EP4488492A1 - Module for a fluid flow machine - Google Patents

Abstract

The present invention relates to a module for a turbomachine, with a guide vane arrangement, a seal carrier which is arranged radially within an inner platform of the guide vane arrangement, seal carrier walls, namely a first and a second seal carrier wall, and a sliding body and a connecting element, wherein the first seal carrier wall and the seal carrier are formed integrally with one another, and wherein the seal carrier walls are made up of several pieces relative to one another and the second seal carrier wall is fastened to the first seal carrier wall and the seal carrier via the connecting element, wherein the sliding body keeps the seal carrier walls spaced apart from one another in such a way that they axially delimit an intermediate space in which the guide vane arrangement engages with a guide pin extending radially inwards, wherein the second seal carrier wall is spaced apart from the wall surface of the first seal carrier wall pointing in the axial direction and from the seal carrier.

Description

technical field

The present invention relates to a module for a turbomachine.

State of the art

The turbomachine can be a jet engine, for example a turbofan engine. Functionally, the turbomachine is divided into a compressor, combustion chamber and turbine. In the case of a jet engine, for example, the air drawn in is compressed by the compressor and burned in the downstream combustion chamber with added kerosene. The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process. The turbine also extracts energy from the hot gas in order to drive the compressor. The turbine and compressor are usually constructed in several stages, with each stage having a guide vane and a rotor blade ring.

The present invention relates to a module with a guide vane arrangement and a seal carrier. The guide vanes of the guide vane arrangement extend radially between a radially outer outer platform and a radially inner inner platform. The seal carrier is arranged radially inside this inner platform and forms part of the so-called inner air seal (IAS). The seal carrier helps to reduce or avoid gas losses, which is advantageous in terms of the efficiency of the turbomachine. As large a portion as possible, or as far as possible all of the fluid or gas, should flow through the gas channel of the turbomachine.

representation of the invention

The present invention is based on the technical problem of specifying a particularly advantageous module for a turbomachine.

This is achieved according to the invention with a module according to claim 1. In this module, the seal carrier and the guide vane arrangement are mounted relative to one another by means of a first and a second seal carrier wall, for which purpose the seal carrier walls axially delimit an intermediate space into which the guide vane arrangement engages from the radial outside with at least one guide pin. The second seal carrier wall is provided in several pieces to the first seal carrier wall, i.e. as a previously separate part it is assembled with the first seal carrier wall and fastened to it. This fastening is implemented with a connecting element, with a sliding body arranged in the intermediate space keeping the seal carrier walls at the defined distance so that they delimit the intermediate space.

The second seal carrier wall is indeed attached to the first seal carrier wall and thus also to the seal carrier via the sliding body and the connecting element, but is spaced apart from the wall surface of the first seal carrier wall facing in the axial direction and also from the seal carrier itself. Said wall surface of the first seal carrier wall faces the second seal carrier wall, in other words it limits the intermediate space in the axial direction. The second seal carrier wall is spaced apart from this wall surface and also from the seal carrier itself, in other words it lies neither on this wall surface nor on the seal carrier itself.

The spacing can be advantageous, for example, in that it can reduce or avoid axial force input into the connecting element, which can increase the robustness of the multi-part structure or create opportunities for weight reduction. On the other hand, the spacing from the seal carrier can reduce or avoid radial force input into it, so it can prevent the seal carrier from tipping, for example.

This could occur temporarily, for example, due to transient temperature behavior and then sometimes result in permanent leaks. In summary, the spacing allows a structure to be realized that is advantageous in terms of robustness and tightness, despite the multi-piece seal carrier walls.

The multi-piece design of the seal carrier walls can be advantageous in terms of production, for example, because, for example, if two seal carrier walls are formed monolithically with the seal carrier and the material is removed, the space between them would have to be exposed by a relatively deep cut. Irrespective of this, the multi-piece design can also open up possibilities in the choice of material or thickness, for example, the second seal carrier wall can be made thinner and in particular in the form of a sheet metal, thus creating scope for weight optimization. The seal carrier is designed as one piece with the first seal carrier wall, which in turn can create stability (despite the seal carrier walls being made up of multiple parts).

Preferred embodiments can be found in the dependent claims and the entire disclosure, whereby the presentation of the features does not always distinguish in detail between the module and the turbomachine or corresponding methods or uses. The disclosure is to be read with regard to all claim categories.

In the context of this disclosure, the term "one-piece" means that it cannot be separated without destruction, and can therefore generally refer to, for example, two parts connected in a joining process, for example welded together. Preferably, however, the one-piece design is accompanied by a monolithic design, i.e. the parts in question, e.g. the seal carrier and the first seal carrier wall (or e.g. a seal carrier wall and its axial section/web, see below), are formed from the same uninterrupted, continuous material. In other words, "monolithic" means an integral design without a material boundary in between.

The first seal carrier wall and the seal carrier are formed in one piece, preferably monolithically. Since the second seal carrier wall is attached separately and the gap does not have to be taken into account when producing the seal carrier, the monolithic production of the seal carrier and the first seal carrier wall can be simplified, for example by casting. The gap does not have to be created by removing material, for example, in a complex process, see above.

In general, within the scope of this disclosure, "axial" or "axial direction" refers to the longitudinal axis of the module, i.e. the longitudinal axis of the turbomachine. This longitudinal axis can, for example, coincide with a rotation axis around which the rotor blades assigned to the guide vane arrangement rotate during operation. "Radial" refers to the radial directions perpendicular to it, pointing away from the longitudinal axis, and "rotation" or "rotation direction" refer to a rotation around the longitudinal axis. "Inner" and "outer" refer to the radial direction unless expressly stated otherwise, so "inner" is closer to the longitudinal axis than "outer". If reference is made to an axial section, this refers to a section plane containing the longitudinal axis.

The seal carrier can, for example, carry a sealing element radially on the inside, which can seal inwards to a sealing structure, such as a sealing tip, which rotates together with the shaft or the rotor blades during operation. A brush seal or a so-called honeycomb seal or, in general terms, a run-in coating can be provided as a sealing element. As explained in detail below, the first seal carrier wall can preferably be formed monolithically with the seal carrier, whereby the two can then form a T-shape in particular when viewed in an axial section (the first seal carrier wall is therefore spaced from the axial ends of the seal carrier).

The connecting element can generally be a screw or a bolt, for example, but is preferably implemented in the form of a rivet. Irrespective of this, the seal carrier walls can be distributed with several connecting elements (and sliding bodies) attached to each other, and these sliding bodies can in particular form a so-called spoke centering, see below in detail. In general, "a" and "an" are to be read as indefinite articles in the context of this disclosure unless expressly stated otherwise and thus always also as "at least one" and "at least one".

In a preferred embodiment, the first and second seal carrier walls form a contactless labyrinth seal with one another and/or the second seal carrier wall and the seal carrier form a contactless labyrinth seal with one another. The first and second seal carrier walls then do not touch one another ("contactless"), but a good sealing effect can still be achieved with the labyrinth seal, for example by (multiple) redirection of a leakage flow. This can generally be achieved by an overlap in the axial and/or radial direction, so for example, viewed in an axial section, an axis-perpendicular line can pass through both the first and second seal carrier walls and/or an axis-parallel line can pass through both a seal carrier wall and the seal carrier.

According to a preferred embodiment, at least one of the seal carrier walls comprises an axial section that protrudes in the axial direction to the other seal carrier wall and is part of the contactless labyrinth seal or forms it. Viewed in an axial section, the axial section can delimit an axially extending channel of the labyrinth seal. Preferably, both the first and the second seal carrier wall can each be provided with a corresponding axial section, wherein the axial sections can delimit the axial channel together.

Insofar as reference is made to an "axial section" of the respective seal carrier wall in the context of the labyrinth seal or below in connection with the radial contact, this is preferably formed integrally, in particular monolithically, with the respective seal carrier wall. Viewed in an axial section, the axial section can be provided in the form of a web, for example have a greater extension in the axial direction than in the radial direction.

According to a preferred embodiment, at least one of the seal carrier walls is formed with a step when viewed in an axial section. This step can also delimit the labyrinth seal, for example together with an axial section of the other seal carrier wall. When viewed in the axial section, the above-mentioned axially perpendicular straight line from radially inside to radially outside can, for example, first pass through the step and then through the axial section of the other seal carrier wall, preferably it can then pass through the seal carrier wall with the step again. In other words, the seal carrier wall with the step can additionally have an axial section which, together with the step, forms an axially oriented U-shape into which the other seal carrier wall engages with an axial section.

To form the contactless labyrinth seal between the second seal carrier wall and the seal carrier, the latter can have a radially extending flank, for example on a step or in particular a radial section that rises radially outwards. This flank, together with the second seal carrier wall, can delimit the labyrinth seal, i.e. a radially extending channel of the labyrinth seal. The radial section can preferably be provided in one piece, in particular monolithically, with the seal carrier, for example as a web that rises radially outwards.

According to an alternative embodiment to the contactless labyrinth seal, the second seal carrier wall is spaced apart from the seal carrier and also axially spaced apart from the wall surface of the first seal carrier wall, but it still has radial contact with the first seal carrier wall. "Radial contact" here means that the two are pressed radially against each other, i.e., for example, radial compression increases the contact pressure in the contact surface (whereas radial pulling apart would reduce the contact pressure in the contact surface).

Viewed in an axial section, the contact surface in which the radial contact exists is preferably aligned essentially parallel to the axis, for example not tilted more than 20°, 10° or 5° to the longitudinal axis, preferably actually parallel to the axis. Regardless of these details, there is a contact due to the radial contact, so the seal is achieved by a tight fit between the seal carrier walls. These can be frictionally engaged, but are not, for example, firmly connected to one another, which can reduce mechanical stresses, for example.

The second seal carrier wall is spaced apart from the seal carrier, and the radial contact is accordingly offset radially outwards compared to the seal carrier. This radial offset can be used to reduce the introduction of forces into the seal carrier despite the frictional fit, i.e. to prevent tilting, for example (see above). The first seal carrier wall preferably comprises an axial section that projects axially towards the second seal carrier wall, in particular a web formed integrally/monolithically therewith (see above), which forms the radial contact with the second seal carrier wall. The axial section is offset radially outwards in relation to the seal carrier. In general, the second seal carrier wall can also be designed to be radially shortened, i.e. with its radially inner end directly abutting (sitting, so to speak) on the axial section of the first seal carrier wall.

In a preferred embodiment, however, the second seal carrier wall also has an axial section, which can in particular be designed as a web provided in one piece/monolithically therewith (see above) and is also offset radially outwards (relative to the seal carrier). The axial section of the second seal carrier wall protrudes towards the first seal carrier wall and forms the radial contact with its axial section. The axial section of the second seal carrier wall can be arranged radially inside or outside the axial section of the first seal carrier wall, i.e. it can rest against it from the radial inside or radial outside.

According to a preferred embodiment, which can relate to both the contactless labyrinth seal and the radial contact, the seal carrier is positioned exclusively by the first seal carrier wall. In an axial Viewed in section, for example, an axially parallel straight line that lies radially outside the seal carrier (i.e. no longer passes through the seal carrier) can only pass through the first seal carrier wall, i.e. not the second seal carrier wall. An axially parallel straight line that lies radially further out, in the area of the gap, then naturally passes through both seal carrier walls. In other words, there can be an annular space radially between the seal carrier and the second seal carrier wall in which only the first seal carrier wall is present.

The seal carrier preferably has no sections that extend/rise radially outwards. Viewed in an axial section, apart from the first seal carrier wall, no sections or similar extend radially outwards from the seal carrier, so the two form a simple T-shape, for example. In other words, preferably only the integral/monolithic first seal carrier wall rises radially outwards from the seal carrier.

In relation to a flow through the gas channel of the module with the working gas, which flows around the rotor blades of the rotor blade arrangement, for example, "front" means upstream and "back" means downstream. In a preferred embodiment, the first seal carrier wall is arranged at the front and the second seal carrier wall at the rear, i.e. the first seal carrier wall is upstream and the second is downstream. In the present disclosure, reference is made in principle to the first and second seal carrier walls, with "first" always also being read as "front" and "second" as "back".

In general, the sliding body can also be provided monolithically with one of the seal support walls, i.e. the first or in particular the second seal support wall. In a preferred embodiment, however, it is made up of several parts in relation to the seal support walls and the connecting element passes through it axially. The latter is also preferred in the case of a monolithic design, but not mandatory. The connecting element, which passes through the multi-part sliding body, holds it radially form-fitting between the seal carrier walls, and the sliding body is then additionally clamped axially.

In a preferred embodiment, the second seal carrier wall has a smaller thickness than the first seal carrier wall, so the multiple pieces are used to optimize weight. The thicknesses are each considered in an axial section, with an average value being used as a basis in the case of a thickness that varies over the extent of the respective seal carrier wall.

According to a preferred embodiment, the second seal carrier wall is made of a sheet metal, which can allow a particularly thin design and/or simple manufacture. The sheet metal can generally be segmented in the circumferential direction, i.e. provided in several parts. However, a continuous design in the circumferential direction, i.e. not divided/segmented, is preferred.

The guide pin, with which the guide vane arrangement engages in the intermediate space, extends radially inwards from its inner platform. In relation to the direction of rotation, the guide pin preferably rests on the sliding body, i.e. on the circumferential side. In a preferred embodiment, it encloses the sliding body together with another guide pin, which rests on the opposite side of the sliding body in the direction of rotation. This is therefore held between the guide pins, which is also referred to as a tang ("pincer"). The guide pins and the sliding body can still slide radially against each other, with several correspondingly held sliding bodies distributed all around, so the arrangement represents a spoke centering.

The invention also relates to a turbine for a turbomachine, in particular for an aircraft engine, which has a module disclosed here.

Short description of the drawings

In the following, the invention is explained in more detail using an embodiment, whereby the individual features are also described in the context of the independent claims in other combinations may be essential to the invention and no distinction is made in detail between the different claim categories.

Figur 1

ein Strahltriebwerk in einem Axialschnitt;

Figur 2

ein erstes erfindungsgemäßes Modul mit einer Leitschaufelanordnung und einem Dichtungsträger in einem Axialschnitt;

Figur 3

ein zweites erfindungsgemäßes Modul mit Leitschaufelanordnung und Dichtungsträger;

Figur 4

ein drittes erfindungsgemäßes Modul mit Leitschaufelanordnungen und Dichtungsträger;

Figur 5

ein viertes erfindungsgemäßes Modul mit Leitschaufelanordnung und Dichtungsträger;

Figur 6

ein fünftes erfindungsgemäßes Modul mit Leitschaufelanordnung und Dichtungsträger;

Figur 7

ein sechstes erfindungsgemäßes Modul mit Leitschaufelanordnung und Dichtungsträger.

In detail,

Figure 1

a jet engine in an axial section;

Figure 2

a first module according to the invention with a guide vane arrangement and a seal carrier in an axial section;

Figure 3

a second module according to the invention with guide vane arrangement and seal carrier;

Figure 4

a third module according to the invention with guide vane arrangements and seal carrier;

Figure 5

a fourth module according to the invention with guide vane arrangement and seal carrier;

Figure 6

a fifth module according to the invention with guide vane arrangement and seal carrier;

Figure 7

a sixth module according to the invention with guide vane arrangement and seal carrier.

Preferred embodiment of the invention

Fig. 1 shows a turbomachine 1 in a schematic view, specifically a jet engine. The turbomachine 1 is functionally divided into compressor 1a, combustion chamber 1b and turbine 1c. Both the compressor 1a and the turbine 1c are each made up of several stages, each stage consists of a guide vane and a rotor blade ring or comprises a rotor blade ring (axially front or rear). In the case of the turbine 1c and/or the compressor 1a, a rotor blade ring can be arranged downstream of the associated guide vane ring, provided that the relevant stage comprises a guide vane ring. During operation, the rotor blades rotate around the longitudinal axis 2.

Fig. 2 shows a section of the turbine 1c as module 20, again in an axial section. In detail, a guide vane arrangement 21 with a guide vane blade 21a and an inner platform 21b, as well as a guide pin 21c can be seen. The guide vane blade 21a is arranged radially on the outside of the inner platform 21b, the guide pin 21c extends radially inside it into an intermediate space 22. This intermediate space 22 is axially delimited between a first, front seal carrier wall 31 and a second, rear seal carrier wall 32. The first seal carrier wall 31 is upstream in relation to a flow 15 of the module 20 and the second seal carrier wall 32 is downstream.

The first seal carrier wall 31 is monolithically formed with a seal carrier 41, the two can be manufactured as a cast part, for example. A sealing element 42, for example a honeycomb seal, is provided radially on the inside of the seal carrier 41. The sealing element 42 seals against a sealing structure 43, which is only shown schematically as a contour here and rotates together with the shaft during operation.

The second seal carrier wall 32 is provided in several pieces to the first seal carrier wall 31 and is attached to it via a connecting element 35, in this case a rivet. The connecting element 35 passes through a sliding body 36, which holds the seal carrier walls 31, 32 at the defined axial distance. In relation to an axial direction 17, the first seal carrier wall 31 has a wall surface 31a facing away from the intermediate space 22, which in this case points upstream, and a wall surface 31b facing the intermediate space 22, which in this case points downstream.

The second seal carrier wall 32 is spaced apart from the wall surface 31b of the first seal carrier wall 31 in the axial direction 17. There is therefore a gap 24 between the axial section 32.1 of the second seal carrier wall 32, which in the present example forms at its radially inner end, and the first seal carrier wall 31 or wall surface 31b. However, this is comparatively small and therefore cannot be seen in detail in the present illustration. This can be used, for example, to reduce the force introduced into the connecting element 35, see the detail above.

Furthermore, the second seal carrier wall 32 is also spaced apart from the seal carrier 41, i.e. provided at a distance from it in the radial direction 18. As explained at the beginning, this can prevent, for example, a force being introduced into the seal carrier and thus a tilting. The seal carrier walls 31, 32 form a contactless labyrinth seal 25 with one another, in this case through the overlap between the axial section 32.1 of the second seal carrier wall 32 with an axial section 31.1 of the first seal carrier wall 31. Despite the gap 24 between the axial section 31.1 and the seal carrier wall 32 and the gap 24 between the axial section 32.1 and the first seal carrier wall 31, a relative seal can be achieved with the contactless labyrinth seal 25 by redirecting the leakage flow.

Figure 3 shows a Figure 2 alternative design, whereby the following illustration primarily emphasizes the differences, which also applies to all other embodiments. In general, within the scope of this disclosure, the same reference numerals designate the same part or parts with the same function and reference is always made to the description of the other figures. Even in the embodiment according to Figure 3 the second seal carrier wall 32 is spaced apart in the axial direction 17 from the wall surface 31b of the first seal carrier wall 31, so that there is a gap 24 between the wall surface 31b and the axial section 32.1 of the second seal carrier wall 32 (not shown in detail).

The same applies to the axial section 31.1 of the first seal carrier wall 31 and the second seal carrier wall 32, where there is also a gap 24. With the axial sections 31.1, 32.1, the seal carrier walls 31, 32 in turn form a contactless labyrinth seal 25. Since the axial section 32.1 is smaller than the variant according to Figure 2 is offset further radially inward, it also forms a contactless labyrinth seal 125 with the seal carrier 41, despite the radial gap 26 therebetween.

In the embodiment according to Figure 4 the first seal carrier wall 31 is formed with a step 31.2, i.e. viewed in the axial section with an axial offset. This step 31.2 forms the contactless labyrinth seal 25 with the axial section 32.1 of the second seal carrier wall 32. In the present example, the first seal carrier wall 31 is additionally formed with an axial section 31.1, which together with the step 31.2 forms a U-shaped recess into which the axial section 32.1 engages. Despite the gaps between the axial sections 31.1, 32.1 and the other seal carrier walls 31, 32, which are not referenced in detail here for the sake of clarity, a good seal can be achieved in this way.

Even in the embodiment according to Figure 5 the seal carrier walls 31, 32 together form a contactless labyrinth seal 25, namely via the axial section 32.1 of the second seal carrier wall 32. Furthermore, any leakage path is further extended by the contactless labyrinth seal 125 between the seal carrier 41 and the second seal carrier wall 32. For this purpose, the seal carrier 41 is formed with a radial section 41.1 that rises radially outwards. The radial section 41.1 does not lie against the second seal carrier wall 32, neither axially nor radially (column not referenced in detail for the sake of clarity).

The embodiment according to Figure 6 corresponds to the previously discussed variants in terms of the basic structure with the seal carrier walls 31, 32, which are fastened relative to each other via the sliding body 36 and the connecting element 35. Furthermore, in this case too, as in the Figures 2-4 , both the first seal carrier wall 31 and the second seal carrier wall 32 are each provided with an axial section 31.1, 32.1. In contrast to the variants discussed so far, these axial sections 31.1, 32.1 are not spaced apart from one another, but are provided in a radial contact 65. They therefore lie against one another in the radial direction 18 and thus form a seal 66, whereby a certain relative offset is possible in the axial direction 17. This prevents the introduction of axial forces, whereby a seal is created at the same time with the system.

The variant according to Figure 7 corresponds in its basic structure to that according to Figure 6 , the seal carrier walls 31, 32 are in radial contact 65 with each other via a respective axial section 31.1, 32.1. In contrast to Figure 6 In this case, the second seal carrier wall is made of a sheet metal and the axial section 32.1 is produced by bending a radially inner section accordingly. The same applies to the embodiment according to Figure 8 , in which the axial section 32.1 formed from the sheet metal, in contrast to Figure 7 not from the radial outside, but from the radial inside on the axial section 31.1 of the first seal carrier wall 31.

For illustration purposes, Figure 8 furthermore, a front and a rear sealing plate 81, 82 are referenced, which are assembled as multi-piece parts to form the seal support walls 31, 32 and are also held together by the connecting element 35. The front sealing plate 81, together with the inner platform 21b and an inner platform 85 (only shown schematically as a contour) of the upstream rotor blade arrangement, forms a so-called fish mouth seal 91, and the rear sealing plate 82, together with the inner platform 21b and the inner platform 86 (only shown schematically as a contour) of the downstream rotor blade arrangement, forms a fish mouth seal 92. Although also shown in the other figures, the sealing plates 81, 82 are optional; the module 20 can also be provided without a fish mouth seal or, alternatively, only with a front or a rear sealing plate.

REFERENCE SYMBOL LIST

turbomachine 1 compressor 1a combustion chamber 1b turbine 1c longitudinal axis 2 flow 15 axial direction 17 radial direction 18 module 20 guide vane arrangement 21 guide vane blade 21a interior platform 21b guide pin 21c interior platform 21b space 22 gap 24 contactless labyrinth seal 25 radial gap 26 first, front seal carrier wall 31 opposite wall surface 31a facing wall surface 31b second, rear seal carrier wall 32 axial section 32.1 connecting element 35 sliding body 36 seal carrier 41 sealing element 42 sealing structure 43 radial contact 65 sealing sheets 81, 82 interior platform 85 interior platform 86 fish mouth seals 91, 92 contactless labyrinth seal 125

Claims (14)

Module (20) for a turbomachine (1), with a guide vane arrangement (21), a seal carrier (41) arranged radially within an inner platform (21b) of the guide vane arrangement (21), seal carrier walls (31, 32), namely a first (31) and a second seal carrier wall (32), and a sliding body (36) and a connecting element (35), wherein the first seal carrier wall (32) and the seal carrier (41) are formed integrally with one another, and wherein the seal carrier walls (31, 32) are made up of several pieces relative to one another and the second seal carrier wall (32) is attached to the first seal carrier wall (31) and the seal carrier (41) via the connecting element (35), wherein the sliding body (36) keeps the seal carrier walls (31, 32) spaced apart from one another in such a way that they axially define an intermediate space (22) in which the guide vane arrangement (21) engages with a radially inwardly extending guide pin (21c), wherein the second seal carrier wall (32) is spaced from the wall surface (31b) of the first seal carrier wall (31) facing in the axial direction (17) and from the seal carrier (41). Module (20) according to claim 1, wherein the first seal support wall (31) and the second seal support wall (32) form a contactless labyrinth seal (25) with each other. Module (20) according to claim 1 or 2, wherein the second seal carrier wall (32) and the seal carrier (41) form a contactless labyrinth seal (125) with each other. Module (20) according to claim 2 or 3, wherein the second seal carrier wall (32) comprises an axial portion (32.1) protruding in the axial direction to the first seal carrier wall (31) for forming the contactless labyrinth seal (25, 125). Module (20) according to one of claims 2 to 4, in which at least one of the seal carrier walls (31, 32) viewed in an axial section is shaped with a step (31.2) to form the contactless labyrinth seal (25, 125). Module (20) according to claim 1, wherein the first seal carrier wall (31) comprises an axial section (31.1) which projects in the axial direction (17) towards the second seal carrier wall (32), which is offset radially to the seal carrier (41) and forms a seal (66) with the second seal carrier wall (32) by means of a radial contact (65) therewith. Module (20) according to claim 6, wherein the second seal carrier wall (32) comprises an axial portion (31.1) projecting in the axial direction towards the first seal carrier wall (31), which is offset radially to the seal carrier (41) and forms the radial contact (65) with the axial portion of the first seal carrier wall (31). Module (20) according to one of the preceding claims, in which the seal carrier (41) is positioned exclusively by the first seal carrier wall (31) and, in the intended arrangement, is otherwise free of contact with other components radially outward and/or does not comprise any further sections projecting radially outward. Module (20) according to one of the preceding claims, in which, with respect to a flow (15) through the module (20), the first seal carrier wall (31) is arranged upstream and the second seal carrier wall (32) is arranged downstream. Module (20) according to one of the preceding claims, in which the sliding body (36) is in multiple pieces with respect to the seal carrier walls (31, 32) and the connecting element (35) passes through the sliding body (36). Module (20) according to one of the preceding claims, wherein the second seal support wall (32) has a smaller thickness than the first seal support wall (31). Module (20) according to claim 11, wherein the second seal carrier wall (32) is formed from a sheet metal which is preferably provided continuously without interruption in the circumferential direction. Module (20) according to one of the preceding claims, in which the first seal carrier wall (31) is formed monolithically with the seal carrier (41), in particular forms a T-shape with the seal carrier (41) in cross section. Turbine (1c) for a turbomachine (1), in particular an aircraft engine, with a module (20) according to one of the preceding claims.

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