Improved turbine ring assembly

Abstract

The present invention relates to a turbine ring assembly (10) extending around a longitudinal axis (X-X'), the turbine ring assembly comprising: a plurality of annular corner sectors (16) made of a ceramic matrix composite material arranged circumferentially in a manner forming a turbine ring, each sector (16) including a base (18), an upstream leg (22) and a downstream leg (24) extending radially from the base; a ring support structure (14) including: an isolation ring (30) extending around the sector (16) and including a downstream flange (36) such that the downstream leg (24) of each sector abuts against the downstream flange (36); an upstream suction plate (32) extending circumferentially around the longitudinal axis such that it contacts the upstream leg of each sector and is attached to an upstream region (40b) of the isolation ring, the upstream region extending from the upstream leg (22).

Description

Technical Field

[0001] This disclosure relates to a turbine ring assembly for a turbine engine, wherein the turbine ring assembly includes a plurality of corner sectors arranged circumferentially, head-to-head, to form a turbine ring made of a ceramic matrix composite material.

[0002] This invention is particularly applicable to aviation gas turbine engines, and even to other turbine engines, such as industrial turbines. Background Technology

[0003] In aero gas turbine engines, it is well known that the corner sectors of turbine ring assemblies are made of ceramic matrix composites (CMCs) instead of metallic materials (especially metal alloys). This is because the mechanical properties of CMCs make them more suitable for forming high-temperature structural components compared to metallic materials, which require particularly high cooling airflow velocities. Therefore, the use of CMCs can reduce the flow rate of cooling air typically drawn from the engine, and thus improve the performance of the turbine engine.

[0004] Turbine ring assemblies for turbine engines using CMC materials are known in particular from patents FR3056636, FR3055146 and FR3076578.

[0005] While these turbine ring assemblies are satisfactory, their structure still needs improvement. Summary of the Invention

[0006] Therefore, the object of the present invention is to provide a turbine ring assembly extending around a longitudinal axis, along which fluid is intended to flow from upstream to downstream, the turbine ring assembly comprising:

[0007] - Multiple annular corner sectors made of ceramic matrix composite material arranged circumferentially in a manner forming a turbine ring, each annular corner sector including a base, an upstream leg and a downstream leg extending radially from the base and axially spaced apart from each other along the extension direction of the longitudinal axis.

[0008] A ring support structure comprising: a spacer extending circumferentially around the plurality of corner sectors and including one or more downstream flanges, such that a downstream leg of each corner sector abuts against the downstream flange or a downstream flange of the spacer; and an upstream suction plate extending circumferentially around a longitudinal axis and radially relative to the axis, such that it abuts against an upstream leg of each corner sector on one hand and is attached to an upstream region of the spacer on the other hand, the upstream region being outside the upstream legs relative to the longitudinal axis and arranged radially in a straight line with the upstream legs of each corner sector.

[0009] An air diffuser is arranged between the isolation ring and each annular sector, and the air diffuser includes an upstream wall attached between the upstream suction plate and the upstream area of ​​the isolation ring.

[0010] This configuration of the turbine ring assembly allows for control of the axial positioning of the multiple annular corner sectors and significantly improves the correction of axial dimensional tolerances in the corner sectors. The turbine ring assembly is held directly to the turbine housing via the aforementioned ring support structure, for example, via upstream and downstream hooks. This novel turbine ring assembly configuration also eliminates the multiple components of the prior art (particularly a single suction upstream plate), reducing the number of operations required to install the assembly and thus facilitating its installation. This also reduces the weight of the assembly. Furthermore, the air diffuser of the turbine ring assembly is axially held in place by its upstream wall, which is arranged (clamped) between the upstream suction plate and the upstream region of the isolation ring.

[0011] Based on other possible characteristics:

[0012] - Multiple flange components are circumferentially distributed between the upstream suction plate and the upstream area of ​​the isolation ring, so that a pre-clamping force of the upstream suction plate is generated in the upstream area of ​​the isolation ring.

[0013] -The upstream retaining member connects the upstream support leg and the upstream suction plate of each annular sector;

[0014] -The downstream retaining member connects the downstream legs and isolation rings of each annular sector to the one or more downstream flanges;

[0015] - The upstream suction plate includes a first plate component that is radially inner and a second plate component that is radially outer. The second plate component extends radially relative to the longitudinal axis in the extending direction of the first plate component. The first plate component contacts the upstream leg of each annular sector and is axially thickened relative to the second plate component attached to the upstream region of the isolation ring.

[0016] - The second plate component is axially thickened relative to the isolation ring or each downstream flange;

[0017] - The isolation ring includes an upstream hook and a downstream hook, which are axially spaced apart from each other and each has the same orientation pointing upstream or downstream. Each hook is designed to engage with a corresponding hook with the opposite orientation on the turbine housing for hooking the isolation ring onto it.

[0018] - The upstream and downstream hooks of the isolation ring are oriented downstream;

[0019] - The isolation ring includes a downstream region, which includes the one or more downstream flanges and cantilevered radially inward from the downstream hook of the isolation ring along the direction of the longitudinal axis;

[0020] - The one or more downstream flanges of the isolation ring extend radially from the base of the one or more downstream flanges toward a plurality of annular sectors, and the isolation ring includes a component that extends axially from the base of the one or more downstream flanges to an upstream region of the isolation ring, the component having a radial dimension that increases in the direction toward the upstream region, such that the component of the isolation ring has a generally triangular shape in the axial cross section.

[0021] -The typically triangular isolation ring component comprises multiple consecutive segments arranged circumferentially adjacent to each other;

[0022] - An air diffuser includes a wall arranged to face a diagonal sector (to be cooled) and through which a plurality of through-holes are provided for allowing cooling air to pass through and for distributing a cooling airflow over the facing diagonal sector (radially, particularly from the outside to the inside of the ring assembly); the air diffuser may include a cavity arranged radially around the wall through which the plurality of through-holes are provided with cooling air; the wall through which the plurality of through-holes are arranged substantially radially and extends circumferentially around and facing the outer surface of the diagonal sector, the wall facing and parallel to the outer surface, such that the cooling airflow exits from through-hole openings directly on the surface;

[0023] - The walls of the diffuser, through which multiple through-holes pass, are arranged at a distance close enough to the facing corner sector, especially its outer surface, so as to minimize the temperature gradient in the facing corner sector.

[0024] - An air diffuser is arranged in an interior space that is defined on one hand by an isolation ring and on the other hand by each annular sector. The air diffuser has a typical shape suitable for being introduced into the interior space of the market, and is particularly triangular.

[0025] Another object of the present invention is a turbine engine comprising a turbine ring assembly as briefly disclosed above. Attached Figure Description

[0026] Other features and advantages of the subject matter of this invention will be apparent from the following description of embodiments provided by way of non-limiting examples with reference to the accompanying drawings.

[0027]

Figure 1

[0028]

Figure 2

[0029]

Figure 3

[0030]

Figure 4

[0031]

Figure 5

[0032] Now it will be described as follows Figures 1 to 5 The turbine ring assembly of a turbine engine (in an aircraft) according to an embodiment of the present invention is shown and indicated by general reference numeral 10. The assembly 10 extends around a longitudinal axis X-X', along which gaseous fluid is intended to flow to the inner side of the turbine ring assembly.

[0033] The terms "upstream" and "downstream" used here refer to the direction of airflow along the axis X-X' into the turbine ring assembly, such as... Figure 1 As indicated by the middle arrow F.

[0034] exist Figure 1 In the middle, arrow D A The arrow D indicates the axial direction of the turbine ring assembly 10. R This indicates its radial direction. For the sake of simplicity, Figures 1 to 5 This is a partial view of the component, which is actually a ring.

[0035] The component 10 specifically includes a turbine ring 12 made of ceramic matrix composite (CMC) with its center on the longitudinal axis X–X', and a metal ring support structure 14 that radially surrounds the turbine ring 12 and extends circumferentially around the ring.

[0036] Turbine ring 12 surrounds a turbine blade assembly that is known in itself but not shown in the figure.

[0037] In the remainder of this specification, the turbine described herein is a high-pressure turbine. However, the invention can also be applied to low-pressure turbines.

[0038] The turbine ring 12 is formed by a plurality of annular corner sectors 16, which are circumferentially arranged end-to-end to form a complete ring together. In particular, these sectors are mechanically connected to each other by connecting elements such as axial pins, which will be described below.

[0039] The axial cross-section of each annular sector 16 ( Figure 1 The turbine ring 12 is basically shaped like an inverted Greek letter Pi (or π). Its base 18 has an inner surface 18a oriented towards the axis X-X', which defines an angular portion of the inner surface of the turbine ring 12, and an outer surface 18b, oriented away from the axis X-X', opposite to the inner surface 18a, which defines an angular portion of the outer surface of the ring turbine 12. The inner surface 18a is, for example, provided with a wear-resistant coating 20 that also serves as a thermal and environmental barrier.

[0040] The upstream outrigger 22 and the downstream outrigger 24 extend radially from each angular portion of the outer surface 18b of each turbine annulus corner sector along the X-X' axis, in other words, toward the outside of the turbine annulus 12. These outriggers extend along direction D... A They are axially spaced apart by a distance equivalent to almost the entire width of the corner sector (axial dimension along axis X-X'). Furthermore, each of the two legs 22, 24 of each corner sector 16 extends radially or vertically (along direction D). R The overall length (in radians) of the associated corner sector extends circumferentially (along a transverse plane perpendicular to the axis X-X'), and the overall length varies according to the presence of component members or multiple components arranged axially relative to the associated corner sector.

[0041] The ring support structure 14 is made of a combination of multiple components that are different from each other (i.e., independent).

[0042] More specifically, such as Figure 1 and 2 As shown, the ring support structure 14 includes an isolation ring 30, an upstream suction plate 32, and an air diffuser 34.

[0043] As shown in this embodiment, the isolation ring 30 can be manufactured by assembling multiple isolation ring corner sectors 31 that are circumferentially placed with their heads connected (this construction proves to be relatively easy to assemble), or the isolation ring 30 can be formed by a single rotationally symmetric component (in other words, extending more than 360°).

[0044] Typically, the insulating ring 30 extends circumferentially around a plurality of annular corner sectors 16 and includes one or more downstream flanges such that a downstream leg 24 of each annular corner sector 16 abuts against a downstream flange of the insulating ring or one of the downstream flanges 36. In this embodiment, each annular corner sector 31 includes a downstream flange 36 that extends radially toward the facing (along the axis X-X') annular corner sector 16 and parallel to the downstream leg 24, extending abutting against the latter. The downstream leg 24 is ferried by means such as a downstream axial pin 38 ( Figure 1 , 2The retaining member of (4) abuts against the downstream flange 36, the downstream axial pin 38 being arranged aligned with a portion of the downstream leg 24, the portion having an increased radial extension, for example in the form of a groove (a cutout profile of the upper edge of the downstream leg 24, i.e., non-linear, which can limit the weight of the component). Here, the downstream flange 36 has the same radial extension (arc-shaped) along its length to ensure continuous contact with the ring, with the aim of maintaining a radial seal. The downstream flange 36 is relatively thin compared to the rest of the isolation ring structure, and therefore has a degree of flexibility to absorb some of the forces transmitted to the isolation ring. To retain each downstream leg 24 on each downstream flange 36, for example, there are two axial pins 38 ( Figure 2 Furthermore, this set of axial pins is regularly distributed around the longitudinal axis X-X', so that all the angle rings and isolation ring sectors are circumferentially connected. The number of axial pins for each pair of downstream legs and downstream flanges can, of course, vary.

[0045] like Figure 1 , 2 As shown in Figure 4, the downstream flange 36 of each isolation ring sector 31 extends radially from the base 36a toward the facing annular sector 16. The isolation ring sector 31 includes a component 40 that extends axially (along direction D) from its downstream end 40a, located at the base 36a of the downstream flange 36, toward its opposite upstream end 40b, which defines the downstream region of the isolation ring, toward the upstream region of the isolation ring. A The extension increases its radial dimension. Typically, the downstream region 40a of the isolation ring, including the downstream flange 36, cantilevered radially inward (towards axis X-X') from the base 36a.

[0046] Here, component 40 has a generally triangular axial cross-section. The upstream end 40b extends radially toward the upstream leg 22 of the annular sector 16 (the upstream end 40b is arranged aligned with the upstream leg 22 and positioned outside the upstream leg 22 relative to the axis X-X'), and here along the cross-section (in... Figure 3 The front view) has a free lower edge that is cut so that it is nested with the partially slotted profile of the free upper edge of the upstream leg 22.

[0047] like Figure 2 As shown, the component 40 of the isolation zone sector 31 includes a plurality of circumferentially arranged adjacent sections, which define different adjacent hollow functional areas of the isolation zone forming a partially enclosed compartment (to reduce structural bulk), for example... Figure 1 , 2 The three compartments C1, C2, and C3 shown in 4 and 5 (however, in another embodiment, the number of compartments may be different).

[0048] Compartments C2 and C3 are symmetrical to each other relative to the central compartment C1. Figure 1 The axial section shows two compartments C2-3. The central compartment C1 is in... Figure 2 , 4 As seen in 5.

[0049] Central compartment C1 in the rear view from above (downstream) ( Figure 2 In the front view, it has a hollow section formed by two walls that slope toward each other, and in the front view ( Figure 5 ), having a front surface ( Figure 5 The central block B1 (visible in the middle) through which the orifice O1 passes Figure 1 Two axial grooves A1 and A2 on both sides (A1 is visible in the middle) Figure 4 As can be seen in the image, components A1, A2, and B1 are arranged in... Figure 2 The hollow part below ( Figure 4 (groove A1 in the middle).

[0050] Compartments C2 and C3 open from above, as... Figure 2 and 5 As shown, each has an axial cross-section that is essentially triangular. Figure 1 ).according to Figure 5 The front (upstream) perspective view shows that compartments C2 and C3 each consist of blocks B2 and B3, with each block passing through orifices O2 and O3 on the front surface.

[0051] It will be noted that the construction of the compartments divided into isolation ring sectors 31 can be varied without departing from the scope of the invention.

[0052] Each isolation zone sector 31 ( Figure 1 On the one hand, it may include an upstream hook 31a of a corresponding upstream hook Ctam intended to engage the turbine housing Ct, and on the other hand, it may include a downstream hook 31b of a corresponding downstream hook Ctav intended to engage the turbine housing, so that the ring support structure 14 can be directly assembled onto the turbine housing and held in place.

[0053] The two upstream and downstream hooks of the turbine housing are oriented upstream, for example, and the two upstream and downstream hooks of each isolation ring sector 31 are oriented in opposite directions, in other words, downstream. This arrangement facilitates direct mounting of the isolation ring onto the turbine housing without requiring any ring support housing for mounting the components onto the turbine housing. It will be noted that the two hooks follow different radii relative to the longitudinal axis X-X'. More specifically, the downstream region 40a of the isolation ring, including the downstream flange 36, cantilevered radially inward (towards the axis X-X') from the downstream hook 31b.

[0054] generally, Figure 1 , 2The air diffuser 34 shown in Figure 4 extends circumferentially around the longitudinal axis X-X' in a 360° manner and is sectored in a manner corresponding to the sector of each angular annular-isolation ring assembly. The air diffuser 34 is designed to diffuse cooling air across a plurality of annular sectors 16, and more specifically, onto the outer surface 18b of each of the plurality of annular sectors. Figure 1 Air diffuser 34 is arranged between each isolation corner sector 31 and each annular corner sector 16. More specifically, air diffuser 34 faces each annular corner sector and is arranged radially outward relative to the axis X-X' of the annular corner sector.

[0055] In the described embodiment, the air diffuser 34 is arranged in an internal space defined on one hand by each isolation ring corner sector, particularly by the downstream flange 36 and the isolation ring component 40, and on the other hand by each ring corner sector 16. Figure 1 , 2 As shown in Figure 4, the air diffuser 34 therefore has a general shape suitable for being introduced into the aforementioned interior space, such as a typical triangle. It will be noted that the respective shapes of the isolation ring component 40 with the downstream flange 36 and the diffuser body can vary together in a way that keeps them adapted to each other.

[0056] The air diffuser 34 includes cavities 34a positioned around a base 18 of each annular sector 16, the cavities being fed cooling air, for example, from a compressor stage of a turbine engine including a turbine ring assembly 10. The cavities 34a are defined by walls 34b of the diffuser body, which face the outer surface 18b of the annular sector, are oriented substantially parallel to the annular sector, and have a plurality of through-holes 34c opening to the outer surface 18b to distribute the cooling air onto the outer surface 18b. Figure 1 The through-hole 34c of the air diffuser is configured sufficiently close to the facing parallel outer surface 18b to be cooled in order to minimize the temperature gradient on the annular sector due to the effect of localized airflow in the radial direction. Excessive distance between the through-hole 34c and the facing outer surface 18b will result in a more diffused airflow and therefore less impact on the outer surface 18a, leading to a larger temperature gradient and thus reduced efficiency.

[0057] like Figure 2 As shown, the air diffuser 34 also includes an upstream wall 34d connected to the diffuser body, the upstream wall being provided by two parallel structural arms 34e and 34f that are circumferentially spaced apart from each other and extend axially (arm 34f is in...). Figure 4 (See in the background) Enclosed cavity 34a. The two arms 34e and 34f are designed to be assembled into... Figure 5The axial grooves A2 and A1 of the isolation ring sector. The upstream wall 34d forms the upstream flange of the diffuser and is pierced by multiple holes t1-t5 through its thickness. Figure 2 It is designed to receive various component parts. The upstream flange 34d is designed to abut against the end of each isolation ring sector 31 or the end surface of the upstream region 40b.

[0058] As already mentioned, the ring support structure 14 includes an upstream suction plate 32, which has the following characteristics: Figure 2 The rotationally symmetric shape (360°) about the longitudinal axis X-X' is shown in partial view. Typically, the upstream plate 32, made as a single piece, is arranged such that it directly contacts (and abuts against) the upstream leg 22 of each annular sector 16 on one hand, and is attached to the upstream end 40b of each isolated annular sector on the other (this end 40b is radially positioned relative to the longitudinal axis X-X' and radially extending outward of the upstream leg 22). This arrangement holds the multiple annular sectors 16 in an axial position (along direction D). A ).

[0059] More specifically, the upstream suction plate 32 extends radially relative to the longitudinal axis X-X' in the form of two plate components (forming a single identical component) extending away from this axis: a first plate component 32a radially inward (relative to the axis X-X'), followed by a second plate component 32b radially outward (relative to the axis X-X'). The first inner plate component 32a is axially thickened relative to the second outer plate component 32b (along direction D). A The second outer plate component 32b is arranged facing the upstream end or region 40b of the isolation ring. It will be noted that the second plate component 32b is axially thickened relative to the relatively flexible downstream flange 36 of the isolation ring, thereby providing relatively high rigidity to the assembly of the upstream suction plate 32 in a normally compliant manner.

[0060] More specifically, the upstream wall 34d of the air diffuser 34 is inserted between the upstream plate 32 and the insulating ring 30, and attached between these two components, thereby axially blocking the diffuser. More specifically, the upstream wall 34d is clamped between the upper part of the second plate component 32b and the first plate component 32a on one side, and the upstream end 40b of the insulating ring on the other side. The upstream wall 34d is similarly arranged on its outer side relative to the axis X-X' in the radial extension direction of the upstream leg 22.

[0061] like Figure 1 and 4 As shown, in the assembly of the ring support structure 14, the first plate member 32a is arranged in contact with the upstream leg 22 (and also partially in contact with the lower part of the upstream wall 34d of the diffuser). The second plate member 32b itself is arranged in contact with the upstream wall 34d of the diffuser and is attached together with the latter to the upstream isolation ring end 40b.

[0062] Multiple flange / connecting members are circumferentially distributed to connect the second plate component 32b (through multiple through holes 32c circumferentially), the upstream wall 34d of the diffuser, and the upstream isolation ring end 40b, thereby creating a pre-clamping of the upstream plate on the isolation ring. For example, Figure 1 , 2 The components marked 42 in section 4 are clamping screws 42 with nuts 44, and sequentially engage the through hole 32c, the orifices t2 and t5 of the upstream flange 34d of the diffuser, and the orifices O2 and O3 of the isolation ring sector 31 to provide access to cavities C2 and C3.

[0063] With axial pin 46 ( Figure 1 Multiple component parts manufactured in the form of ) are sequentially joined through multiple other through holes 32d of the second plate component 32b. Figure 1 ), through the hole t3 of the upstream flange 34d of the diffuser ( Figure 2 ) and the orifice O1 through the isolation ring corner sector leading to the bottom of the housing ( Figure 5 These pins 46 are used to precisely position the diffuser 34 tangentially relative to the upstream plate 32 so as to better position the upstream plate 32 facing the annular sector and facing the two holes arranged on both sides of the bore 32d. Figure 2 Here, these two holes are calibration holes used to supply air from the diffuser.

[0064] It will be noted that the upstream suction plate 32 is on its inner surface ( Figure 2 The diffuser includes non-intersecting protrusions or ribs r1, r2 oriented opposite to the upstream flange 34d and the upstream legs 22 of each annular sector. These protrusions or ribs extend over the arcuate portions (corner sectors) and are designed to insert between the lower edge of the upstream flange 34d and the upper edge of the upstream legs 22. These protrusions, by radially retaining the diffuser supplementary pin 46, ensure that the diffuser is at an optimal distance from and does not contact the annular sectors in question.

[0065] like Figure 2 and 4 As shown, each upstream retaining member connects to the upstream support leg 22 and the upstream suction plate 32 of each annular sector 16, and engages at one end with the housing (blind hole) of the first plate member 32a. Figure 4 These components are, for example, connecting members 48 made in the form of axial pins 38.

[0066] It will be noted that, compared to the isolation ring component 40 whose thickness increases downstream (the isolation ring component 40 may have a different construction without affecting the principles described herein), the thinner downstream construction of the isolation ring sector can restrict the transmission of force to the annular sector 16, which is applied to the upstream plate 32 via a high-pressure distributor (not shown) in contact with the upstream plate 32.

[0067] The downstream thinning of the isolation ring sector is manufactured here in the form of a thinning leg 36, which therefore has a certain degree of axial flexibility (elasticity) relative to the rest of the isolation ring sector.

[0068] Furthermore, the upstream suction plate 32 has high stiffness / rigidity, partly due to the greater thickness of its first plate component 32a in contact with the annular sector 16 compared to its second plate component 32b, and partly due to the greater stiffness of the upstream plate 32, especially its second plate component 32b, relative to the downstream region of the isolation ring sector.

[0069] Therefore, the force applied to the upstream plate 32 by the high-voltage distributor is mainly absorbed by this component, and the transmission of these forces to the annular sector 16 is limited.

[0070] The upstream suction plate 32 is formed as a single rotationally symmetrical component, which improves the management of axial leakage between the circular cavity and the annular cavity located above the high-voltage distributor. Furthermore, this monolithic plate ensures better positioning of the annular corner sectors compared to sectorized plates.

[0071] Furthermore, axial retention at the annular sector position is ensured by pre-clamping introduced by the flange / connecting member circumferentially distributed between the upstream suction plate 32 (particularly the second plate component 32b) and the upstream end 40b of the isolation ring.

[0072] It will be noted that, apart from the upstream plate 32, diffuser 34 and isolation ring 30, there are no other components in the components of the ring support structure, particularly in the upstream region of the component, where the plate is arranged directly and simultaneously against the diffuser (which itself is against the upstream region 40b of the isolation ring) and the upstream legs of the ring sector.

[0073] Although specific exemplary embodiments have been referenced in this specification, modifications may be made to these embodiments without departing from the general scope of the invention as defined by the claims. Furthermore, individual features of the different embodiments illustrated or mentioned may be combined in additional embodiments. Therefore, the specification and drawings should be considered illustrative rather than restrictive.

Claims

1. A turbine ring assembly (10) extending around a longitudinal axis (X-X'), along which fluid is intended to flow from upstream to downstream, the turbine ring assembly comprising: - Multiple annular sectors (16) made of ceramic matrix composite material arranged circumferentially in a manner forming a turbine ring, each annular sector (16) including a base (18), an upstream leg (22) and a downstream leg (24) extending radially from the base and axially spaced apart from each other along the extension direction of the longitudinal axis. - Ring support structure (14), which includes: An isolation ring (30) extends circumferentially around the plurality of annular sectors (16) and includes one or more downstream flanges (36) such that the downstream leg (24) of each annular sector abuts against the downstream flange or a downstream flange (36) of the isolation ring. An upstream suction plate (32) extends circumferentially around a longitudinal axis (X-X') and radially relative to that axis, such that it abuts against the upstream leg (22) of each annular sector on one side and is attached to the upstream region (40b) of the isolation ring (30) on the other side. The upstream region is located outside the upstream leg (22) relative to the longitudinal axis and is arranged radially in a straight line with the upstream leg (22) of each annular sector (16). An air diffuser (34) is arranged between the isolation ring (30) and each annular sector (16), the air diffuser (34) including an upstream wall (34d) attached between the upstream suction plate (32) and the upstream region (40b) of the isolation ring (30).

2. The turbine ring assembly according to claim 1, wherein, Multiple flanged components (42, 44) are circumferentially distributed between the upstream suction plate (32) and the upstream region (40b) of the isolation ring (30), resulting in pre-clamping of the upstream suction plate in the upstream region of the isolation ring (30).

3. The turbine ring assembly according to claim 1, wherein, The upstream retaining member (48) connects the upstream support leg (22) and the upstream suction plate (32) of each annular sector (16).

4. The turbine ring assembly according to claim 1, wherein, The downstream retaining member (38) connects the downstream leg (24) of each annular sector (16) to the one or more downstream flanges (36) of the isolation ring (30).

5. The turbine ring assembly according to claim 1, wherein, The upstream suction plate (32) includes a first plate component (32a) that is radially inner and a second plate component (32b) that is radially outer. The second plate component (32b) extends radially relative to the longitudinal axis in the extension direction of the first plate component (32a). The first plate component (32a) contacts the upstream leg (22) of each annular sector and is axially thickened relative to the second plate component (32b) attached to the upstream region (40b) of the isolation ring (30).

6. The turbine ring assembly according to claim 5, wherein, The second plate component (32b) is axially thickened relative to each of the downstream flanges (36) of the isolation ring (30).

7. The turbine ring assembly according to claim 1, wherein, The isolation ring includes an upstream hook (31a) and a downstream hook (31b) that are axially spaced apart from each other and each having the same orientation pointing upstream or downstream. Each hook is designed to engage with a corresponding hook of the turbine housing that is oriented in the opposite direction for hooking the isolation ring onto it.

8. The turbine ring assembly according to claim 7, wherein, The upstream hook (31a) and downstream hook (31b) of the isolation ring (30) are oriented downstream.

9. The turbine ring assembly according to claim 7, wherein, The isolation ring (30) includes a downstream region (40a) which includes the one or more downstream flanges (36) and cantilevered radially inward from the downstream hook (31b) of the isolation ring (30) along the longitudinal axis.

10. The turbine ring assembly according to claim 1, wherein, The one or more downstream flanges (36) of the isolation ring (30) extend radially from the base (36a) of the one or more downstream flanges toward a plurality of annular sectors (16), and the isolation ring (30) includes a component (40) that extends axially from the base (36a) of the one or more downstream flanges to an upstream region of the isolation ring (30), the component having a radial dimension that increases in the direction toward the upstream region, such that the component (40) of the isolation ring (30) has a generally triangular shape in the axial cross section.

11. The turbine ring assembly of claim 10, wherein, Typically, the triangular isolation ring component (40) comprises multiple consecutive segments (C1-C3) arranged circumferentially adjacent to each other.

12. The turbine ring assembly according to claim 1, wherein, The air diffuser (34) includes a wall (34b) arranged to face diagonal sectors and passed through by a plurality of through holes (34c) for passing through cooling air and for distributing cooling airflow on the facing diagonal sectors (16).

13. The turbine ring assembly of claim 12, wherein, The diffuser wall (34b) through which multiple through holes (34c) pass is arranged at a distance close enough to the facing corner sector (16) to minimize the temperature gradient in the facing corner sector.

14. The turbine ring assembly according to any one of claims 1 to 13, wherein, An air diffuser (34) is arranged in an interior space defined on one side by an isolation ring (30) and on the other side by each annular sector (16), the air diffuser having a general shape suitable for being introduced into the interior space.

15. The turbine ring assembly of claim 14, wherein, The air diffuser is triangular.

16. A turbine comprising a turbine ring assembly according to any one of claims 1 to 15.

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