presence of inclined portions therefore makes it possible to obtain a sliding of the ring sectors in the event of radial and / or axial expansion of the attachment lugs, which makes it possible to avoid any radial or axial blockage of the ring sectors and therefore to avoid that these last 25 are subjected to too high constraints. The presence of the inclined portions is all the more advantageous as the hooking tabs are housed between the legs of the ring sectors, these hooking tabs therefore having a relatively small space to expand, thus leading to the application a significant mechanical stress on the legs of the ring sectors in the case where they are devoid of such inclined portions. In one exemplary embodiment, the tabs of the ring sectors can grip the attachment tabs for a length less than the length of the tabs of the ring sectors.
    [0004] Alternatively, the tabs of the ring sectors can grip the latching lugs for a length equal to the length of the legs of the ring sectors. This embodiment advantageously makes it possible to increase the extent of the bearing surface between the lugs of the ring sectors and the attachment lugs and to reduce the presence of local forces at this bearing surface. . In an exemplary embodiment, the inclined portions may form an angle of between 300 and 60 ° with the radial direction.
    [0005] Preferably, the tabs of the ring sectors may have at their outer radial end recesses extending in the tangential direction. The outer radial end of a tab of a ring sector corresponds to the end of said tab located on the opposite side to the flow stream of the gas stream. The tangential direction corresponds to the circumferential direction of the turbine ring. The presence of such recesses advantageously reduces the mechanical stresses to which the ring sector is subjected during operation.
    [0006] Preferably, a resilient damping member may be present between the inner radial ends of the hooking tabs of the ring support structure and the annular base of the ring sector whose tabs enclose said hook tabs. The presence of such a damping element advantageously makes it possible to damp the radial displacements of the ring sectors and thus to contribute to the maintenance of the ring sectors on the latching lugs during operation. In an exemplary embodiment, the damping element may be perforated. The presence of one or more openings may advantageously make it possible to cool the ring sectors. In an exemplary embodiment, the ring sectors have a substantially u-shaped section. The present invention also relates to a turbomachine comprising a turbine ring assembly as defined above.
    [0007] In an exemplary embodiment, the turbine ring assembly may be part of the turbomachine distributor.
    [0008] The turbine ring assembly may be part of a gas turbine engine of an aircraft engine or may alternatively be part of an industrial turbine.
    [0009] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of non-limiting examples, with reference to the appended drawings, in which: FIG. 1 is a meridian sectional view showing an embodiment of a turbine ring assembly according to the invention; FIG. 2 is an isolated view of a ring sector used in the assembly of FIG. Figure 3 illustrates the mounting of one of the ring sectors on the ring support structure to obtain the turbine ring assembly of Figure 1, FIG. 4 is a view of the turbine ring assembly of FIG. 1 once all of the ring sectors have been mounted, and FIG. 5 is a meridian sectional view showing an alternative embodiment of FIG. a turbine ring assembly according to the invention. DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows a turbine ring sector 1 and a metal housing 2 constituting a ring support structure. The set of ring sectors 1 is mounted on the casing 2 so as to form a turbine ring which surrounds a set of rotary blades 3. The arrow F represents the direction of flow of the gas stream in the turbine. The ring sectors 1 are in one piece and made of 30 CMCs. The use of a CMC material to make the ring sectors 1 is advantageous in order to reduce the ventilation requirements of the ring. The ring sectors 1 have a substantially n-shaped section with an annular base 5 whose inner face 6 coated with a layer 7 of abradable material defines the flow vein of the gas flow in the turbine. The annular base 5 has, in addition, an outer face 8 from which extend tabs 9a and 9b.
    [0010] Each ring sector 1 described above is made of CMC by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix.
    [0011] For producing the fiber preform, ceramic fiber yarns, for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon", or carbon fiber yarns, may be used. The fiber preform is advantageously made by three-dimensional weaving, or multilayer weaving with the provision of debonding zones enabling the parts of preforms corresponding to the lugs 9a and 9b of the preform portion corresponding to the base 5 to be spaced apart. The weaving may be of interlock type. 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 can be shaped to obtain a ring sector preform which is then consolidated and densified by a ceramic matrix, the densification being achieved in particular by chemical vapor infiltration (CVI) which is well known in itself. A detailed example of manufacture of ring sectors in CMC is described in particular in document US 2012/0027572. The casing 2 comprises latching lugs 11a and 11b extending radially towards a flow vein of the gaseous flow, the lugs 9a and 9b of the ring sectors 1 axially sealingly gripping the legs of the casing. fastening 11a and 11b of the housing 2. The attachment lugs 11a and 11b of the housing 2 are partially housed between the lugs 9a and 9b of the ring sectors 1 as shown (ie only a part of the length of the attachment lugs 11a and 11b is housed between the tabs 9a and 9b). In particular, the inner radial ends 14a and 14b of the attachment lugs 11a and 11b are sandwiched between the lugs 9a and 9b. The fact that the tabs 9a and 9b axially grip the latching lugs 11a and 11b advantageously makes it possible to protect the latching lugs 11a and 11b of the gaseous flow flowing in the vein since the ring sector 1 is resistant to heat and form a thermal barrier. The presence of the differential expansion phenomenon may advantageously also make it possible to maintain the tightness of the connection between the ring sectors 1 and the fastening lugs 11a and 11b of the casing 2. In fact, the axial expansion of the flanges hooking 11a and 11b makes it possible to exert a slight pressure on the lugs 9a and 9b of the ring sectors 1 thus ensuring the maintenance of the tightness of the connection. The hooking lugs 11a and 11b are clamped axially between inclined portions 12a and 12b defined by the lugs 9a and 9b of the ring sector 1. As illustrated, the inclined portions 12a and 12b are located opposite the hooking tabs 11a and 11b and are supported on said attachment lugs 11a and 11b in order to grip them. The inclined portions 12a and 12b are in contact with the attachment lugs 11a and 11b. As illustrated, the inclined portions 12a and 12b each extend in a straight line at a non-zero angle α with the radial direction R and a non-zero angle α 2 with the axial direction A. As mentioned above, the implementation of these inclined portions 12a and 12b advantageously makes it possible to compensate for the differences in expansion between the latching lugs 11a and 11b and the lugs 9a and 9b of the ring sectors 1 as well as to reduce the mechanical stresses to which the ring sectors 1 are subject. The ring sector 1 is thus, in the illustrated example, connected to the attachment lugs 11a and 11b of the casing 2 by means of a hammer attachment. The angle α1 may for example be between 30 ° and 60 °. In the example illustrated in FIG. 1, each of the tabs 9a or 9b has a single inclined portion 12a or 12b forming a non-zero angle with respect to the radial direction R and to the axial direction A. We do not leave the frame of the present invention when the legs of the ring sectors each comprise several inclined portions as will be detailed below. As illustrated in FIG. 1, the tabs 9a and 9b of the ring sectors 1 enclose the hooking tabs 11a and 11b over a length which is shorter than the length lp of the tabs 9a and 9b of the ring sector 1 The lengths 1a and 1p are, as illustrated, measured perpendicularly to the outer face 8 of the annular base 5 of the ring sector 1. The length can for example be less than or equal to 0.75 times the length lp.
    [0012] FIG. 1 shows an embodiment where only part of the length of the latching lugs 11a and 11b is housed between the lugs 9a and 9b. In a variant not shown, the tabs of the ring sector have a sufficient length to substantially enclose the entire length of the fastening tabs. In the example illustrated in FIG. 1, an elastic damping element 15 is present between the inner radial ends 14a and 14b of the attachment tabs 11a and 11b and the annular base 5 of the ring sector 1 whose legs 9a and 9b enclose said attachment lugs 11a and 11b. The elastic damping element 15 may for example be in the form of a plate, for example formed of a metallic material. The damping element 15 may comprise one or more openings. The presence of these openings is advantageous in order to allow the ring sector 1 to be cooled. FIG. 2 shows in isolation a ring sector 1 used in the turbine ring assembly of FIG. 1. As illustrated, the tabs 9a and 9b of the ring sector 1 have at their outer radial end 16a and 16b recesses 17a and 17b extending tangentially when the ring sector 1 is attached to the structure of the ring. ring support. As mentioned above, the presence of the recesses 17a and 17b advantageously makes it possible to reduce the mechanical stresses to which the ring sector 1 is subjected during operation. In addition, the ring sector 1 may comprise one or more sealing strips 18. These sealing strips 18 allow once all the ring sectors 1 mounted on the ring support structure to reduce, and even eliminate air leaks between the ring sectors 1. Figure 3 illustrates the mounting of a ring sector 1 to the housing 2. The ring sector 1 to be mounted is presented facing the 2. The ring sector 1 to be mounted can, in one embodiment, be provided with a damping element 15 as illustrated in FIG. 1. The ring sector 1 is inserted in FIG. translation and then angularly offset as represented by the arrows of FIG. 3. FIG. 4 is a view of the turbine ring assembly of FIG. 1 once the set of ring sectors has been mounted. As illustrated, a plurality of CMC ring sectors 1 are mounted on the ring support structure 2. The turbine ring assembly further includes a closure key 20 present at one of the sectors. ring and 3033826 9 to ensure the cohesion of all ring sectors between them. The closure key 20 is present at the last mounted ring sector. FIG. 5 illustrates an alternative embodiment in which the tabs 9'a and 9'b of the ring sectors 1 'enclose the hooking tabs 11'a and 11'b over a length substantially equal to the length of the tabs 9'a and 9'b. In the example of FIG. 5, each of the tabs 9'a or 9'b has a first inclined portion 12'a or 12'b forming a non-zero angle with respect to the radial direction and to the axial direction as well as a second inclined portion 12 "a or 12" b forming a non-zero angle with respect to the radial direction and the axial direction. The first and second inclined portions are present on either side of a bend C formed by the tabs 9'a and 9'b of the ring sector 1 '. The elbow C may, as illustrated, be substantially located at mid-length of the legs 9'a and 9'b. The expression "understood between ... and ..." or "from ... to" must be understood as including boundaries.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A turbine ring assembly comprising a plurality of ceramic matrix composite material ring sectors (1; 1 ') and a ring support structure (2), each ring sector (1; 1') having an annular base portion (5) with an inner face (6) defining the inner face of the turbine ring and an outer face (8) from which at least two leg portions (9a; 9b; 9'a; 9'b), the ring support structure (2) comprising at least two radially extending hook tabs (11a; 11b; 11'a; 11'b), the tabs (9a; 9b, 9'a, 9'b) of each ring sector (1; 1 ') enclosing the hooking tabs (11a; 11b; 11'a; 11'b) of the ring support structure ( 2) at least at the inner radial ends (14a; 14b; 14'a; 14'b) of said latches (11a; 11b; 11'a; 11'b).
    [0002]
    2. An assembly according to claim 1, wherein the tabs (9a, 9b, 9'a, 9'b) of the ring sectors (1; 1 ') have in meridian section inclined portions (12a; 12b; 12'). a, 12 'b; 12 "a; 12" b) facing the hooking tabs (11a; 11b; 11'a; 11'b) of the ring support structure (2), these inclined portions ( 12a; 12b; 12a; 12b; 12a; 12b) forming a non-zero angle (a1; a2) with respect to the radial direction (R) and the axial direction (A).
    [0003]
    3. An assembly according to any one of claims 1 and 2, wherein the tabs (9a, 9b) of the ring sectors (1) enclose the latching lugs (11a, 11b) for a length less than the length of the tabs (9a, 9b) of the ring sectors (1).
    [0004]
    4. An assembly according to any one of claims 1 and 2, wherein the tabs (9'a; 9'b) of the ring sectors (1 ') enclose the latches (11'a; Mt) on a length substantially equal to the length of the tabs (9'a; 9'b) of the ring sectors (1 '). 3033826 11
    [0005]
    5. An assembly according to any one of claims 2 to 4, wherein the inclined portions (12a; 12b; 12'a; 12'b; 12 "a; 12" b) form an angle of between 300 and 60 ° with the radial direction (R). 5
    [0006]
    6. An assembly according to any one of claims 1 to 5, wherein the tabs (9a; 9b) of the ring sectors (1) have at their outer radial end (16a; 16b) recesses (17a; 17b) s. extending in tangential direction. 10
    [0007]
    7. An assembly according to any one of claims 1 to 6, wherein an elastic damping element (15) is present between the inner radial ends (14a; 14b) of the latches (11a; 11b) of the structure ring support (2) and the annular base (5) of the ring sector (1) whose tabs (9a; 9b) enclose said hooking tabs (11a; 11b).
    [0008]
    8. The assembly of claim 7, wherein the damping element (15) is openwork. 20
    [0009]
    An assembly according to any of claims 1 to 8, wherein the ring sectors have a substantially r-shaped cross-section.
    [0010]
    A turbomachine comprising a turbine ring assembly according to any one of claims 1 to 9.
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    同族专利:
    公开号 | 公开日
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    CA2979474A1|2016-09-22|
    EP3271556A1|2018-01-24|
    CN107429574B|2020-03-20|
    FR3033826B1|2018-11-23|
    BR112017019585A2|2018-05-02|
    CN107429574A|2017-12-01|
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    WO2016146942A1|2016-09-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    US10100737B2|2013-05-16|2018-10-16|Siemens Energy, Inc.|Impingement cooling arrangement having a snap-in plate|FR3033825B1|2015-03-16|2018-09-07|Safran Aircraft Engines|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    FR3045715B1|2015-12-18|2018-01-26|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH COLD AND HOT HOLDING|
    FR3049003B1|2016-03-21|2018-04-06|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET|
    FR3064024B1|2017-03-16|2019-09-13|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
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    US11255210B1|2020-10-28|2022-02-22|Rolls-Royce Corporation|Ceramic matrix composite turbine shroud assembly with joined cover plate|
    法律状态:
    2016-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-23| PLSC| Publication of the preliminary search report|Effective date: 20160923 |
    2017-02-10| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-25| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170725 Owner name: HERAKLES, FR Effective date: 20170725 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20170717 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    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
    FR1552147|2015-03-16|
    FR1552147A|FR3033826B1|2015-03-16|2015-03-16|TURBINE RING ASSEMBLY COMPRISING A PLURALITY OF RING SECTIONS IN CERAMIC MATRIX COMPOSITE MATERIAL|FR1552147A| FR3033826B1|2015-03-16|2015-03-16|TURBINE RING ASSEMBLY COMPRISING A PLURALITY OF RING SECTIONS IN CERAMIC MATRIX COMPOSITE MATERIAL|
    RU2017134699A| RU2717180C2|2015-03-16|2016-03-16|Turbine ring assembly comprising a plurality of ring sectors made of composite material with ceramic matrix|
    BR112017019585-2A| BR112017019585A2|2015-03-16|2016-03-16|turbine ring assembly and turbine engine|
    CN201680016325.6A| CN107429574B|2015-03-16|2016-03-16|Turbine ring assembly comprising a plurality of ring sectors made of a ceramic matrix composite material|
    EP16715017.6A| EP3271556B1|2015-03-16|2016-03-16|Assembly of turbine rings comprising shrouds made of ceramic composite|
    PCT/FR2016/050580| WO2016146942A1|2015-03-16|2016-03-16|Turbine ring assembly comprising a plurality of ring sectors made from ceramic matrix composite material|
    CA2979474A| CA2979474A1|2015-03-16|2016-03-16|Turbine ring assembly comprising a plurality of ring sectors made from ceramic matrix composite material|
    US15/558,829| US10544704B2|2015-03-16|2016-03-16|Turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material|
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