• 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 forming a turbine ring and a ring support structure (2), each ring sector. (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 a hooking portion (9) extends; ) from the ring sector to the ring support structure, the ring support structure (2) comprising two annular flanges (11a; 11b) between which the catch portion of each ring sector is held, the annular flanges of the ring support structure each having at least one inclined portion (12a; 12b; 13a; 13b) resting on the attachment portions of the ring sectors, said inclined portion forming when observed in meridian section, a non-zero angle to the ra direction diale (R) and in the axial direction (A).
    公开号:FR3036435A1
    申请号:FR1554626
    申请日:2015-05-22
    公开日:2016-11-25
    发明作者:Clement Roussille；Gael Evain；Adele Lyprendi；Lucien Quennehen
    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. As a result, these metal hooking parts undergo hot expansion, which can lead to mechanical stressing of the CMC ring sectors and embrittlement thereof.
    [0003] There is 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 proposes, in a first aspect, a turbine ring assembly comprising a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a structure. ring support, 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 latching portion of the annular sector. ring support structure, the ring support structure comprising two annular flanges between which the catch portion of each ring sector is held, the annular flanges of the ring support structure each having at least one inclined portion resting on the attachment portions of the ring sectors, said inclined portion forming, when observed in meridian section, a non-zero angle with respect to the direction ra diale and axial direction. 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 axial direction corresponds to the direction along the axis of revolution of the turbine ring as well as to the flow direction of the gaseous flow in the vein. The use of such inclined portions at the annular flanges of the ring support structure advantageously makes it possible to compensate for the differences in expansion between the annular flanges and the attachment portions of the ring sectors and therefore to reduce the mechanical stresses to which the ring sectors are subjected during operation. Preferably, at least one of the flanges of the ring support structure is elastically deformable. This advantageously makes it possible to compensate even better for the differential expansions between the fastening portions of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the "cold" stress exerted by the flanges on the attachment parts of the ring sectors. In particular, the two flanges of the ring support structure are elastically deformable or only one of the two flanges of the ring support structure is elastically deformable. In an exemplary embodiment, each of the annular flanges of the ring support structure may have first and second inclined portions resting on the hooking portions of the ring sectors, said first and second inclined portions each forming when observed in meridian section, a non-zero angle with respect to the radial direction and the axial direction. In particular, the first inclined portion may bear on the upper half of the attachment portions of the ring sectors and the second inclined portion may be supported on the lower half of the attachment portions of the ring sectors. The upper half of a hook portion of a ring sector corresponds to the portion of said hook portion extending radially between the mid-length region of the hook portion and the end of the hook portion. the snap portion located on the side of the ring support structure. The lower half of a hooking portion of a ring sector corresponds to the portion of the hooking part extending radially between the half-length zone of the hooking portion and the end of the hook portion. fastening portion located on the side of the annular base. In an exemplary embodiment, the hooking portions of the ring sectors can be maintained at the ring support structure at axial portions each extending parallel to the axial direction, these axial portions being formed by the flanges. 30 annular or by a plurality of inserts engaged without cold play through the annular flanges. In an exemplary embodiment, the annular flanges of the ring support structure may grip the ring sector engaging portions over at least half the length of said attachment portions.
    [0004] In an exemplary embodiment, the annular flanges of the ring support structure can grip the attachment portions of the ring sectors at least at the outer radial ends of said attachment portions. The outer radial end of a hooking portion corresponds to the end of this hooking portion located on the opposite side to the flow passage of the gas flow. In particular, the annular flanges of the ring support structure may enclose the engaging portions of the ring sectors only at the upper half of said attachment portions. In an exemplary embodiment, the attachment portion of each ring sector may be in the form of radially extending tabs. In particular, the outer radial ends of the legs of the ring sectors may not be in contact and the tabs of the ring sectors may define between them an internal ventilation volume for each of the ring sectors. In an exemplary embodiment, the attachment portion of each of the ring sectors is in the form of a bulb. In an exemplary embodiment, the ring sectors have a substantially S2-shaped or substantially U-shaped section. The present invention also relates to a turbomachine comprising a turbine ring assembly as described above. 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: Fig. 1 is a meridian sectional view showing an embodiment of a turbine ring assembly according to the invention; - Fig. 2 shows a detail of Fig. 1, 3036435; - Figs. 3 to 6 are views. in meridian section showing embodiments of turbine ring assemblies according to the invention; FIG. 7 shows the flange implemented in the embodiment of FIG. 6; FIGS. 8 to 10 illustrate the mounting the ring sectors in the case of the embodiment of Figure 5, and - Figures 11 to 15 illustrate the mounting of the ring sectors in the case of the embodiment of Figure 6.
    [0005] DETAILED DESCRIPTION OF EMBODIMENTS In the following, the terms "upstream" and "downstream" are used herein with reference to the direction of flow of the gas stream in the turbine (see arrow F in Fig. 1, for example).
    [0006] Figure 1 shows a turbine ring sector 1 and a housing 2 made of metallic material constituting ring support structure. The ring support structure 2 is made of a metallic material such as Waspaloy® alloy or Inconel® alloy 718. The set of ring sectors 1 is mounted on the housing 2 so as to form a turbine ring which surrounds a set of rotating blades 3. The arrow F represents the direction of flow of the gas flow in the turbine. Ring sectors 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, in the example shown, a substantially shaped section herewith an annular base 5 whose inner face 6 coated with a layer 7 of abradable material defines the flow vein of the gas stream in the turbine. The annular base 5 has, in addition, an outer face 8 from which extends a hooking portion 9. In the example shown, the hooking portion 9 is in the form of a solid bulb, it is not beyond the scope of the invention when the attachment portion is in the form of a hollow bulb or when the latter is in another form as detailed below. Inter-sector sealing is provided by sealing tabs (not shown) housed in grooves facing each other in opposite edges of two adjacent ring sectors.
    [0007] 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 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. The weaving can be interlock type. Other three-dimensional weave or multilayer weaves may be used such as multi-web or multi-satin weaves. For this purpose, reference may 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 can be 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 two annular radial flanges 11a and 11b of metallic material extending radially towards a flow vein of the gas flow. The annular flanges 11a and 11b of the casing 2 axially grip the attachment portions 9 of the ring sectors 1. Thus, as shown in FIG. 1, the attachment portions 9 of the ring sectors 1 are held between the flanges. 11a and 11b, the hooking portions 9 being housed between the annular flanges 11a and 11b. In addition, conventionally, ventilation orifices 34 formed in the flange 11a make it possible to supply cooling air to the outside of the turbine ring 1. The annular flanges 11a and 11b each have two inclined portions. resting on the attachment parts 9 ring sectors 1 and ensuring their maintenance. The inclined portions of the annular flanges 11a and 11b are in contact with the attachment portions 9 of the ring sectors 1. The upstream annular flange 11a has a first inclined portion 12a and a second inclined portion 13a. The downstream annular flange 35 also has a first inclined portion 12b and a second inclined portion 13b. When observed in section 3036435 7 meridian and as illustrated in Figures 1 and 2, the first inclined portion 12a of the upstream annular flange 11a forms a non-zero angle al with the radial direction R and forms a non-zero angle a2 with the axial direction A. Similarly, when observed in meridian section, the second inclined portion 13a of the upstream annular flange 11a forms a non-zero angle a3 with the radial direction R and forms a non-zero angle a4 with the axial direction A. is the same for the first and second inclined portions 12b and 13b of the downstream annular flange 11b. As illustrated, the inclined portions of the annular flanges 11a and 11b each extend in a straight line at a non-zero angle to the radial direction R and a non-zero angle to the axial direction A. When viewed in meridian section, all or part of the inclined portions of the annular flanges 11a and 11b may form an angle of between 30 ° and 60 ° with the radial direction. For each of the annular flanges 11a and 11b, the angle formed between its first inclined portion and the radial direction may or may not be equal to the angle formed between its second inclined portion and the radial direction, when the first and second inclined portions are observed in meridian section. In the example shown, the annular flanges 11a and 11b 20 enclose the attachment portions 9 of the ring sectors over more than half the length I of said attachment portions 9, in particular over at least 75% of this length. . The length I is measured in the radial direction R. In the example illustrated in FIG. 1, the first inclined portions 12a and 12b are, when observed in meridian section, each resting on the upper half M1 of the parts of 9 and the second inclined portions 13a and 13b are, when observed in meridian section, each resting on the lower half M2 of the attachment portions 9. The upper half M1 corresponds to the portion of the attachment portion 9 extending radially between the Z zone at mid-length of the attachment portion 9 and the end E1 of the attachment portion located on the side of the ring support structure 2 (outer radial end). The lower half M2 corresponds to the portion of the hooking part 9 extending radially between the half-length zone Z of the fastening part 9 and the end E2 of the fastening part situated on the side of the fastening part 9. the annular base 5. The inclined portions 3036435 8 of the annular flanges 11a and 11b define two hooks between which the attachment portions 9 of the ring sectors 1 are gripped axially. Each of these hooks has, in the illustrated example, substantially a form of C.
    [0008] The invention is however not limited to the case where the annular flanges each have such first and second inclined portions. It will be, in fact, described hereinafter the case where each of the annular flanges has a single inclined portion bearing on the attachment portions of the ring sectors.
    [0009] As mentioned above, the implementation of the inclined portions advantageously makes it possible to compensate for the differences in expansion between the annular flanges 11a and 11b, on the one hand, and the ring sectors 1, on the other hand, and thus reduce the mechanical stresses to which the ring sectors 1 are subjected during operation. In the embodiments of Figures 1 to 5, at least one of the annular flanges (flange IIb in Figure 1) is, as illustrated, provided on its outer face with a hook 25 whose function will be detailed later.
    [0010] In the example illustrated in FIG. 1, the maintenance of the ring sectors 1 to the ring support structure 2 is only ensured by the annular flanges 11a and 11b (no presence of an attached element such as a peg through the attachment portion 9 of the ring sectors). As will be detailed hereinafter, certain exemplary embodiments of the invention may employ such inserts to participate in maintaining the ring sectors on the ring support structure. FIG. 3 shows an alternative embodiment of a turbine ring assembly according to the invention. In this example, the latching portion of the ring sectors 1a is in the form of tabs 9a and 9b extending radially from the outer face 8 of the annular base 5. In this example, the outer radial ends 10a and 10b of the legs 9a and 9b of the ring sectors 1a are not in contact. The outer radial end of a tab of a ring sector 35 corresponds to the end of said tab located on the opposite side to the flow line of the gas stream. The outer radial ends 10a and 10b are, in the example illustrated in FIG. 3, spaced along the axial direction A. The lugs 9a and 9b of the ring sectors define between them an internal volume V of ventilation for each of the ring sectors la. It is thus possible to ventilate the ring sectors 1a by sending cooling air to their annular base 5 through the ventilation opening 14 defined between the tabs 9a and 9b. The ring sectors 1a of FIG. 3 have substantially an open shape S2 at its end located on the side of the ring support structure 2.
    [0011] The fiber preform intended to form the ring sector 1a of the type illustrated in FIG. 3 can be made by three-dimensional weaving, or multilayer weaving with the provision of debonding zones enabling the portions of preforms corresponding to the legs 9a and 9b to be spaced apart. of the preform part corresponding to the base 5. In a variant, the parts of preforms corresponding to the tabs can be made by weaving layers of threads passing through the preform part corresponding to the base 5. FIG. an alternative embodiment in which the ring sectors 1b are held in the ring support structure 2 by means of annular flanges 21a and 21b each having, as illustrated, an axial portion 16a or 16b extending parallel to the axial direction A. In addition, each of the annular flanges 21a and 21b has a single inclined portion 13a or 13b resting on the legs 19a o 19b of the ring sectors 1b and forming a non-zero angle with respect to the radial direction R and to the axial direction A. The tabs 19a and 19b forming the attachment portion of the ring sectors 1b are maintained at ring support structure 2 at the axial portions 16a and 16b. The annular flanges 21a and 21b axially enclose the tabs 19a and 19b of the ring sectors 1b at their outer radial end 20a and 20b. In the illustrated example, the inclined portion and the axial portion form for each of the annular flanges 21a and 21b a hook bearing on the tabs 19a and 19b of the ring sectors 1b. The tabs 19a and 19b of the ring sectors 1b are clamped axially between these two hooks formed by the annular flanges 21a and 21b. In the example shown in Figure 4, the ring sectors 1b have a substantially shaped section -1-r.
    [0012] The embodiments to be described illustrated in Figures 5 and 6 relate to the case where an insert is present through the attachment portion of the ring sectors to maintain them. As explained above, the presence of such an added element is optional in the context of the present invention. FIG. 5 shows an alternative embodiment in which the ring sectors 1c are held by blocking pins 35 and 37. More specifically and as illustrated in FIG. 5, pins 35 are engaged both in the annular upstream radial flange 31a of the ring support structure 10 and in the upstream legs 29a of the ring sectors 1c. For this purpose, the pins 35 each respectively pass through an orifice formed in the annular upstream radial flange 31a and an orifice formed in each upstream leg 29a, the orifices of the flange 31a and lugs 29a being aligned during the assembly of the ring sectors. 1c on the ring support structure 2. Likewise, pins 37 are engaged both in the annular downstream radial flange 31b of the ring support structure 2 and in the downstream legs 29b of the ring sectors. 1 C. For this purpose, the pins 37 each respectively pass through an orifice formed in the annular downstream radial flange 31b and an orifice formed in each downstream lug 29b, the orifices of the flange 31b and lugs 29b being aligned during the assembly of the ring sectors. 1c on the ring support structure 2. The pins 35 and 37 are engaged without cold play through the flanges 31a and 31b and the tabs 29a and 29b. The pins 35 and 37 make it possible to block in rotation the ring sectors 1c. The annular flanges 31a and 31b each further have a single inclined portion 13a or 13b for reducing the stress applied to the ring sectors 1c during the expansion of the annular flanges 31a and 31b during operation. FIG. 6 shows an alternative embodiment in which each ring sector 1c has a substantially u-shaped section with an annular base 5 whose inner face coated with a layer 7 of abradable material defines the d flow of gas flow in the turbine. Upstream and downstream tabs 29a and 29b extend from the outer face of the annular base 5 in the radial direction R.
    [0013] The ring support structure 2 is, in this embodiment, formed of two parts, namely a first part 3036435 11 corresponding to an annular upstream radial flange 31a which is preferably formed integrally with a turbine casing and a second portion corresponding to an annular retention flange 50 mounted on the turbine casing. The annular upstream radial flange 31a 5 comprises an inclined portion 13a as described above in bearing on the upstream legs 29a of ring sectors 1c. On the downstream side, the flange 50 comprises an annular web 57 which forms an annular downstream radial flange 54 having an inclined portion 13b as described above in support on the downstream legs 29b of the ring sectors 1c. The flange 50 comprises an annular body 51 extending axially and comprising, on the upstream side, the annular web 57 and, on the downstream side, a first series of teeth 52 distributed circumferentially on the flange 50 and spaced from each other by first engagement passages 53 (Figure 7). The turbine casing has on the downstream side a second series of teeth 60 extending radially from the inner surface 38a of the ferrule 38 of the turbine casing. The teeth 60 are distributed circumferentially on the inner surface 38a of the ferrule 38 and spaced from each other by second engagement passages 61 (Fig. 13). The teeth 52 and 60 cooperate with each other to form a conventional interconnection. The tabs 29a and 29b of each ring sector 1c are preloaded between the annular flanges 31a and 54 so that the flanges exert, at least "cold", that is to say at room temperature about 25 ° C, a strain on the tabs 29a and 29b. Furthermore, as in the embodiment of Figure 5, the ring sectors 1c are further maintained by blocking pins 35 and 37. At least one of the flanges of the ring support structure is elastically deformable This further compensates for the differential expansion between the legs of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the "cold" stress caused by the flanges on the metal ring support structures. paws of the ring areas. In addition, the upstream-downstream seal of the turbine ring assembly is provided by an annular boss 70 extending radially from the inner surface 38a of the ferrule 3036435 12 turbine shell 38. and whose free end in contact with the surface of the body 51 of the flange 50. There will now be described two methods of mounting used to mount the ring sectors on the ring support structure. FIGS. 8 to 10 which will be described illustrate the mounting of the ring sectors in the case of the embodiment of FIG. 5. As illustrated in FIG. 8, the gap E between the annular upstream radial flange 31 a and the annular downstream radial flange 31b at "rest", i.e. when no ring sector is mounted between the flanges, is smaller than the distance D between the outer faces 29c and 29d of the upstream legs and downstream 29a and 29b of the ring sectors. The gap E is measured between the ends of the inclined portions 13a and 13b of the annular flanges 31a and 31b.
    [0014] The ring support structure comprises at least one annular flange which is elastically deformable in the axial direction A of the ring. In the present example, the annular downward radial flange 31b is elastically deformable. When mounting a ring sector 1c, the annular downstream radial flange 31b is drawn in the axial direction A as shown in FIGS. 9 and 10 in order to increase the spacing between the flanges 31a and 31b and to allow insertion of the tabs 29a and 29b between the flanges 31a and 31b without risk of damage. Once the tabs 29a and 29b of a ring sector 1c inserted between the flanges 31a and 31b and positioned to align the orifices 35a and 35b, on the one hand, and 37a and 37b on the other hand, the flange 31b is released to maintain the ring sector. In order to facilitate pulling apart the annular downstream radial flange 31b, the latter comprises a plurality of hooks 25 distributed on its face 31c, which face is opposite the face 31d of the flange 31b opposite the downstream tabs 29b. ring sectors 1c. The traction in the axial direction A of the ring exerted on the elastically deformable flange 31b is here carried out by means of a tool 250 comprising at least one arm 251 whose end comprises a hook 252 which is engaged in the hook 25 present on the outer face 31c of the flange 31b. The number of hooks 25 distributed on the face 31c of the flange 31b is defined as a function of the number of traction points that one wishes to have on the flange 31b. This number depends mainly on the elastic nature of the flange. Other forms and arrangements of means for exerting traction in the axial direction A on one of the flanges of the ring support structure can of course be envisaged.
    [0015] Once the ring sector 1c has been inserted and positioned between the flanges 31a and 31b, pins 35 are engaged in the aligned orifices 35b and 35a respectively formed in the annular upstream radial flange 31a and in the upstream leg 29a, and pieces 37 are engaged in the aligned orifices 37b and 37a formed respectively in the annular downstream radial flange 31b and in the downstream leg 29b. Each ring sector lug 29a or 29b may comprise one or more orifices for the passage of a blocking pin. A similar method may be used to mount the ring sectors in the context of the examples illustrated in FIGS. 1, 3 and 4 except that no blocking pin is used in this case. We will now describe the mounting of the ring sectors 1c in the case of the embodiment of Figure 6. As shown in Figure 11, the ring sectors 1c are first fixed by their upstream leg 20 29a to the annular upstream radial flange 31a of the ring support structure 2 by pins 35 which are engaged in the aligned orifices 35b and 35a formed respectively in the annular upstream radial flange 31a and in the upstream leg 29a. Once all the ring sectors 1c thus fixed to the annular upstream radial flange 31a, the annular retaining flange 50 is assembled by interconnection between the turbine casing and the downstream lugs of the ring sectors 29b. According to the embodiment described here, the spacing E 'between the annular downstream radial flange 54 formed by the annular web 57 of the flange 50 and the outer surface 52a of the teeth 52 of said flange is greater than the distance D' present between the external face 29d of the downstream legs 29b of the ring sectors and the inner face 60a of the teeth 60 present on the turbine casing. By defining a gap E 'between the annular downstream radial flange and the outer surface of the teeth of the upper flange at the distance D' between the outer face of the downstream lugs of the ring sectors and the inner face of the teeth present 3036435 14 on the turbine casing, it is possible to mount the ring segments prestressed between the flanges of the ring support structure. The ring support structure comprises at least one annular flange which is elastically deformable in the axial direction A of the ring. In the example described here, it is the annular downstream radial flange 54 present on the flange 50 which is elastically deformable. Indeed, the annular web 57 forming the annular downstream radial flange 54 of the ring support structure 2 has a reduced thickness relative to the annular upstream radial flange 31a, which gives it a certain elasticity. As illustrated in Figures 14 and 15, the flange 50 is mounted on the turbine casing by placing the teeth 52 present on the flange 50 vis-à-vis the engagement passages 61 formed on the turbine housing, the teeth 60 present on said turbine casing being also placed vis-a-vis the engagement passages 53 formed between the teeth 52 on the flange 50. The spacing E 'being greater than the distance D', it is necessary to apply an axial force on the flange 50 in the direction indicated in Figure 14 to engage the teeth 52 beyond the teeth 60 and allow a rotation R 'of the flange at an angle 20 substantially corresponding to the width of the teeth 60 and 52. After this rotation, the flange 50 is released, the latter then being maintained in axial stress between the downstream tabs 29b of the ring sectors and the inner surface 60a of the teeth 60 of the turbine casing. Once the flange thus installed, pins 37 are engaged in the aligned orifices 56 and 37a formed respectively in the annular downstream radial flange 54 and in the downstream leg 29b. Each ring sector lug 29a or 29b may comprise one or more orifices for the passage of a blocking pin.
    [0016] 30 The expression "understood between ... and ..." or "from ... to" must be understood as including boundaries.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A turbine ring assembly comprising a plurality of ring sectors (1; la; lb; 1c) of ceramic matrix composite material forming a turbine ring and a ring support structure (2), each sector of ring (1; la; lb; 1c) 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 extends a hooking portion (9; 9a; 9b; 19a; 19b; 29a; 29b) of the ring sector to the ring support structure, the ring support structure (2) comprising two annular flanges (11a 11b; 21a; 21b; 31a; 31b; 50) between which the hooking portion of each ring sector is held, the annular flanges of the ring support structure each having at least one inclined portion (12a; 12b, 13a, 13b) resting on the hooking portions of the ring sectors, said inclined portion forming, when observed in section m ridienne, a non-zero angle relative to the radial direction (R) and the axial direction (A).
    [0002]
    2. An assembly according to claim 1, wherein each of the annular flanges (11a; 11b) of the ring support structure (2) has a first (12a; 12b) and a second (13a; 13b) portions inclined in abutment. on the hooking portions (9; 9a; 9b) of the ring sectors (1; la), said first (12a; 12b) and second (13a; 13b) inclined portions each forming, when observed in meridian section, a non-zero angle with respect to the radial direction (R) and the axial direction (A).
    [0003]
    3. An assembly according to claim 2, wherein the first inclined portion (12a; 12b) bears on the upper half (M1) of the attachment portions (9; 9a; 9b) of the ring sectors (1; ) and wherein the second inclined portion (13a; 13b) bears on the lower half (M2) of the hooking portions (9; 9a; 9b) of the ring sectors (1; la). 3036435 16
    [0004]
    An assembly according to claim 1, wherein the hooking portions (19a; 19b; 29a; 29b) of the ring sectors (Ib; 1c) are held at the ring support structure (2) at the axial portions (16a; 16b) each extending parallel to the axial direction, said axial portions being formed by the annular flanges (21a; 21b) or by a plurality of inserts (35; 37) engaged without cold play through the annular flanges (31a; 31b).
    [0005]
    An assembly according to any one of claims 1 to 4, wherein the annular flanges (11a; 11b) of the ring support structure (2) enclose the engaging portions (9) of the ring sectors. (1) at least half the length / hooking portions (9). 15
    [0006]
    An assembly according to any one of claims 1 to 5, wherein the annular flanges (21a; 21b) of the ring support structure (2) enclose the latching portions (19a; ring (1b) at least at the outer radial ends (20a; 20b) of said hooking portions (19a; 19b). 20
    [0007]
    An assembly according to any one of claims 1 to 6, wherein the engagement portion of each ring sector is in the form of radially extending tabs (9a; 9b; 19a; 19b; 29a; 29b). . 25
    [0008]
    An assembly according to claim 7, wherein the outer radial ends (10a; 10b; 20a; 20b) of the tabs of the ring sectors are not in contact and in which the tabs of the ring sectors define a volume between them. inside (V) of ventilation for each of the ring sectors. 30
    [0009]
    9. An assembly according to any one of claims 1 to 6, wherein the attachment portion of each of the ring sectors is in the form of a bulb (9). 3036435 17
    [0010]
    An assembly according to any one of claims 1 to 9, wherein the ring sectors have a substantially Q-shaped or substantially u-shaped section. 5
    [0011]
    A turbomachine comprising a turbine ring assembly according to any one of claims 1 to 10.
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    RU2017145079A3|2019-10-23|
    EP3298246A1|2018-03-28|
    CN108138579A|2018-06-08|
    RU2017145079A|2019-06-24|
    CN108138579B|2020-03-06|
    WO2016189223A1|2016-12-01|
    FR3036435B1|2020-01-24|
    RU2741192C2|2021-01-22|
    US20180156068A1|2018-06-07|
    US10724401B2|2020-07-28|
    US20200291820A1|2020-09-17|
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    法律状态:
    2016-05-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-25| PLSC| Publication of the preliminary search report|Effective date: 20161125 |
    2017-04-26| 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 AIRCRAFT ENGINES, FR Effective date: 20170719 Owner name: SAFRAN CERAMICS, 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
    FR1554626A|FR3036435B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY|
    FR1554626|2015-05-22|FR1554626A| FR3036435B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY|
    PCT/FR2016/051168| WO2016189223A1|2015-05-22|2016-05-18|Turbine ring assembly|
    CN201680040291.4A| CN108138579B|2015-05-22|2016-05-18|Turbine ring assembly|
    CA2986661A| CA2986661A1|2015-05-22|2016-05-18|Turbine ring assembly|
    EP16726369.8A| EP3298246A1|2015-05-22|2016-05-18|Turbine ring assembly|
    CN202010080478.5A| CN111188655A|2015-05-22|2016-05-18|Turbine ring assembly|
    US15/576,157| US10724401B2|2015-05-22|2016-05-18|Turbine ring assembly|
    BR112017024871-9A| BR112017024871A2|2015-05-22|2016-05-18|"turbine ring assembly, and turbine engine".|
    RU2017145079A| RU2741192C2|2015-05-22|2016-05-18|Turbine ring assembly|
    US16/886,331| US11118477B2|2015-05-22|2020-05-28|Turbine ring assembly|
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