Upstream detachable turbine seal ring

Abstract

A turbine for a turbomachine comprises an annular casing (1), an upstream ring support (3) and a downstream ring support (4) configured to extend around and radially face a blade assembly (6) of a turbine rotor, the supports being mounted against a radially inner surface of the casing (1), and a sealing ring (2) configured to be disposed radially between the blade assembly (6) and the housing (1) and mounted against the upstream support and the downstream support, the sealing ring (2) having a maximum radius with respect to a main axis (X) of the turbine, the housing (1) is dimensioned such that the maximum radius of the sealing ring (2) is strictly smaller than the radius of the upstream end of the housing (1) in order to allow the sealing ring (2) and the upstream ring support (3) to be mounted against the downstream ring support (4) by means of axial insertion.

Description

Technical Field

[0001] The present disclosure relates to a sealing ring for a turbine of a turbine engine, and more particularly to a sealing ring for a turbine that can be disassembled from the upstream. Background Art

[0002] Maintenance limitations of turbines in turbine engines are well known and require access to components inside the turbine.

[0003] For example, low-pressure turbine blades are often difficult to access for maintenance operations.

[0004] To facilitate maintenance and thus reduce operating costs, turbine engines are provided with sealing rings that can be disassembled from the upstream.

[0005] However, the possibility of disassembling the sealing ring from the upstream usually impairs the sealing ability of the sealing ring, thereby increasing fuel consumption. Summary of the Invention

[0006] The present disclosure aims to provide a turbine engine designed to address the above problems.

[0007] To this end, the present disclosure relates to a turbine for a turbine engine, which has a main axis and includes a housing (usually an annular housing), an upstream ring support, a downstream ring support, and a sealing ring configured to extend around a blade assembly of a turbine rotor and face the blade assembly radially, wherein:

[0008] The upstream ring support and the downstream ring support are mounted against the radial inner surface of the housing, and the upstream ring support and the downstream ring support have an upstream end and a downstream end.

[0009] The sealing ring is configured to be radially disposed between the blade assembly and the housing and is mounted against the upstream ring support and the downstream ring support.

[0010] The sealing ring has a maximum radius relative to the main axis, and the housing is sized such that the maximum radius of the sealing ring is strictly less than the radius of the upstream end of the housing, so as to allow the sealing ring and the upstream ring support to be mounted against the downstream ring support by axial insertion.

[0011] In the present disclosure, the terms "axial", "radial", "circumferential", "inner", "outer" and their derivatives are defined relative to the main axis of the turbine engine; finally, the terms "upstream", "downstream", "front" and "rear" are defined relative to the main axis along the general direction of fluid circulation inside the turbine engine. "Axially, radially or circumferentially extending" respectively means "extending along a direction having a non-zero component in the axial, radial or circumferential direction". The circumferential direction is perpendicular to the axial direction and the radial direction. The main axis of the turbine engine corresponds to the rotation axis of the turbine engine.

[0012] In some embodiments, the upstream ring support is circumferential, preferably 360° around. Preferably, the upstream ring support is continuously installed against the radial inner surface of the housing along the circumference.

[0013] In some embodiments, the downstream ring support is circumferential, preferably 360° around. Preferably, the downstream ring support is segmented.

[0014] The upstream ring support and the downstream ring support respectively refer to the upstream support and the downstream support.

[0015] This dimensional design of the sealing ring and the housing enables the removal of the sealing ring by translating upstream along the main axis after the upstream ring support is removed, without being hindered by the housing.

[0016] In particular, it can be installed from the front without tilting, thus achieving more accurate and faster installation and reducing the risk of part damage.

[0017] Of course, unless otherwise specified, any described features related to the disassembly operation also apply to the installation operation in the reverse order, and vice versa.

[0018] Compared with a turbine where the sealing ring can only be removed from the downstream, removing the sealing ring from the upstream thus reduces maintenance time and cost.

[0019] The support of the sealing ring on the support ensures the centering of the sealing ring, thereby reducing the relative wear of the parts and being compatible with the removal of the sealing ring from the upstream.

[0020] According to an example, the support of the sealing ring on the upstream ring support is a radial support. According to an example, the support of the sealing ring on the downstream ring support is a radial support.

[0021] A radial support means supporting on a surface where the normal of the surface has a non - zero radial component.

[0022] According to an example, the radial support has a positive component or zero component along the main axis in the upstream direction, thus further facilitating removal from the upstream.

[0023] According to an example, as a supplement or alternative, the sealing ring is axially supported on the upstream ring support. According to an example, the sealing ring is axially supported on the downstream ring support.

[0024] An axial support means supporting on a surface where the normal of the surface has a non - zero axial component.

[0025] The axial support can ensure that it is axially held on the upstream ring support.

[0026] In some embodiments, the turbine includes at least one seal disposed between the downstream ring support and the radially protruding portion.

[0027] The seal between the downstream ring support and the radially protruding portion ensures sealing even if relative displacements are caused by differences in thermal expansion within the turbine, particularly between the sealing ring and the downstream ring support, and these displacements can be compensated for by deformation of the seal. The differences in thermal expansion are caused by temperature deviations between the ring and the downstream ring support and different material coefficients of thermal expansion.

[0028] According to one example, the seal is an axial seal, that is, it extends axially between two contact surfaces.

[0029] Using an axial seal is compatible with centering by the sealing ring and the downstream ring support, such that the relative axial displacement between the sealing ring and the downstream ring support is restricted, thereby reducing the shear force applied to the seal and extending its service life. More notably, using an axial seal at the radial support between the downstream ring support and the sealing ring can enhance the sealing performance, and since the support direction between the downstream ring support and the sealing ring forms an angle of nearly 90° with the seal extension direction, the shear force applied to the seal is also significantly reduced.

[0030] In some embodiments, the seal is in direct contact with the downstream ring support and the radially protruding portion.

[0031] According to one example, the seal is segmented. If at least one of the sealing ring and the downstream ring support is segmented, the seal is also segmented similarly to the component, that is, it includes multiple segments / parts at the same circumferential positions as the respective segments / parts of the component.

[0032] Each segment / part of the segmented seal can move and deform more independently than a non-segmented seal, thereby ensuring better sealing performance.

[0033] According to one example, the seal is an Omega seal. An Omega seal refers to a seal whose cross-sectional shape resembles the Omega symbol (Ω). The cross-section of an Omega seal can have an open profile or a closed profile. An Omega seal can also refer to an accordion-shaped seal, that is, formed by a series of consecutive folds in alternating directions, equivalent to a combination of multiple Omega seals with open profiles.

[0034] Omega seals, particularly accordion-shaped seals, can maintain sealing within a wide range of deformations while ensuring a satisfactory degree of sealing.

[0035] In some embodiments, the housing is a low-pressure turbine housing.

[0036] For a low-pressure turbine casing, the possibility of disassembly from the upstream is particularly desirable for ease of maintenance operations.

[0037] In some embodiments, the blade assembly comprises a ceramic matrix composite (CMC). CMC materials generally include fiber reinforcement within at least a portion of a ceramic matrix.

[0038] Using ceramic matrix composites allows the blade assembly to withstand higher temperatures than blade assemblies made of metallic materials, thereby reducing the intake air volume taken from the high-pressure compressor required to cool the blade assembly. This can improve the specific fuel consumption of the turbine and enable the turbine to operate at higher temperatures, thereby increasing the efficiency of the turbine. Additionally, the density of ceramic matrix composites is lower than that of metallic materials, which can provide an advantage in weight / mass, thereby reducing the fuel consumption of the turbine.

[0039] Compared to blade assemblies made of metallic materials, blade assemblies made of CMC materials are more susceptible to FOD (foreign object damage) or DOD (damage from internal objects), which typically occur inside the turbine. Therefore, an upstream mounting method is more conducive to maintenance, which is particularly desirable in the case of using CMC blade assemblies.

[0040] In some embodiments, the seal ring is segmented / divided into multiple parts.

[0041] In some embodiments, at least one of the upstream ring support and the downstream ring support is segmented / divided into multiple parts.

[0042] Segmented / divided into multiple parts means being composed of segments / parts connected to each other. In this example, segmented / divided into multiple parts means being segmented / divided into multiple parts along the circumferential direction around the main axis, that is, being composed of multiple segments / parts extending circumferentially and connected to each other.

[0043] A segmented / divided seal ring is less susceptible to thermal expansion than a non-segmented / divided seal ring, thereby minimizing the relative displacement between the seal ring and other parts inside the turbine during the service life of the turbine. Therefore, it is beneficial to control the end face clearance of the blade assembly relative to the seal ring and ensure good thermal performance and seal retention of the turbine.

[0044] Since one (or more) support is also segmented / divided into multiple parts, these supports are not easily affected by thermal expansion, thereby further improving the control of the end clearance of the blade assembly. Due to the reduction in thermal expansion, the displacement also decreases, thereby reducing the deformation amplitude applied to the intermediate member (such as a seal), thereby reducing its fatigue damage.

[0045] In some embodiments, the turbine includes at least one locking member configured to hold together the downstream end of the sealing ring and the downstream ring support. According to one example, the locking member is C-shaped and is configured such that the downstream end of the sealing ring and the downstream ring support are held in contact within the C-shape.

[0046] In some embodiments, the turbine includes at least one locking member configured to hold together the upstream end of the sealing ring and the upstream ring support. According to one example, the locking member is C-shaped and is configured such that the upstream end of the sealing ring and the upstream ring support are held in contact within the C-shape.

[0047] The locking member ensures the downstream and / or upstream centering of the sealing ring, thereby maintaining it in place within the turbine.

[0048] In some embodiments, the locking member is a clip.

[0049] Such a locking member enables stable locking and is easy to disassemble prior to maintenance operations on the blade assembly.

[0050] In some embodiments, the sealing ring includes a radially protruding portion, and the maximum radius of the sealing ring is equal to the maximum radius of the radially protruding portion from the main axis, that is, the distance from the main axis to the position where the radially protruding portion is farthest from the main axis.

[0051] In other words, the sealing ring includes a radially protruding portion, and the maximum radius of the sealing ring is measured on the radially protruding portion.

[0052] In some embodiments, at least one sealing metal sheet is provided between the seal and the downstream ring support and / or between the seal and the radially protruding portion.

[0053] The metal sheet ensures good contact with the seal, thereby ensuring the sealing performance.

[0054] According to one example, the metal sheet is a circumferential / hoop metal sheet. The circumferential metal sheet provides a larger bearing surface for the seal, thereby improving the efficiency of the seal and reducing seal wear.

[0055] According to one example, the metal sheet is a circumferential metal sheet that is not divided into segments / parts. For example, the metal sheet is constant / identical around the main axis.

[0056] In the case where the sealing ring is divided into segments / parts and the metal sheet is not divided into segments / parts, the thermo-mechanical properties of the segmented / segmented sealing ring are retained without reducing the sealing performance ensured by the seal.

[0057] According to one example, the metal sheet is detachably mounted on the radially protruding portion, for example, the metal sheet is clamped on the radially protruding portion.

[0058] According to one example, the metal sheet is in direct contact with one of the seal, the downstream ring support, and the radially protruding portion.

[0059] By extension, the measurement of the maximum cross-section of the seal ring (and thus also the measurement of the radially protruding portion) includes the metal sheet mounted on the seal ring.

[0060] In some embodiments, the turbine includes a metal sheet mounted between the seal and the downstream ring support.

[0061] The metal sheet between the seal and the front ring support ensures downstream centering through the downstream ring support.

[0062] In some embodiments, at least one of the downstream end of the seal ring and the downstream end of the downstream ring support is received in the housing of the outer platform of the downstream distributor. The downstream distributor refers, for example, to a distributor located downstream of the seal ring.

[0063] In some embodiments, the housing is a groove, and at least one end is axially inserted into the groove.

[0064] The present invention also relates to a turbine including a turbine according to the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0065] Other features and advantages of the objectives of the present disclosure will become apparent from the following description of embodiments given as non-limiting examples with reference to the accompanying drawings.

[0066] Figure 1 Figure 1 is a half-sectional view of the turbine.

[0067] Figure 2 Figure 2 is a schematic cross-sectional view of the main axis including a low-pressure turbine according to the first embodiment.

[0068] Figure 3 Figure 3 is a schematic cross-sectional view of the main axis including a low-pressure turbine according to the second embodiment.

[0069] Figure 4 Figure 4 is a schematic cross-sectional view of the main axis including a low-pressure turbine according to the third embodiment.

[0070] Figure 5 Figure 5 is a schematic cross-sectional view of the main axis including a low-pressure turbine according to the fourth embodiment. DETAILED DESCRIPTION ​​​​​​​​​​

[0071] Figure 1 Shows a longitudinal half-section view of the turbine 101 along a plane passing through its main axis A1 - A1. The turbine 101 is a dual-rotor turbofan turbine, but other turbines can also be equipped with a turbine according to an embodiment.

[0072] The turbine 101 includes, from upstream to downstream according to the air flow cycle, a fan 102, a low-pressure compressor 103 (also called a booster), a high-pressure compressor 104, a combustion chamber 105, a high-pressure turbine 106, and a low-pressure turbine 107. These different elements are installed within the nacelle 120 so as to obtain a propulsion assembly including the nacelle 120 and the turbine 101.

[0073] Downstream of the fan 102, the air flow is divided into a first air flow portion (also called the primary flow) F1 passing through the low-pressure compressor 103, and a second air flow portion (also called the secondary flow) F2 flowing in the bypass around the low-pressure compressor 103.

[0074] The fan 102 and the low-pressure compressor 103 are driven by the low-pressure turbine 107 via the low-pressure main shaft SL, while the high-pressure compressor 104 is driven by the high-pressure turbine 106 via the high-pressure main shaft SH. The low-pressure main shaft SL generally extends inside the high-pressure main shaft SH.

[0075] The structure of the low-pressure turbine 107 will be described in more detail in conjunction with Figure 2 and the embodiments will be described as Figures 3 to 5 variations of Figure 2

[0076] In Figures 2 to 5 the upstream direction is denoted by the reference mark AM and the downstream direction is denoted by the reference mark AV.

[0077] As Figure 2 shown, the low-pressure turbine 107 includes a casing 1, an upstream ring support 3 (or upstream support 3), a downstream ring support 4 (or downstream support 4), a sealing ring 2, and a blade assembly 6.

[0078] The casing 1 is an annular casing having an inner surface.

[0079] The upstream support 3 and the downstream support 4 are mounted against the inner surface of the annular casing 1, thereby defining a casing section.

[0080] The upstream support 3 and the downstream support 4 contact along a surface having a radial normal, thereby facilitating the installation and disassembly of the parts relative to each other.

[0081] The upstream support 3 may have a radial protrusion abutting the upstream face of the casing 1 so as to facilitate the correct relative positioning of the different components of the casing 1 during installation.

[0082] The blade assembly 6 of the rotor of the turbine 107 is disposed within the housing 1 to extract mechanical power from the combustion gases from the combustion chamber via the high-pressure turbine.

[0083] The blade assembly 6 is made of CMC material.

[0084] The sealing ring 2 is disposed radially between the blade assembly 6 and the housing 1.

[0085] A wear-resistant element 11 can be disposed between the sealing ring 2 and the blade assembly 6, which can ensure better control of the tolerances of the blade assembly 6, thereby limiting the leakage rate bypassing / flowing past the blade assembly 6.

[0086] The sealing ring 2 is mounted between the upstream support member 3 and the downstream support member 4 and abuts against the upstream support member 3 and the downstream support member 4.

[0087] The sealing ring 2 has a radially outermost end, the distance of which from the main axis is R1.

[0088] For example, the sealing ring 2 includes a radially protruding portion 2A, one end of which is located at the radially outermost position of the sealing ring 2, and the distance from the main axis is R1.

[0089] In other words, the sealing ring 2 is contained within a virtual rotating cylinder centered on the main axis, which extends axially together with the sealing ring 2, the radius being equal to the above-mentioned distance R1, and the rotating cylinder is tangent to the sealing ring 2 at the radially outermost position (and tangent to the radially protruding portion 2A when appropriate).

[0090] Therefore, the housing 1 can be virtually divided into an upstream half and a downstream half of the housing 1, where the upstream half of the housing 1 corresponds to the half of the housing 1 located upstream of the radially outermost end of the sealing ring 2, and the downstream half of the housing 1 corresponds to the half of the housing 1 located downstream of the radially outermost end of the sealing ring 2.

[0091] The radially innermost position of the upstream half of the housing 1 is at a distance R2 from the main axis.

[0092] In other words, within the upstream half of the housing 1, there is a virtual rotating cylinder centered on the main axis with a radius equal to the distance R2, which extends axially together with the upstream half of the housing 1, the radius being equal to the distance R2, and the rotating cylinder is tangent to the upstream half of the housing 1 at the radially innermost position of the upstream half of the housing 1.

[0093] The distances R1 and R2 are set such that R1 < R2 (“R1 is strictly less than R2”).

[0094] Thus, the turbine is dimensioned such that: upstream of the main axis, along the main axis, the maximum section of the sealing ring 2 is strictly included within any section of the housing 1.

[0095] In other words, a virtual infinite semi-cylinder containing the sealing ring 2 can be constructed, which extends infinitely upstream without intersecting or forming a tangent with the upstream half of the housing.

[0096] In other words, the turbine is dimensioned such that: the maximum radius R1 of the sealing ring 2 is strictly less than the radius R2 of the upstream end of the housing 1, which corresponds to the upstream half of the housing 1.

[0097] In this way, the sealing ring 2 can be translated upstream without the sealing ring 2 coming into contact with the upstream part of the housing 1.

[0098] This also makes it possible to ensure the installation by means of the axial insertion of the sealing ring 2 and the upstream ring support 3 relative to the downstream ring support 4.

[0099] Then the sealing ring 2 can be removed from the upstream, and it can be removed from the interior of the housing 1 by axial translation upstream, and various devices connected to other components of the turbine (to be described below) are previously disassembled and / or separated.

[0100] The upstream support 3 extends radially, and its inner surface contacts the outer surface of the sealing ring 2.

[0101] The contact surface between the inner surface of the upstream support 3 and the outer surface of the sealing ring 2 can be provided between the two corresponding ends of the upstream support 3 and the sealing ring 2. This contact surface can be a radial contact surface.

[0102] A radial surface is a surface whose normal has a non-zero radial component.

[0103] These two ends can be held in contact with each other by a locking member 8.

[0104] The locking member 8 can be, for example, a C-shaped clip, that is to say, a clip configured to surround the two corresponding ends of the sealing ring 2 and the upstream support 3 to keep them in contact with each other / abutting against each other.

[0105] The contact between the inner surface of the upstream support 3 and the outer surface of the sealing ring 2 can be achieved by means of a seal 9.

[0106] The downstream support 4 extends radially, and the inner surface of the housing 1 contacts the outer surface of the downstream support 4.

[0107] The contact surface between the inner surface of the housing 1 and the outer surface of the downstream support 4 can be provided between the two corresponding ends of the housing 1 and the downstream support 4. This contact surface can be a radial contact surface.

[0108] The two ends can be held against each other by a locking member 8 (such as a C-clamp).

[0109] The contact between the inner surface of the housing 1 and the outer surface of the downstream support 4 can be achieved by means of a seal 9.

[0110] The contact between the locking member 8 and the surfaces of the two ends held against each other by the locking member 8 can be achieved by a sealing piece 12.

[0111] The downstream end of the sealing ring 2 contacts the end of the downstream support 4. The downstream end of the sealing ring 2 has a radial bearing surface located on the end of the downstream support 4.

[0112] The radial surface between the sealing ring 2 and the downstream support 4 can be purely radial, that is, having a radial normal, or having a certain inclination such that the surface is away from the main axis in the upstream direction. In this way, the contact / abutment with the radial surface does not prevent the removal of the sealing ring 2 from the upstream.

[0113] As Figure 2 shown, the turbine includes a distributor 7, which can have a first end inserted into the opening of the housing 1 and a second end in the shape of a C, which is arranged to clamp the downstream end of the sealing ring 2 and the end of the downstream support 4 so that they contact / abut each other.

[0114] The second end of the distributor 7 can include only one branch, which only contacts the inner surface of the downstream end of the sealing ring 2, as Figure 4 and Figure 5 shown in the embodiments, or only contacts the inner surface of the end of the downstream support 4.

[0115] The second end of the distributor 7 can include only one branch that contacts a radial inner surface - for example, the radial inner surface of the end of the downstream support 4 as shown in the embodiments of Figure 3 or the radial inner surface of the end of the sealing ring 2.

[0116] The end of the downstream support 4 can clamp the sealing ring 2, as Figure 3 shown. According to an example, the end of the downstream support 4 clamps the sealing ring 2 so as not to prevent removal from the upstream.

[0117] A seal 5 is provided between the downstream support 4 and the radially protruding portion 2A.

[0118] According to an example, the seal 5 is provided between the axial surface of the downstream support 4 and the axial surface of the radially protruding portion 2A.

[0119] The axial surface refers to a surface whose normal has a non-zero axial component.

[0120] According to one example, as a supplement or alternative, a seal 5 is provided between the radial surface of the downstream support 4 and the radial surface of the radially protruding portion 2A. This additional contact allows for better fixing in place.

[0121] The seal 5 can be, for example, an Omega seal, in particular an accordion-shaped seal.

[0122] The seal 5 can be in direct contact with the corresponding axial surfaces of the radially protruding portion 2A and the downstream support 4.

[0123] The seal 5 can also be in contact with these surfaces via a metal sheet.

[0124] The seal 5 can be in direct contact with at least one of the radial surfaces of the downstream support 4 and the radially protruding portion 2A, or in contact via a metal sheet.

[0125] A metal sheet 10 can be provided against the radially protruding portion 2A. The metal sheet 10 of the radially protruding portion 2A can, for example, surround the radially protruding portion 2A like a C-shaped clip in order to be fixed in place relative to the radially protruding portion 2A.

[0126] As a supplement or alternative, a metal sheet 10 can be provided against the downstream support 4. The metal sheet 10 of the downstream support 4 can, for example, surround a part of the downstream support 4 like a C-shaped clip in order to be fixed in place relative to the downstream support 4.

[0127] The metal sheet 10 can be circumferential, for example a non-segmented / non-divided-into-multiple-parts circumferential metal sheet, and thus improves the seal between the downstream support 4 and the seal ring 2 by improving the seal between the seal 5 and the radially protruding portion 2A and / or by improving the seal between the seal 5 and the downstream support 4.

[0128] In the case where the metal sheet 10 surrounds the radially protruding portion 2A, as an alternative to previously defining the distance R1 only relative to the seal ring 2, the distance R1 can be defined relative to the assembly of the seal ring 2 and the metal sheet mounted on the seal ring 2.

[0129] In other words, the distance R1 can be defined at the radially outermost position of the assembly formed by the seal ring 2 and the metal sheet 10 mounted on the seal ring.

[0130] In this way, the seal ring 2 and the metal sheet 10 can be disassembled from upstream of the assembly.

[0131] It can be understood that the turbine 107 may not have one or two metal sheets 10 provided between the downstream support 4 and the seal ring 2 and between the seal 5 and the radially protruding portion 2A.

[0132] For example, in Figure 3In the embodiment, no metal sheet is provided between the turbine 107, the seal 5 and the radially protruding portion 2A.

[0133] In Figure 4 and Figure 5 the embodiment, no metal sheet is provided between the downstream support member 4, the seal ring 2, the seal 5 and the radially protruding portion 2A of the turbine 107.

[0134] The turbine 107 may also not be provided with a seal between the seal ring 2 and the downstream support member 3.

[0135] In order to ensure the seal between the seal ring 2 and the downstream support member 4 in the absence of the seal 5, the radially protruding portion 2A may, for example, have a first radially contacting surface in contact with the radially inner portion of the downstream support member 4 and a second radially contacting surface in contact with the radially outer portion of the downstream support member 4.

[0136] Thus, the radially protruding portion 2A can clamp the downstream support member 4 so as to apply a force to the downstream support member 4, thereby ensuring the seal between the downstream support member 4 and the seal ring 2.

[0137] The downstream support member 4 and / or the seal ring 2 may be partitioned. Where applicable, the number of parts / sections forming the downstream support member 4 is strictly less than the number of parts / sections forming the seal ring 2.

[0138] Although the present invention has been described with reference to specific embodiments, it will be apparent that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, the various features of the respective illustrated / described embodiments can be combined into additional embodiments. Accordingly, the specification and drawings are to be regarded as illustrative rather than restrictive.

Claims

1. A turbine for a turbine engine, the turbine having a main axis (X) and comprising an annular casing (1), an upstream ring support (3), a downstream ring support (4) and a sealing ring (2), the sealing ring (2) being configured to extend around a blade assembly (6) of a rotor of the turbine and to face the blade assembly radially, wherein the upstream ring support (3) and the downstream ring support (4) are mounted against a radial inner surface of the casing (1), the upstream ring support (3) and the downstream ring support (4) having an upstream end and a downstream end, the sealing ring (2) is configured to be radially disposed between the blade assembly (6) and the casing (1) and to be mounted against the upstream ring support (3) and the downstream ring support (4), the sealing ring (2) having a maximum radius relative to the main axis (X), and the casing (1) is dimensioned such that the maximum radius of the sealing ring (2) is strictly less than the radius of the upstream end of the casing (1) so as to allow the sealing ring (2) and the upstream ring support (3) to be mounted against the downstream ring support (4) by axial insertion, the turbine engine comprises at least one C-shaped locking member (8) configured to keep an upstream end of the sealing ring (2) in contact with the upstream ring support (3) inside the C-shape, and / or comprises at least one C-shaped locking member (8) configured to keep a downstream end of the sealing ring (2) in contact with the downstream ring support (4) inside the C-shape.

2. The turbine for a turbine engine according to claim 1, wherein, The seal ring (2) includes a radially protruding portion (2A), and the maximum radius of the seal ring (2) is equal to the maximum radius of the radially protruding portion (2A).

3. The turbine for a turbine engine according to claim 2, comprising at least one seal (5) disposed between the downstream ring support (4) and the radially protruding portion (2A).

4. The turbine for a turbine engine according to claim 3, wherein, The at least one seal (5) extends axially.

5. The turbine for a turbine engine according to claim 3 or 4, comprising at least one sealing metal sheet (10), the sealing metal sheet (10) being disposed between the seal (5) and the downstream ring support (4) and / or between the seal (5) and the radially protruding portion (2A).

6. The turbine for a turbine engine according to any one of claims 1 to 5, wherein, The housing (1) is a low-pressure turbine housing (1).

7. The turbine according to any one of claims 1 to 6, wherein, At least one of the downstream end of the seal ring (2) and the downstream end of the downstream ring support (4) is received in the housing of the outer platform of the downstream distributor.

8. The turbine according to claim 7, wherein, The housing is a groove, and at least one of the downstream end of the seal ring (2) and the downstream end of the downstream ring support (4) is axially inserted into the groove.

9. A turbine, comprising a turbine according to any one of the preceding claims.

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