Casing for an aircraft turbine or turbomachine

Abstract

A housing (5, 6) for an aircraft turbomachine, said housing (5, 6) being made of metal and having an annular shape about an axis, the housing (5, 6) comprising: - an annular wall (51) having an internal annular surface and an external annular surface, and - at least one annular flange (52, 53) extending radially inward from the internal surface of the wall (51), characterized in that it further comprises: - at least one sealing element (100) permanently fixed to said at least one flange (52, 53). Abbreviated figure: Figure 3

Description

Title of the invention: CASING FOR AN AIRCRAFT TURBINE OR TURBOMACHINE Technical field of the invention

[0001] The invention relates to the technical field of turbomachines, in particular for aircraft. More particularly, the invention relates to a casing for an aircraft turbine or turbomachine, as well as a turbine or turbomachine comprising this casing. Technical background

[0002] The technical background includes in particular documents FR-A1-3 064 023 and FR-A1-3 065 481.

[0003] Generally speaking, an aircraft turbomachine such as a bypass turbojet comprises, from upstream to downstream, a fan, a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.

[0004] A high-pressure turbine of the turbomachine comprises at least one stage comprising a distributor formed from an annular row of fixed straightening vanes and a bladed wheel mounted to rotate downstream of the distributor in a sealing ring also called a turbine ring.

[0005] When the turbine ring is made of a metal alloy, it is necessary to cool it by a flow of ventilation air because it is subjected to relatively high temperatures during operation. This cooling has a significant impact on the performance of the engine since the air flow used is taken from the main flow of the engine. In addition, the use of metal for the turbine ring limits the possibilities of increasing the temperature at the turbine, which would nevertheless improve the performance of aeronautical engines.

[0006] In an attempt to resolve these problems, it was considered to produce the turbine ring from a ceramic matrix composite (CMC) material to avoid the use of a metallic material.

[0007] CMC materials have good mechanical properties making them suitable for forming structural elements and advantageously retaining their properties at high temperatures. The use of CMC materials has advantageously made it possible to reduce the cooling flow required during operation and therefore to increase the performance of the turbomachine. In addition, the use of CMC materials advantageously makes it possible to reduce the mass of the turbomachine and to reduce the effect of hot expansion encountered with metal parts.

[0008] The turbine ring is generally sectorized and formed of several ring sectors arranged circumferentially end to end. The ring sectors are fixed to a metal casing.

[0009] There are several technologies for fixing a turbine ring or ring sectors to a casing and we are interested here in fixing by flanges.

[0010] The housing comprises an annular wall having an inner annular surface and an outer annular surface, and at least one annular flange which extends radially inwardly from the inner surface of its wall.

[0011] The ring is mounted within the housing and comprises an annular wall having an inner annular surface and an outer annular surface, and at least one annular flange extending radially outwardly from the outer surface of its wall.

[0012] The flanges of the casing and the ring are axially supported on each other and can also be fixed to each other by fixing or centering elements which pass through orifices in these flanges. The axial support of the flanges makes it possible to create a seal between the casing and the ring and to prevent the passage of hot air flows through them.

[0013] In operation, due to relative movements and differential expansions, the flanges rub against each other, which causes wear on the casing. Since the support of the flanges is essentially linear, the casing flange undergoes very localized wear around its entire circumference. This wear causes a loss of sealing in this support zone. This loss of sealing makes it possible for air to be introduced from the turbine stream into the metal casing. In addition, this causes a loss of engine performance.

[0014] Similarly, the distribution of contact forces between the flanges leads to accelerating wear phenomena and generating local over-stresses in these flanges.

[0015] The present invention provides a solution to at least some of these problems, which is simple, effective and economical. Summary of the invention

[0016] To this end, the invention proposes a casing for an aircraft turbomachine, this casing being made of metal and having an annular shape around an axis, the casing comprising:

[0017] - an annular wall comprising an internal annular surface and a surface outer annular, and

[0018] - at least one annular flange extending radially inward from the internal surface of the wall,

[0019] characterized in that it further comprises:

[0020] - at least one sealing member permanently fixed on said at least one flange, this sealing member having an annular shape around the axis and projecting from the flange, this sealing member comprising an annular support part defining a radially oriented support plane, and an annular connecting part which is interposed axially between the support part and the flange and which ensures the connection of the sealing member to this flange, the connecting part having a capacity for deformation in axial compression which is greater than that of the support part.

[0021] The invention thus proposes to associate at least one sealing member with the flange of the casing. This sealing member is not a conventional seal. A seal is generally mounted between two elements to ensure sealing. Here, the sealing member is not mounted since it is permanently fixed to the flange of the casing. Furthermore, the sealing member comprises two parts having different axial compression deformation capacities. The support part of the member, which defines the support plane, and is able to come into contact with a sealing ring or turbine for example, is more rigid than the connecting part. The connecting part is therefore able to deform to absorb relative displacements, differential expansions and geometric defects, while the support part maintains a sealed support.In the above case of using a CMC turbine ring, there is less risk of frictional wear of the casing flanges and therefore less risk of loss of sealing between the turbine ring and the casing.

[0022] The invention applies to the context mentioned above, namely a turbine casing to which a turbine or sealing ring is attached, but applies generally to any metal casing comprising an annular support flange in the axial direction.

[0023] The casing according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another:

[0024] — said support part has a solid section or parts of solid section, and said connecting part has a hollow section or parts of hollow section; • said support part comprises wires or strands of solid section and said connecting part comprises wires or strands of hollow section, the wires or strands having an annular shape around the axis or being wound around the axis and being integral with each other to form a single-piece annular assembly; • the wires or strands are metallic and joined to each other by welding or brazing; • at least two wires or strands of the support part define said support plane; • the wires or strands of the support part have a cross-sectional diameter of between 0.2 and 2mm, and the wires or strands of the connecting part have a cross-section diameter of between 0.4 and 2mm; • the support part comprises at least one layer of wires or strands oriented radially, and the connecting part comprises several layers of wires or strands oriented radially and stacked axially; • at least part of the wires or strands are housed in an annular groove in the flange, this groove opening out in the axial direction; • said support part comprises a repetition of first annular patterns produced by additive manufacturing and said connecting part comprises a repetition of second annular patterns different from the first patterns and produced by additive manufacturing, the first and second patterns being integral with each other to form a single-piece annular assembly; • at least two first annular patterns of the support part define said support plane; • the first patterns have a semi-circular shape in section and define said support plane by their convex curved surfaces; • the second patterns have a polygonal shape in section; • the support part comprises at least one layer of first patterns oriented radially, and the connecting part comprises several layers of second patterns oriented radially and stacked axially; • said at least one sealing member has a generally tubular shape; • said at least one sealing member has a tri-shaped axial section angular and comprises a first wall which is oriented substantially radially and which forms said bearing part, and two second walls which are inclined relative to each other and which are connected respectively to internal and external annular edges of the first wall, these second walls being connected to the flange on the side opposite the first wall and forming said connecting part.

[0025] The present invention also relates to an aircraft turbine or turbomachine, comprising a casing as described above and a sealing ring mounted around the axis and inside the casing, this ring being made of ceramic matrix composite material and comprising:

[0026] - an annular wall comprising an internal annular surface and a surface outer annular, and

[0027] - at least one annular flange extending radially outwardly from the external surface of the wall,

[0028] said at least one flange of the sealing ring bearing on the sealing member of the casing in said bearing plane.

[0029] Advantageously, the flange of the ring comprises axial through orifices which are aligned with axial through orifices of the flange of the casing for mounting fixing or centering elements, these orifices being located on a circumference which is centered on the axis and which has a first diameter, and the sealing members being located on another circumference which is centered on the axis and which has a second diameter smaller than the first diameter. Brief description of the figures

[0030] Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the appended drawings in which:

[0031] [Fig-1] [Fig.l] is a partial schematic half-view in axial section of a turbomachine turbine;

[0032] [Fig.2] [Fig.2] is a schematic perspective view of a casing and a sealing ring of the turbine of [Fig.l];

[0033] [Fig.3] [Fig.3] is a very schematic half view in axial section of a casing according to the invention equipped with a sealing member according to a first embodiment of the invention;

[0034] [Fig.4] [Fig.4] is a very schematic half-view in axial section of a casing according to the invention equipped with a sealing member according to a second embodiment of the invention; and

[0035] [Fig.5] [Fig.5] is a very schematic half view in axial section of a casing according to the invention equipped with a sealing member according to a third embodiment of the invention. Detailed description of the invention

[0036] Generally speaking, in the present application, the terms “longitudinal” and “axial” describe the orientation of structural elements extending in the direction of a longitudinal axis. This longitudinal axis may be confused with an axis of rotation of a turbomachine engine. The term “radial” describes an orientation of structural elements extending in a direction perpendicular to the longitudinal axis. The terms “inner” and “outer”, and “internal” and “external” are used with reference to a positioning relative to the longitudinal axis. Thus, a structural element extending along the longitudinal axis comprises an inner face facing the longitudinal axis and an outer surface, opposite its inner surface.

[0037] By convention, in the present application, the terms “upstream” and “downstream” are defined in relation to the direction of circulation of a gas flow in the turbomachine.

[0038] A turbomachine conventionally comprises, from upstream to downstream, a fan, at least one compressor (for example a low pressure compressor and a compressor high pressure), a combustion chamber, and at least one turbine (e.g. a high pressure turbine and a low pressure turbine).

[0039] More particularly, [Fig.l] illustrates a part (such as a module) of a turbomachine 10 extending along a longitudinal axis X, and comprising, from upstream to downstream, a combustion chamber 1a, a high pressure (HP) turbine 1b and a low pressure (LP) turbine 1c. Each turbine stage 1b, 1c comprises an annular row of guide or fixed straightening vanes 20, 20' and a bladed wheel 3 arranged alternately in a known manner. The annular row of fixed vanes 20 of the HP turbine 1b forms a distributor 2. The wheel 3 (rotor) is rotatably mounted downstream of the distributor 2 in a sealing or turbine ring 4. The annular row of fixed vanes 20' of the LP turbine 1c forms another distributor 2'.

[0040] The turbine ring 4 comprises a plurality of ring sectors 40 arranged circumferentially end to end and surrounding the wheel 3. The turbine ring 4 is mounted inside a turbine casing 6 or an annular support 5 of this casing 6. This annular support 5 comprises at its internal periphery first and second annular radial flanges 52, 53, respectively upstream and downstream, which are connected to each other by an annular wall 51.

[0041] The ring sectors 40 comprise at their upstream and downstream ends first and second attachment flanges 42, 43 on, respectively, the first and second flanges 52, 53 of the annular support 5.

[0042] [Fig.2] shows further details of the ring sectors 40 and their attachment to the support 5.

[0043] Each ring sector 40 has a section substantially in the shape of the inverted Greek letter “Pi” (ji). Each ring sector 40 thus comprises an annular wall 41 and first and second radial attachment flanges 42, 43.

[0044] The annular wall 41 comprises an inner annular surface 41a and an outer annular surface 41b opposite each other. The inner surface 41a of the annular wall 41 may be coated with a layer of abradable material 44 to define a gas flow path in the turbine.

[0045] The first and second flanges 42, 43 extend outwardly from the external surface 41b and at a distance from the upstream and downstream ends 421a, 421b of the annular wall 41 of each ring sector 40. The first and second flanges 42, 43 extend over the entire width of the ring sector 40, i.e. over the entire arc of a circle described by the ring sector 40, or over the entire circumferential length of the ring sector 40.

[0046] As described previously, the annular support 5 of the turbine casing 6 comprises:

[0047] - a central annular wall 51, and

[0048] - a first annular flange 52 and a second annular flange 53, respectively upstream and downstream, the first and second flanges 52, 53 extending radially inwardly from an inner surface 51a of the wall 51.

[0049] The first flange 52 comprises a first free end 524 and an opposite second end 525 which is connected to the internal surface 51a of the wall 51.

[0050] The second flange 53 comprises a first portion 531, a second portion 532, and a third portion 533 between the first and second portions 531, 532. The first and third portions 531, 533 may form an inner periphery of the second flange 53, and the second portion 532 may form an outer periphery of the second flange 53.

[0051] The first portion 531 comprises a first free end 534 and the second portion 532 comprises a second end 535 connected to the internal face 51a of the wall 51.

[0052] The first portion 531 extends between the first end 534 and the third portion 533, and the second portion 532 extends between the third portion 533 and the second end 535.

[0053] In the example of [Fig.2], the internal periphery of the first portion 531 (in particular a radial annular face 536 of the first portion 531) is in axial support against the second attachment flange 43 of the turbine ring 4.

[0054] The first portion 531 and the third portion 533 have an increased thickness compared to that of the second portion 532 to provide increased rigidity to the second flange 53 compared to the upstream part comprising in particular the first flange 52, so as to reduce axial leaks from the ring in the case of rectilinear support.

[0055] With reference to [Fig. 2], the turbine further comprises first and second annular flanges 56, 57 which are removably fixed to the first flange 52 of the annular support 5. The first and second flanges 56, 57 are arranged upstream of the turbine ring 1 relative to the direction of flow of the gas flow in the turbine.

[0056] The first flange 56 is arranged downstream of the second flange 57. The first flange 56 is in a single piece while the second flange 57 can be sectorized into a plurality of annular sectors of second flange 57 or be in a single piece.

[0057] The first flange 56 has a first free end 564 and a second end 565 removably fixed to the annular support 5, and more particularly to the first clamp 52.

[0058] Furthermore, the first flange 52 has a first portion forming an inner periphery 561 and a second portion forming an outer periphery 562. The inner periphery 561 extends between the first end 564 and the outer periphery 562, and the outer periphery 562 extends between the inner periphery 561 and the second end 565.

[0059] When the ring is mounted, the internal periphery 561 of the first flange 56 (and in particular a radial annular face 566 of the first flange 56) is in axial support against the first attachment lug 42 of each of the ring sectors 40, and the external periphery 562 is in support against at least a part of the first flange 52.

[0060] The second flange 57 has a free first end 574 and a second end 575 opposite the first end 574 and in contact with the annular wall 51. The second end 575 of the second flange 57 is also removably fixed to the annular support 5, and more particularly to the first flange 52. The second flange 57 further comprises a first portion forming an internal periphery 571 and a second portion forming an external periphery 572. The internal periphery 571 extends between the first end 574 and the external periphery 572, and the external periphery 572 extends between the internal periphery 571 and the second end 575.

[0061] The first and second flanges 56, 57 are shaped to have the internal peripheries 561, 571 axially distant from each other and the external peripheries 562, 572 in contact, the two flanges 56, 57 being removably fixed to the first flange 52 using screws 82 and fixing nuts 83, the screws 82 passing through orifices 570, 560 and 520 provided respectively in the external peripheries 572 and 562 of the two flanges 56, 57 as well as in the first flange 52.

[0062] To hold the ring sectors 40, and therefore the turbine ring 4, in position with the annular support 5, two first axial pins 84 cooperate with the first attachment lug 42 and the first flange 56, and two second axial pins 86 cooperate with the second attachment lug 57 and the second flange 53.

[0063] For each corresponding ring sector 40, the internal periphery 561 of the first flange 56 comprises orifices for receiving the first two pins 84, and the third portion 533 of the second flange 53 comprises orifices configured to receive the two second pins 86.

[0064] For each ring sector 40, each of the first and second attachment tabs 42, 43 comprises orifices configured to receive the first pins 84 and the second pins 86.

[0065] Each ring sector 40 of the turbine ring 4 is made of ceramic matrix composite (CMC) material, while the first and second flanges 52, 53 of the annular support 5, the first and second flanges 56, 57 are made of metallic material. This configuration has several drawbacks mentioned above in the technical background, in particular a risk of generating wear by friction of the support 5 and in particular of its flanges 52, 53, in the bearing zones of these flanges on the flanges 42, 43 of the ring sectors 40. In the example shown in [Fig.2], a risk of wear exists for example in the encircled zone ZI, due to the support between the flanges 43, 53.

[0066] The invention makes it possible to remedy this problem thanks to the presence of at least one sealing member on the or each flange 52, 53 of the casing 5 or its support 6.

[0067] According to the invention, at least one sealing member is permanently fixed to the or each flange 52, 53, i.e. in a non-detachable manner.

[0068] Figures 3 to 5 illustrate different embodiments of the sealing member 100. In these figures, the elements already described in the above are designated by the same references.

[0069] This sealing member 100 preferably has an annular shape around the axis X and projects from the flange 52, 53. This sealing member 100 comprises an annular support part 100a defining a support plane PI oriented radially, that is to say perpendicular to the axis X, and an annular connecting part 100b which is interposed axially between the support part 100a and the flange 52, 53 and which ensures the connection of the sealing member 100 to this flange.

[0070] The connecting part 100b has a capacity for deformation in axial compression which is greater than that of the support part 100a, that is to say that in the event of force or stress applied to the member 100, it is the connecting part which will deform as a priority and absorb this force or stress. This makes it possible to absorb the relative displacements and geometric defects of the flange 42, 43 of the ring sector 40 and therefore to guarantee optimal sealing in this zone during operation.

[0071] In the embodiment of [Fig. 3], the support part 100a comprises wires or strands 102 of solid section and the connecting part 100b comprises wires or strands 104 of hollow section.

[0072] The wires or strands 102, 104 have an annular shape around the X axis or are wound around the X axis and are integral with each other to form a single-piece annular assembly.

[0073] The wires or strands 102, 104 are preferably metallic and secured to each other by welding or brazing.

[0074] At least two wires or strands 102 of the support part 100a define the support plane PI so as to multiply the number of surfaces or lines of contact with the ring sectors 40.

[0075] The wires or strands 102 of the support part 100a may have a cross-sectional diameter of between 0.2 and 2 mm.

[0076] The wires or strands 104 of the connecting part 100b may have a cross-sectional diameter of between 0.4 and 2 mm.

[0077] The support part 100a comprises at least one layer C1 of wires or strands 102 radially oriented, as in the example shown.

[0078] The connecting part may comprise several layers C2, C3, C4 of wires or strands 104 which are individually oriented radially and which are stacked axially on top of each other.

[0079] At least a portion of the wires or strands 102, 104 are housed in an annular groove 106 of the flange 52, 53, this groove 106 opening out in the axial direction. The wires or strands 102, 103 may be held at the bottom of this groove 106 by welding or brazing.

[0080] This sealing member 100 with wires or strands 102, 104 makes it possible in particular: - to distribute the mechanical support load on the ring sectors 40 over several generatrices; - to reduce, or even eliminate, the wear of the metal flanges 52, 53 serving as support for the ring sectors 40; etc.

[0081] In the embodiment of [Fig.4], the support portion 100a comprises a repetition of first annular patterns 108 produced by additive manufacturing.

[0082] The connecting part 100b comprises a repetition of second annular patterns 110 different from the first patterns 108 and produced by additive manufacturing.

[0083] The first and second patterns 108, 110 are secured to each other to form a single-piece annular assembly. This securing and the securing of the member 100 to the flange 52, 53 may result directly from the additive manufacturing of the member on the flange 52, 53. Alternatively, the member 100 could be secured to the flange 52, 53 by welding or brazing.

[0084] At least two first annular patterns 108 of the support part 100a define the support plane PI so as to multiply the number of surfaces or lines of contact with the ring sectors 42, 43.

[0085] The first patterns 108 preferably have a semi-circular shape in section and define the support plane PI by their convex curved surfaces, as in the example shown. These first patterns 108 may be solid in section. The support portion 100a preferably comprises at least one layer C1 of first patterns 108 oriented radially.

[0086] The second patterns 110 may have a polygonal shape in section.

[0087] These second patterns 110 may be hollow in section.

[0088] The connecting part 100b may comprise several layers C2, C3, C4 of second patterns 110 which are individually oriented radially and which are stacked axially on top of each other.

[0089] This sealing member 100 with optimized patterns 108, 110 makes it possible in particular: - to distribute the mechanical support load on the ring sectors 40 over several generatrices; - to reduce, or even eliminate, the wear of the metal flanges 52, 53 serving as support for the ring sectors 40; etc.

[0090] In the embodiment of [Fig.5], the sealing member 100 has a generally tubular shape.

[0091] In the example shown, this sealing member 100 has a triangular shape in axial section.

[0092] The sealing member 100 comprises a first wall 112 which is oriented substantially radially and which forms the bearing portion 100a. The wall 112 is solid in section and therefore the bearing portion 100a is solid in section.

[0093] The sealing member 100 further comprises two second walls 114, 116 which are inclined relative to each other and which are connected respectively to internal and external annular edges of the first wall 112.

[0094] The second walls 114, 116 are connected to the flange 52, 53 on the side opposite the first wall 112 and form the aforementioned connecting part 100b. This connecting part 100b is hollow.

[0095] This sealing member 100 with simplified shape makes it possible in particular: - to distribute the mechanical support load over a large surface; - to reduce, or even eliminate, the wear of the metal flanges 52, 53 serving as support for the ring sectors 40; etc.

[0096] The present invention also relates to a turbine or a turbomachine 10, such as that illustrated in [Fig.l] or 2, in which the flange 42, 43 of the sealing ring 4 comprises axial through-orifices which are aligned with axial through-orifices of the flange 52, 53 of the casing 5, 6 for the mounting of fixing or centering elements, such as the screws 82 and the pins 86 mentioned above.

[0097] These orifices are located on a circumference centered on the X axis and which has a first diameter, and the sealing members 100 are preferably located on another circumference which is centered on the X axis and which has a second diameter smaller than this first diameter. The sealing member 100 thus prevents the radial passage of hot gases from the turbine stream to these fixing or centering elements.

[0098] The aim of the invention is to better distribute the forces over the height or radial dimension of the flange 42, 43 of the CMC ring 4 and to establish a stepped or surface seal.

[0099] Each sealing member 100 makes it possible to ensure progressive support of the casing support, by absorbing the relative geometric variations of the parts facing each other, during assembly and in operation.

[0100] The solution is applicable on each bearing face of the flanges 52, 53 of the casing 5 or of its support 6, whether they are continuous over 360° or circumferentially split. It is therefore understood that the sealing member 100 can be continuous over 360° or circumferentially split. conferentially, for example at the level of the slots of the flanges 52, 53 of the casing 5, these slots being able to correspond to the circumferential spaces between the ring sectors 40.

Claims

Claims

1. Casing (5, 6) for an aircraft turbomachine (10), this casing (5, 6) being made of metal and having an annular shape around an axis (A), the casing (5, 6) comprising: - an annular wall (51) having an internal annular surface (51a) and an external annular surface, and - at least one annular flange (52, 53) extending radially inwards from the internal surface (51a) of the wall (51), characterized in that it further comprises: - at least one sealing member (100) permanently fixed on said at least one flange (52, 53), this sealing member (100) having an annular shape around the axis (X) and projecting from the flange (52, 53), this sealing member (100) comprising an annular support portion (100a) defining a radially oriented support plane (PI), and an annular connecting part (100b) which is axially interposed between the support part (100a) and the flange (52,53) and which ensures the connection of the sealing member (100) to this flange, the connection part (100b) having a capacity for deformation in axial compression which is greater than that of the support part (100a).,

2. Casing (5, 6) according to claim 1, wherein said support portion (100a) comprises wires or strands (102) of solid section and said connecting portion (100b) comprises wires or strands (104) of hollow section, the wires or strands (102, 104) having an annular shape around the axis (X) or being wound around the axis (X) and being integral with each other to form a single-piece annular assembly.

3. Housing (5, 6) according to claim 2, in which the wires or strands (102, 104) are metallic and secured to each other by welding or brazing.

4. Housing (5, 6) according to claim 2 or 3, wherein at least two wires or strands (102) of the support part (100a) define said support plane (PI).

5. Housing (5, 6) according to one of claims 2 to 4, in which the wires or strands (102) of the support part (100a) have a cross-sectional diameter of between 0.2 and 2 mm, and the wires or strands (104) of the connecting part (100b) have a cross-sectional diameter of between 0.4 and 2 mm.

6. Housing (5, 6) according to one of claims 2 to 5, in which the support part (100a) comprises at least one layer (Cl) of wires or strands (102) radially oriented, and the connecting part (100b) comprises several layers (C2, C3, C4) of wires or strands (104) radially oriented and axially stacked.

7. Housing (5, 6) according to one of claims 2 to 6, in which at least a portion of the wires or strands (102, 104) are housed in an annular groove (106) of the flange, this groove (106) opening out in the axial direction.

8. Casing (5, 6) according to claim 1, wherein said support portion (100a) comprises a repetition of first annular patterns (108) produced by additive manufacturing and said connecting portion (100b) comprises a repetition of second annular patterns (110) different from the first patterns (108) and produced by additive manufacturing, the first and second patterns (108, 110) being integral with each other to form a single-piece annular assembly.

9. Housing (5, 6) according to claim 8, wherein at least two first annular patterns (108) of the bearing portion (100a) define said bearing plane (PI).

10. Housing (5, 6) according to claim 9, in which the first patterns (108) have a semi-circular shape in section and define said support plane (PI) by their convex curved surfaces.

11. A housing (5, 6) according to claim 9 or 10, wherein the second patterns (110) have a polygonal shape in section.

12. Casing (5, 6) according to one of claims 9 to 11, in which the support part (100a) comprises at least one layer (Cl) of first patterns (108) oriented radially, and the connecting part (100b) comprises several layers (C2, C3, C4) of second patterns (110) oriented radially and stacked axially.

13. Housing (5, 6) according to claim 1, wherein said at least one sealing member (100) has a generally tubular shape.

14. Casing (5, 6) according to claim 13, wherein said at least one sealing member (100) has a triangular shape in axial section and comprises a first wall (112) which is oriented substantially radially and which forms said bearing portion (100a), and two second walls (112, 114) which are inclined relative to each other and which are connected respectively to internal and external annular edges of the first wall (110), these second walls (114, 114) being connected to the flange (52, 54) on the side opposite the first wall (110) and forming said connecting portion (100b).

15. Aircraft turbine or turbomachine (10), comprising a casing (5, 6) according to one of the preceding claims and a sealing ring (4) mounted around the axis (X) and inside the casing (5, 6), this ring (4) being made of ceramic matrix composite material and comprising: - an annular wall (41) comprising an internal annular surface (41a) and an external annular surface (41b), and - at least one annular flange (42, 43) extending radially outwards from the external surface (41b) of the wall (41), said at least one flange (42, 43) of the sealing ring (4) bearing on the sealing member (100) of the casing (5, 6) in said bearing plane (PI).

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