• 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, each ring sector (1) having a base portion annular (2) with an inner face (3) defining the inner face of the turbine ring and an outer face (3a) from which extends a wall (5) defining an inner housing (6) in which a holding member (10) of metal material is present, the holding member (10) being connected to the ring support structure and comprising a body (11) from which elastically deformable holding elements (12) extend into the inner housing (6) on each side of the body (11), the holding elements (12) bearing on the wall (5).
    公开号:FR3034132A1
    申请号:FR1552372
    申请日:2015-03-23
    公开日:2016-09-30
    发明作者:Clement Roussille；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.
    [0002] However, the existing solutions proposed can implement an assembly of a CMC ring sector with metal hooking parts of a ring support structure, these hooking parts 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.
    [0003] 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 material ring sectors and a carrier 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 extends a wall defining an inner housing in which a member metal material is present, the holding member being connected to the ring support structure and comprising a body from which elastically deformable holding members extend into the inner housing on each side of the body, the elements holding being supported on the wall.
    [0004] In the invention, the holding member for maintaining the ring sector to the ring support structure is present in an inner housing of the ring sector and is therefore protected from the flow. The CMC ring sector is hot and has a low thermal conductivity and thus constitutes a thermal barrier for the holding member. The CMC ring sector thus makes it possible to obtain thermal decoupling between the inner face of the turbine ring and the holding member. The configuration according to the invention thus makes it possible to reduce the amount of gas necessary to cool the parts ensuring the maintenance of the ring sector to the ring support structure and therefore leads to an increase in the performance of the engine. Moreover, because of the thermal expansion of the metal material of the retaining member 3034132 3, the latter exerts pressure on the ring sector thus keeping it in position during operation. In one exemplary embodiment, the holding elements may bear against the wall for only part of their length.
    [0005] Unless otherwise stated, the length of a holding member is measured along the longitudinal axis of the inner housing. Such a characteristic advantageously makes it possible to obtain a local support of the holding elements on the wall and thus to maintain the ring sector in position while imposing a low mechanical stress on it. Such a configuration makes it possible to slide the holding elements on the wall in the event of differential expansion and, consequently, to compensate for the differences in expansion between the holding member and the ring sector. The holding members may bear against the wall for a length less than or equal to three quarters of their length, preferably less than or equal to half of their length, more preferably less than or equal to one quarter of their length. In an exemplary embodiment, the holding elements may be supported on the wall at their distal portion. In particular, the holding members may bear against the wall only at their distal portion. The distal portion of a holding member corresponds to the portion of said holding member between its distal end and the mid-length region of the holding member, the holding member extending between a proximal end. located on the side of the body of the holding member and a distal end located on the opposite side to said body. In particular, the holding elements may be supported on the wall at the first and second ends of the inner housing. In an exemplary embodiment, the wall may have at least one recess traversed by at least one fastening element for fixing the body of the holding member to the ring support structure. This recess makes it possible to connect the holding member to the ring support structure. This recess may, in addition, constitute a ventilation opening for supplying cooling air at the level of the holding member and at the level of the ring sector.
    [0006] In an exemplary embodiment, the length of the holding member is greater than or equal to half the length of the inner housing, for example greater than or equal to three quarters of the length of the inner housing.
    [0007] Unless otherwise stated, the length of the holding member is measured along the longitudinal axis of the inner housing. In an exemplary embodiment, the length of all or part of the holding elements is greater than the length of the body of the holding member, for example greater than or equal to twice the length of the body 10 of the holding member. Holding elements having a relatively long length advantageously have an increased elasticity, which makes it possible to obtain a particularly supple support of the holding elements on the ring sector and thus to better compensate for the differences in expansion between the ring. holding member and the ring sector without affecting the holding in position of the ring sector. Unless otherwise stated, the length of the body of the holding member is measured along the longitudinal axis of the inner housing. Alternatively, the length of all or part of the holding members is less than the length of the body of the holding member. All or part of the holding elements may have a length greater than their width, preferably greater than or equal to three times their width. The width of a holding member corresponds to its largest transverse dimension. In an exemplary embodiment, the inner housing may extend along a longitudinal axis and the holding elements may be supported on the wall at symmetrical holding zones relative to the longitudinal axis.
    [0008] In an exemplary embodiment, the holding elements may be in the form of tabs. Alternatively, the holding members may be in the form of flared portions. The flared portions extend widening over all or part of their length when moving from the body of the holding member to one end of the inner housing.
    [0009] The present invention also provides a turbomachine comprising a turbine ring assembly as defined above.
    [0010] In an exemplary embodiment, the turbine ring assembly may be part of the distributor of the turbomachine. 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. BRIEF DESCRIPTION OF THE DRAWINGS Other characteristics 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: FIGS. 1 and 2 show a holding member and a ring sector relating to a first embodiment according to the invention; FIG. 3 is a diagrammatic and partial view in section in the tangential direction of the assembly; FIG. 4 is a diagrammatic and partial view, in section perpendicular to the tangential direction, of the ring sector of FIG. 2 when mounted on the ring support structure, FIG. 5 represents a holding member and a ring sector relating to a second embodiment according to the invention, and - Figure 6 shows a section along the tangential direction of the assembly. e schematized in Figure 5.
    [0011] DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows a turbine ring sector 1 and a holding member 10 according to a first embodiment according to the invention. In FIG. 1, the holding member 10 is shown separated from the turbine ring sector 1. FIG. 2 shows, in turn, the operating configuration of the assembly of FIG. The holding member 10 holds the ring sector 1 to the ring support structure, the holding member 10 being housed in the ring sector 1. In order to form a turbine ring surrounding a set of blades rotary, a plurality of ring sectors 1 each provided with a holding member 10 are mounted on a housing 14 (see Figure 3034132 6 3) of metal material constituting ring support structure. In a manner known per se, the ring sectors 1 may each be provided with one or more sealing strips (not shown). These sealing strips allow once all the ring sectors 1 mounted on the ring support structure to reduce or even eliminate air leaks between the ring sectors 1. The sectors Ring 1 are in one piece and made of CMC. 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 an annular base 2 whose inner face 3 coated with a layer of abradable material (not shown in Figures 1 to 3) defines the flow stream of the gas stream in the turbine. The ring sectors 1 each further have a wall 5 extending from the outer face 3a of the annular base 2. The wall 5 defines an inner housing 6 extending along a longitudinal axis. The inner housing 6 extends in the tangential direction T. The tangential direction T corresponds to the circumferential direction of the turbine ring. A holding member 10 of metal material is present in the inner housing 6. The holding member 10 may be formed of a superalloy, for example "AM1" superalloy. The holding member 10 comprises a body 11 of which extend along the tangential direction of each side of the body 11 of the holding elements 12 bearing on the wall 5. In the example illustrated, the holding elements 12 are in the form of paws. The wall 5 is, in the illustrated example, provided with grooves 25 intended to cooperate with the retaining lugs 12. In a variant not shown, the wall is not provided with such grooves. As illustrated in FIG. 3, a first set of lugs 12 bears on the wall 5 on the side of the first end 61 of the inner housing 6 and a second set of lugs 12 bears against the wall 5 on the side of the second End 62 of the inner housing 6. The holding member 10 is firstly connected to the housing 14 and secondly to the ring sector 1 by supporting the holding elements 12 on the wall 5 defining the inner housing 6 FIGS. 1 to 3 show the case of an internal housing 6 passing through, the invention is not limited to this case, the internal housing being in variants not illustrated, for example being in the form of a blind hole.
    [0012] The inner housing 6 is accessible from outside the ring sector 1 at least through a through recess 9 on the wall 5 to ensure the connection of the holding member 10 to the housing 14 as shown schematically in Figure 3.
    [0013] The casing 14 comprises a plurality of fixing elements 15 in the form of hooking tabs extending radially towards a flow passage of the gas stream through the recesses 9. The radial direction corresponds to the direction according to a radius turbine ring (right connecting the center of the turbine ring to its periphery). The hooking tabs 15 of the housing 14 enclose the body 11 of the holding member 10 to ensure its attachment to the casing 14. The attachment tabs 15 each have a zone 15a located opposite the body 11 of the holding member and an outer radial end 15b located on the side of the casing 14. To mount the ring sectors 1 to the casing 14, 15 the holding member 10 is first introduced into the inner housing 6. The holding member 10 introduced into the inner housing 6 is slightly prestressed at room temperature (ie at a temperature of 20 ° C). The assembly consisting of the ring sector 1 and the holding member 10 housed in the ring sector 1 is mounted on the casing 14 by coming to grip the body 11 of the holding member 10 by the legs of the housing. It is not beyond the scope of the invention if the body is fixed to the casing other than by clipping, for example by screwing. As illustrated in FIG. 3, the latching lugs 15 of the housing 14 are partially housed in the housing 6 (i.e. only part of the length of the latching lugs 15 is accommodated in the housing 6). The recess 9 is furthermore a ventilation orifice for supplying cooling air at the level of the holding member 10 and at the level of the ring sector 1. The fact that the holding member 10 and that a part of the hooking lugs 15 are housed in the housing 6 of the ring sector 1 in CMC advantageously protects these elements from the heat of the gaseous flow flowing in the vein since the ring sector 1 is heat resistant and forms a thermal barrier. Furthermore, the presence of the differential expansion phenomenon advantageously makes it possible to keep the ring sector in axial and radial position because of the pressure exerted by the holding member 10 on it during operation. 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. As illustrated in FIG. 3, the tabs 12 bear on the wall 5 for a length less than or equal to one quarter of the length lp of the tabs 12. The length of the tabs lp is, moreover, greater than the length l of the body 11 of the holding member 10. In the example illustrated, the tabs 12 bear on the wall 5 at their distal end 12a which is located on the opposite side to the body 11. The holding member 10 10 extends, meanwhile, a length lo substantially equal to the length of the inner housing 6. Thus, the holding member 10 extends from the first end 61 to the second end 62 of the inner housing 6. As 1, the tabs 12 bear against the wall 5 at the level of retaining zones Z that are symmetrical with respect to the tangential direction T. The holding zones Z extend over only a portion of the internal circumference of FIG. the wall 5. The legs 12 are in the example shown in plane support on the wall 5. 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. For the production of the fibrous preform, it is possible to use yarns of ceramic material, for example silicon carbide (SiC) threads, such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon", or yarns made of carbon. The fiber preform is advantageously made by three-dimensional weaving or multilayer weaving. The weaving can be interlock type. Other three-dimensional weave or multilayer weaves may be used such as multi-woven or multi-satin weaves. Reference can be made to WO 2006/136755. After weaving, the fibrous blank obtained is shaped to obtain a ring sector preform which is then consolidated and densified by a ceramic matrix, the densification can be achieved in particular by implementing a chemical infiltration process. gas phase (CVI) which is well known per se. A detailed example of manufacture of ring sectors in CMC is described in particular in document US 2012/0027572. FIG. 4 is a diagrammatic and partial view, in section perpendicular to the tangential direction, of the ring sector 1 of FIG. 2 when mounted on the ring support structure 14. FIG. in order to ensure an axial seal and for the sake of simplicity the holding member 10 and the hooking lugs 15 have not been shown. The layer of abradable material 4 covering the inner face 3 of the annular base 2 has been shown in FIG. 4. The layer of abradable material 4 is situated opposite a set of rotary blades P. The arrow F represents the direction flow of the gas stream in the turbine. The gas stream flows along the axial direction A of the high pressure distributor D to the low pressure distributor (not shown). In order to ensure axial sealing, an annular seal 20 is present on the outer face 3a of the annular base 2 of the turbine ring sector 1 on the side of the high pressure distributor D. The ring sector 1 is further clamped at the wall 5 by sealing tabs 21 of the housing 14. The seal 20 and the tabs 21 prevent an axially directed gas flow from flowing between the ring sector 1 and the Casing 14. FIGS. 5 and 6 show an alternative embodiment in which a holding member 10 'made of metal material is present in the inner housing 6. The layer of abradable material 4 covering the inner face 3 of the annular base 2 has been shown in Figures 5 and 6.
    [0014] The holding member 10 'is connected to the ring support structure in the same manner as described in connection with FIG. 3. The holding member 10' comprises a body 11 'of which extend tangentially. T on each side of the body 11 'of the elastically deformable holding elements 12' which bear on the wall 5 delimiting the internal housing 6. The holding elements 12 'are, in the example illustrated in FIGS. 5 and 6, in the form of flared portions extending from the body 11 'to the ends of the inner housing 6. In the illustrated example, the flared portions 12' extend widening over a part of their length when one moves the body 11 'to one of the ends 61 or 62 of the inner housing 6. The flared portions 12' have support portions 13 'in the example shown at their distal end 3034132 10 12'a. The bearing portions 13 'bear on the wall 5 to ensure the maintenance of the ring sector 1 to the ring support structure. In the same manner as described in the exemplary embodiment illustrated in FIGS. 1 to 3, the flared portions 12 'bear against the wall 5 delimiting the internal housing 6 at their distal end 12'a. The flared portions 12 'extend in this embodiment over a length lp less than the length I, of the body 11' of the holding member 10 '. In the exemplary embodiment illustrated in FIGS. 5 and 6, the support portions 13 'of the flared portions 12' are present at the ends 61 and 62 of the inner housing 6. The internal housing 6 has a section perpendicular to its longitudinal axis of the corners C, the support portions 13 'bearing at the corners C of the inner housing 6. In the example illustrated, the support portions 13' of the flared portions 12 'are not in contact with the with each other but it is not beyond the scope of the invention when this is the case. As in the example of FIGS. 1 to 3, the flared portions 12 'bear on the wall 5 at Z holding zones that are symmetrical with respect to the longitudinal axis of the inner housing 6. In a variant that is not illustrated, the Flared portions each have a single bearing portion bearing on all or part of the inner circumference of the wall. To carry out the assembly in this exemplary embodiment, the holding member 10 'is introduced into the internal housing 6 so as to position its support portions 13' at the first and second ends 61 and 62 of the inner housing 6. The holding member 10 'introduced into the inner housing 6 is slightly preloaded at ambient temperature. The assembly consisting of the holding member 10 'and the ring sector 1 is then fixed to the fastening tabs of the housing in the same manner as in FIG. 3. 30 inner housing having a rectangular shape when observed in perpendicular section its longitudinal axis. It is not beyond the scope of the invention when the inner housing has another shape such as a square or circular shape when observed in perpendicular section its longitudinal axis.
    [0015] The term "included between ... and ..." or "from ... to ..." must be understood to include the boundaries.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A turbine ring assembly comprising a plurality of ceramic matrix composite material ring sectors (1) and a ring support structure (14), each ring sector (1) having an annular base portion ( 2) with an inner face (3) defining the inner face of the turbine ring and an outer face (3a) from which extends a wall (5) delimiting an inner housing (6) in which a body of holding (10; 10 ') of metal material is present, the holding member (10; 10') being connected to the ring support structure (14) and comprising a body (11; 11 ') from which resiliently deformable holding elements (12; 12 ') extend into the inner housing (6) on each side of the body (11; 11'), the holding elements (12; 12 ') resting on the wall (5).
    [0002]
    2. An assembly according to claim 1, wherein the holding elements (12; 12 ') bear against the wall (5) for only part of their length.
    [0003]
    3. An assembly according to any one of claims 1 and 2, wherein the holding elements (12; 12 ') are supported on the wall (5) at their distal portion.
    [0004]
    4. The assembly of claim 3, wherein the holding elements (12) are supported on the wall (5) at the first (61) and second ends (62) of the inner housing (6).
    [0005]
    5. An assembly according to any one of claims 1 to 4, wherein the holding elements are in the form of lugs (12).
    [0006]
    An assembly according to any one of claims 1 to 4, wherein the holding members are in the form of flared portions (121).
    [0007]
    7. An assembly according to any one of claims 1 to 6, wherein the length of all or part of the holding elements (12) is greater than the length (1a) of the body (11) of the holding member (10). ). 5
    [0008]
    8. An assembly according to any one of claims 1 to 7, wherein the inner housing (6) extends along a longitudinal axis and the holding elements (12; 12 ') bear against the wall ( 5) at zones (Z) of support symmetrical with respect to the longitudinal axis. 10
    [0009]
    9. Assembly according to any one of claims 1 to 8, wherein the wall (5) has at least one recess (9) traversed by at least one fastening element (15) for fixing the body (11) of the holding member (10) to the ring support structure (14). 15
    [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
    RU2017135500A|2019-04-08|
    FR3034132B1|2018-06-15|
    EP3274565B1|2021-09-22|
    US10718235B2|2020-07-21|
    RU2703896C2|2019-10-22|
    BR112017020246A2|2018-05-22|
    CA2979791A1|2016-09-29|
    CN107532483B|2020-04-14|
    EP3274565A1|2018-01-31|
    RU2017135500A3|2019-08-29|
    CN107532483A|2018-01-02|
    WO2016151233A1|2016-09-29|
    US20180080344A1|2018-03-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20120171027A1|2010-12-30|2012-07-05|General Electric Company|Structural low-ductility turbine shroud apparatus|
    EP2631434A2|2012-02-22|2013-08-28|General Electric Company|Low-ductility turbine shroud|
    US5197853A|1991-08-28|1993-03-30|General Electric Company|Airtight shroud support rail and method for assembling in turbine engine|
    US6733233B2|2002-04-26|2004-05-11|Pratt & Whitney Canada Corp.|Attachment of a ceramic shroud in a metal housing|
    US6758653B2|2002-09-09|2004-07-06|Siemens Westinghouse Power Corporation|Ceramic matrix composite component for a gas turbine engine|
    FR2887601B1|2005-06-24|2007-10-05|Snecma Moteurs Sa|MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART|
    ES2398727T3|2009-03-09|2013-03-21|Snecma|Turbine ring set|
    US9938846B2|2014-06-27|2018-04-10|Rolls-Royce North American Technologies Inc.|Turbine shroud with sealed blade track|US9863265B2|2015-04-15|2018-01-09|General Electric Company|Shroud assembly and shroud for gas turbine engine|
    FR3056632B1|2016-09-27|2020-06-05|Safran Aircraft Engines|TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT|
    FR3065481B1|2017-04-19|2020-07-17|Safran Aircraft Engines|TURBINE ASSEMBLY, PARTICULARLY FOR A TURBOMACHINE|
    US10934877B2|2018-10-31|2021-03-02|Raytheon Technologies Corporation|CMC laminate pocket BOAS with axial attachment scheme|
    US11008894B2|2018-10-31|2021-05-18|Raytheon Technologies Corporation|BOAS spring clip|
    法律状态:
    2016-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-30| PLSC| Publication of the preliminary search report|Effective date: 20160930 |
    2017-02-10| 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 |
    2018-02-20| 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
    FR1552372A|FR3034132B1|2015-03-23|2015-03-23|TURBINE RING ASSEMBLY COMPRISING A PLURALITY OF RING SECTIONS IN CERAMIC MATRIX COMPOSITE MATERIAL|
    FR1552372|2015-03-23|FR1552372A| FR3034132B1|2015-03-23|2015-03-23|TURBINE RING ASSEMBLY COMPRISING A PLURALITY OF RING SECTIONS IN CERAMIC MATRIX COMPOSITE MATERIAL|
    RU2017135500A| RU2703896C2|2015-03-23|2016-03-22|Assembled structure of turbine ring containing multiple ring segments made of composite material with ceramic matrix|
    EP16714491.4A| EP3274565B1|2015-03-23|2016-03-22|Turbine ring assembly with specific holding device for ceramic matrix composite ring segments|
    US15/560,754| US10718235B2|2015-03-23|2016-03-22|Turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material|
    CA2979791A| CA2979791A1|2015-03-23|2016-03-22|Turbine ring assembly comprising a plurality of ceramic matrix composite ring segments|
    CN201680019173.5A| CN107532483B|2015-03-23|2016-03-22|Turbine ring assembly comprising a plurality of ring sectors made of a ceramic matrix composite material|
    BR112017020246-8A| BR112017020246A2|2015-03-23|2016-03-22|turbine ring assembly and turbine engine|
    PCT/FR2016/050627| WO2016151233A1|2015-03-23|2016-03-22|Turbine ring assembly comprising a plurality of ceramic matrix composite ring segments|
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