EP3375980B1 - Seal holder for a flow engine - Google Patents

Description

Technical area

The present invention relates to a seal carrier for a turbomachine.

State of the art

As explained in detail below, the turbomachine may preferably be a jet engine. One component of this is a so-called seal carrier, which encloses the hot gas duct radially outward in the region of a rotor blade ring. Such a seal carrier has a first and a second seal carrier segment, which are assembled successively relative to a circulation about a longitudinal axis of the turbomachine. Radially inside, the first seal carrier segment has a first sealing structure and the second seal carrier segment has a second sealing structure. DE102005002270 . EP0716218 and EP2617949 discloses various sealing devices for turbomachines.

Presentation of the invention

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

According to the invention, this object solves, on the one hand, a seal carrier according to claim 1, in which the first and the second sealing structure are entangled with respect to the circulation about the longitudinal axis of the turbomachine in such a way that a sectional plane which includes the longitudinal axis of the turbomachine both the first and also the second sealing structure intersects,
as well as to the other
a seal carrier according to claim 9, wherein the first and the second sealing structure abut each other.

Preferred embodiments can be found in the present description and the dependent claims, wherein in the representation of the features is not always distinguished in detail between process and device or use aspects; In any case, implicitly, the disclosure must be read with regard to all categories of claims. In particular, all information taken about a seal carrier can also be read on a turbomachine, in particular a jet engine, with such a seal carrier.

The two solution variants, ie the "entanglement" of the sealing structures according to claim 1 or their "contact" to each other according to claim 9, is based on the same inventive idea, namely to extend or block the flow path between the sealing structures. By increasing the flow resistance, the sealing effect can be improved and thus achieve a higher efficiency. If, in contrast to the object according to the invention, sealing element segments according to the prior art are combined, a parting line between the sealing structures is generally located between the sealing structures with a size of between 0.3 mm and 0.4 mm (taken in the direction of rotation) and continuous axially in an axial direction extends. This causes leaks and loss of efficiency result.

According to the invention this is avoided by the sealing structures are entangled with each other or abut each other, the latter at least in the hot state, preferably also already in the cold state. Compared to the comparison case of an axially straight line continuously extending parting line, the flow path is thus at least extended. The specified in claim 1 "cutting plane", which includes the longitudinal axis of the turbomachine (hereinafter also "turbomachine longitudinal axis"), that extends axially and radially, intersects both the first and the second sealing structure due to the entanglement. This is then usually the case for all cutting planes each containing the turbomachine longitudinal axis, which lie within a certain circulation angle interval which, for example, lies above at least 0.01 °, 0.03 ° or 0.05 ° and (independently of this) z. B. not more than 1 °, 0.8 ° or 0.5 ° can extend (each in the order of Naming increasingly preferred). In contrast, the axially rectilinear parting line, however, there is no single such cutting plane that cuts both sealing structures at the same time (but intersect corresponding levels either one or the other sealing structure or lie in between).

The first and the second seal carrier segment may preferably each be a half-shell, see below. Preferably there is then not only a flow-optimized transition through the entanglement or the system, but also the second transition between the sealing structures of the half-shells is optimized, preferably analogous to the first (ie the two transitions are then optimized either by the entanglement or the system) , Quite generally, in the seal carrier, preferably all transitions between circumferentially successive sealing structures, which are respectively assigned to different seal carrier segments, are flow-optimized in the manner according to the invention.

In general, within the scope of these disclosures, "a" and "an" are to be read as indefinite articles, that is to say without expressly indicating otherwise also as "at least one" or "at least one". Thus, for example, as explained above, several cutting planes can fulfill the main criterion, or several transitions of the seal carrier can be correspondingly optimized in terms of flow. The turbomachine can then have, for example, a plurality of correspondingly designed seal carrier.

The seal carrier is "composed" of the seal carrier segments, the latter are thus previously made separately for each separately and then assembled. The assembly can generally be made cohesively, for example by welding or soldering, such as inductive soldering. Preferably may be a seal carrier, which is composed of two seal carrier half-shells, which are assembled together only form-fitting and / or non-positively. The seal carrier half-shells can, however, for example, in turn be constructed in each case from a plurality of seal carrier segments which are materially connected to each seal carrier half-shell, in particular soldered, preferably each of three seal carrier segments. Both transitions are preferred between the seal carrier half-shells as well as those within a respective half-shell in accordance with the invention flow-optimized. The production of the seal carrier segments is preferably generative, that is to say by selective solidification of a shapeless or shape-neutral material, see below in detail. With the generative structure, the interlacing or investment structures can be generated particularly well.

The variant "Entanglement" will now be explained in detail below.

In a preferred embodiment, has a parting line between the first and the second sealing structure seen in the radial direction, looking approximately radially from the turbomachine longitudinal axis thereon, at least in sections an angled to the axial direction course. In other words, the parting line should not extend axially straight through, but for example. A step shape, with one or more stages, or even have a curved course, so describe a waveform (in the sense of a continuously differentiable curve).

Independently of this, the flow path between the sealing structures is lengthened by the course, which is angled at least in sections, that is to say in any case in an axial section, to the axial direction. "Angled" may mean, for example, an angle of 90 °, for example in the case of a pure step shape, also in conjunction with an otherwise axis-parallel extent; On the other hand, any angle smaller than 90 ° are possible (considered always the smallest included with the axial direction angle), wherein the angle over the axial extent of the parting line can also change. Radially, the parting line can extend at least in sections angled to the radial direction; However, preferred is a parting line with a straight line in the radial direction, only radial extent.

As far as generally referred to in the context of this disclosure to an arrangement "axial" or an "axial direction", this refers to the turbomachine longitudinal axis. In the turbomachine, the "turbomachine longitudinal axis" is then, for example, an axis of rotation about which the rotor blade ring arranged in the seal carrier is rotatably mounted. Also "radial" or the "radial direction" refer to the turbomachine longitudinal axis, namely, are perpendicular to it. Similarly, "circulation" and "circulation direction" refer to it, namely to a circulation around the turbomachine longitudinal axis as a rotation axis.

In general, the sealing structures preferably form a cavity structure with a plurality of cavities axially and circumferentially separated from one another via cavity walls. Although the cavities are enclosed axially and circumferentially by the cavity walls and are preferably closed radially outward, to the turbomachine longitudinal axis, ie radially inward, they are open. As the cavity structure, a honeycomb structure may be preferable. The cavities delimited by the cavity walls then each have a hexagonal shape when viewed in the radial direction. However, this is generally not mandatory. As far as generally "axially and circumferentially" on the cavity walls separate and thus successive cavities reference is made, this means that a part of the cavities axially and another part circumferentially following each other, depending on the shape and arrangement some cavities actually at the same time can follow each other axially and circumferentially.

In a preferred embodiment, which relates to the parting line with at least partially angled extension, the parting line passes through at least one of the cavities. This at least one cavity is then formed jointly by the first and the second sealing structure, the sealing structures are at the parting line to each other so at least partially open (relative to the direction of rotation).

In another preferred embodiment, the sealing structures are closed at the parting line to each other, so the parting line is circumferentially enclosed on both sides of separating gap side cavity walls of the two sealing structures over its entire extent. In other words, it is at least in sections angled extending parting line inserted into the cavity structure such that it extends between the cavities of the sealing structures and thereby passes through any of the cavities. Starting from an uninterrupted cavity structure conceived between the sealing structures, the parting line is thus laid exclusively along cavity walls through the structure.

In a preferred embodiment, the cavities are arranged regularly at least in the direction of rotation, even beyond the parting line. As a result of the "regular" arrangement, a specific sequence of differently shaped and / or arranged cavities may occur periodically, ie repeatedly, over the course of time, in general, for example. Preferably, exactly one type cavity (a shape) is repeated over the revolution, and more preferably circumferentially in equidistant arrangement and alignment (the arrangement is rotationally symmetric with a certain number of counts). Preferably, the cavities are also regularly arranged in the axial direction, that is to say that the same type of cavity is particularly preferably repeated in the axial direction in an equidistant arrangement.

Preferably, the cavities, as seen in the radial direction, each have a polygonal outer shape, particularly preferably a hexagonal shape (honeycomb shape). In the case of sealing structures closed to one another at the parting line, the parting line can then extend along two side edges for each adjacent honeycomb, ie, describe a zig-zag line.

In a preferred embodiment, the sealing structures are entangled with one another such that a cavity wall of the first sealing structure extends in the circumferential direction into the second sealing structure. This cavity wall of the first sealing structure is then arranged axially between cavity walls of the second sealing structure, but preferably also axially spaced therefrom. A cavity wall of the second sealing structure preferably also extends in the direction of rotation into the first sealing structure (and is arranged axially between cavity walls of the first sealing structure). More preferably, each sealing structure has a respective plurality of cavity walls extending in the direction of rotation into the respective other sealing structure. Especially preferred are the corresponding ones Cavity walls of the two sealing structures in the axial direction alternately to each other, the cutting plane is thus interspersed alternately by a respective cavity wall of the first and the second sealing structure. Also independently of this, in particular, "extending in the circumferential direction" of the respective cavity wall does not necessarily imply an extension exclusively in the circumferential direction, although this is preferred (looking radially in a view therefrom).

In a preferred embodiment ends or end in the respective other sealing structure reaching (s) cavity wall or walls in the respective other sealing structure in each case to the cavity walls. Despite the entanglement thus remains between the cavity walls of the first and the second sealing structure nevertheless a certain amount of play. This can be advantageous, for example, with regard to sometimes large temperature differences that can occur between the operating and the off-state. Despite a possible, due to the temperature differences occurring relative offset thus tension can be prevented.

In a preferred embodiment, a cavity wall of the first sealing structure merges into a cavity wall of the second sealing structure at the sectional plane, namely the two cavity walls together form a positive connection with one another. This positive engagement is intended to block relative displacement with respect to the axial direction, generally only with respect to one of the axial directions, but preferably with respect to both opposite axial directions.

In a preferred embodiment, the intermeshing cavity walls are nut and spring-like composite, thus forming one of the cavity walls at its circumferential end a groove into which the other cavity wall is inserted with its circumferential end. Their longitudinal extent, the groove base and the spring in this case each have substantially in the radial direction. Although the form-fitting blocks an axial relative offset, there may still be a certain amount of play in the direction of rotation for the reasons described above, so that the spring does not necessarily have to reach the bottom of the groove, at least in the cold state.

Hereinafter, the abutting sealing structures will be further explained in detail.

In a preferred embodiment, the first sealing structure has a spring element and rests with this spring element on the second sealing structure. The spring element forms a contact surface, which is mounted elastically displaceable as a result of the spring property in the direction of rotation. This "elastic-displaceable-bearing-being" goes beyond a material inherent, beyond the E-modulus detected elasticity, namely, for example, supported by an at least partially or partially cantilever designed spring element geometry. Seen in the radial direction, the spring element can, for example, have a clasp or bridge shape. Preferably, the second sealing structure on a spring element, which forms an elastically displaceably mounted bearing surface, wherein the two sealing structures then abut each other with their spring elements.

The provision of an elastically mounted contact surface may be of interest with a view to a certain offset compensation, cf. also the comments above. Ideally, a seal carrier can be realized in which the sealing structures lie against one another in both the cold and the hot state, without material-critical strains.

In a preferred embodiment, the spring element is slidably mounted with a storage area in the remaining sealing structure, wherein the offset of the contact surface in the direction of rotation is proportionately converted into a displacement of the storage area. In general, the spring element can also be formed monolithically with the rest of the sealing structure at its opposite end, but preferably it has a further storage area, which is likewise displaceably mounted in the remaining sealing structure. Depending on the storage point, a relative mobility (of the storage point with respect to the remaining sealing structure) with at least one directional component in the axial direction results as a result of the "displaceably stored" being, preferably a total axially aligned displacement distance. Even independently of this, a corresponding sealing structure with a spring element can be generated generatively in a particularly advantageous manner produce, where the bearing is then, for example, partially constructed with a sacrificial material and the relative mobility is then given after its release.

In a preferred embodiment, which may be of interest both in the case of the "installation" and in the "entanglement", the seal carrier segments each have a support structure radially outside the respective sealing structure. The seal carrier segments are connected to each other via their support structures, in particular positive and / or non-positive, but apart from that, in their sealing structures movable relative to each other. Reference is made to the above information on offset compensation and its advantages.

In a preferred embodiment, the first seal carrier segment is a first seal carrier half-shell and the second seal carrier segment is a second seal carrier half-shell, see. also the comments at the beginning. Preferably, each of the seal carrier half shells circumferentially extends over 180 °. The seal carrier is then, based on the direction of rotation, composed exclusively of the two seal carrier half shells, these are positively and / or non-positively connected to each other, preferably exclusively positive and / or non-positive. In other words, form the two half-shells over the entire circulation the seal carrier, so there are in the seal carrier apart from the half-shells no further seal carrier segments.

As already mentioned, the seal carrier segments are each in a preferred embodiment for themselves generatively manufactured parts. In general terms, therefore, the parts are constructed on the basis of a data model from an informal or shape-neutral material which, for example, is converted selectively into regions in a dimensionally stable state by means of physical and / or chemical processes, for example by selective local melting. Accordingly, a wide range of different geometries can be produced, that is, for example, in the sealing structure, a spring element can be molded or can be realized in the circumferential direction protruding cavity walls, which then protrude into the other sealing structure after assembly. On the other hand, a support structure, which is then ideally constructed with the sealing structure in the same process, can be made to special structural mechanical requirements are optimized. Independently of this, in each case a construction of a powder bed may be preferred for the seal carrier segments, that is to say by layerwise selective solidification of a powder bed by appropriately selective irradiation, preferably by a laser beam.

As already mentioned, the invention also relates to a turbomachine with a presently disclosed seal carrier, in particular a jet engine.

Brief description of the drawings

In the following, the invention will be explained in more detail with reference to embodiments, wherein the individual features in the context of the independent claims in another combination may be essential to the invention and continue to distinguish not in detail between the different categories of claims.

Figur la-b

jeweils zwei Dichtstrukturen eines Dichtungsträgers, die in einer sich zumindest abschnittsweise gewinkelt erstreckenden Trennfuge aneinander grenzen und dabei zueinander hin geöffnet sind;

Figur 2

zwei Dichtstrukturen eines Dichtungsträgers, die in einer sich gewinkelt zur axialen Richtung erstreckenden Trennfuge aneinander grenzen und dabei zueinander hin geschlossen sind;

Figur 3

zwei Dichtstrukturen eines Dichtungsträgers mit einer Hohlraumstruktur, deren Hohlraumwände wechselseitig in die jeweilig andere Dichtstruktur hineinreichen;

Figur 4

zwei Dichtstrukturen eines Dichtungsträgers mit einer Hohlraumstruktur, deren Hohlraumwände an einer Trennfuge zwischen den Dichtstrukturen formschlüssig ineinander übergehen;

Figur 5a, b

zwei Dichtstrukturen eines Dichtungsträgers, die mit Federelementen aneinander anliegen;

Figur 6

ein Strahltriebwerk mit einem Dichtungsträger in schematischer Ansicht.

Show in detail

Figure la-b

in each case two sealing structures of a seal carrier, which adjoin one another in an at least sectionally angled extending parting line and are thereby open towards each other;

FIG. 2

two sealing structures of a seal carrier, which adjoin each other in an angle to the axial direction extending parting line and are closed to each other;

FIG. 3

two sealing structures of a seal carrier with a cavity structure whose cavity walls mutually extend into the respective other sealing structure;

FIG. 4

two sealing structures of a seal carrier with a cavity structure whose cavity walls merge into one another in a form-fitting manner at a parting line between the sealing structures;

FIG. 5a, b

two sealing structures of a seal carrier, which bear against each other with spring elements;

FIG. 6

a jet engine with a seal carrier in a schematic view.

Preferred embodiment of the invention

The FIGS. 1a-c each illustrate a first sealing structure 1a and a second sealing structure 1b, looking radially to a turbomachine longitudinal axis 2 thereon. The sealing structures 1a, b are each part of a respective seal carrier half-shell (not shown in detail), the seal carrier half-shells are assembled into a seal carrier. For this purpose, the seal carrier half shells radially outside the respective sealing structure 1a, b each have a support structure, via which the half shells are connected to one another. The sealing structures 1a, b shown in the figures form the radially inner part of the seal carrier. Put simply, the seal carrier has an overall ring shape and limits the hot gas channel of a jet engine radially outward. In the jet engine, the seal carrier accommodates a blade ring, with its radially outer ends, the blades then strip along the sealing structure 1 shown in the figures, this is also referred to as inlet lining.

The first sealing structure 1a and the second sealing structure 1a form a cavity structure with a plurality of radially inwardly open, honeycomb-shaped cavities 3. Axially and in the direction of rotation 4, the cavities 3 via cavity walls 5 are separated from each other.

A parting line 6 runs between the first 1a and the second sealing structure. In the case of FIGS. 1a-c, the first 1a and the second sealing structure 1b are open at the parting line 6 towards each other. The parting line 6 thus passes through some of the cavities 3, the cavities 3 arranged on the parting line 6 are delimited both by cavities 5 of the first 1a and by the second sealing structure 1b. Incidentally, the figures la-c then differed in the course of the parting line. 6

So shows FIG. 1a a parting line 6 with a step, but apart from axis-parallel extension. In contrast, the parting line 6 according to FIG. 1b over its entire axial extent a curved course, the included with the axial direction angle changes over the axial extent. The parting line 6 of the embodiment according to Figure 1c Although considered by itself a straight line extension, but is tilted overall to the axial direction. Each of these embodiments is advantageous insofar as the parting line 6 is lengthened compared to a rectilinear and exclusively axially parallel extension, which lengthens the flow path accordingly and thus increases the flow resistance. This can improve the efficiency, cf. also the description introduction.

An improved efficiency also gives the embodiment according to FIG. 2 in which the parting line 6 describes a zig-zag line. In contrast to the embodiments according to the figures la-c, the first 1a and the second sealing structure 1b in this case, however, are closed to each other at the parting line 6. Thus, the parting line 6 does not penetrate any of the cavities 3. It is encircled on both sides by separating-cavity-side cavity walls 5aa, 5ba of the respective sealing structure 1a, b.

In the embodiment according to FIG. 3 An extension of the flow path between the sealing structures 1a, b is achieved by extending cavity walls 5ab of the first sealing structure 1a into the second sealing structure 1b and extending cavity walls 5bb of the second sealing structure 1b into the first sealing structure 1a. The flow path is thus extended labyrinth-like.

In the embodiment according to FIG. 4 Go cavity walls 5ac of the first sealing structure 1a form fit in cavity walls 5bc of the second sealing structure 1b over. For this purpose, the cavity walls engage 5ac, 5bc nut and spring into each other, which in the ideal case, a flow path between the sealing structures la, b can be completely blocked.

In all the previously described embodiments, the first 1a and the second sealing structure 1b were entangled with each other, so there is a sectional plane containing the turbomachine longitudinal axis 2 (the sectional plane extends axially and radially), which intersects both the first la and the second sealing structure 1b , In the illustrated embodiments, this cutting plane would be horizontal in the plane of the drawing and perpendicular thereto.

Also with the embodiment or the embodiments according to the FIGS. 5a, b an extension or blockage of the flow paths between the sealing structures 1a, b is achieved. In this case, however, the sealing structures abut one another, for which purpose they each have a spring element 50a, b. The spring elements 50a, b each form a contact surface 51a, b, so they rest against each other. Due to the resilient properties of the contact surfaces 51a, b mounted in the direction of rotation a bit far elastically displaceable, which allows an offset compensation, such as in the case of temperature fluctuations.

In the embodiment according to FIG. 5a the spring elements 50a, b are each axially end connected to the rest of the respective sealing structure 1a, b, between them they are designed to support the spring function cantilevered. In the embodiment according to FIG. 5b, the spring element 50a is mounted so as to be displaceable in the remaining sealing structure, with two bearing regions 50aa arranged at the axially opposite ends. If the abutment surface 51 is thus offset in the direction of rotation 4, a part of this offset is converted into a displacement of the bearing regions 50aa, ab.

FIG. 6 shows a turbomachine 60, namely a jet engine, in a schematic section, wherein the cutting plane includes the longitudinal axis 2 of the turbomachine 60. The turbomachine is functionally divided into compressor 60a, combustion chamber 60b and turbine 60c. The compressor 60a is constructed of a plurality of stages 61a, b, in each of which a blade ring follows a vane ring (not shown in detail). The turbine is also constructed in several stages, with only one blade ring 62 being shown for the sake of clarity. After radially outward, the blade ring 62 is bordered by a seal carrier 63, which is constructed in a manner described above. The blades therefore graze along the in FIG. 6 Not shown in detail sealing structure of the seal carrier 63. Also, the blade rings of the compressor 60a can each be enclosed by a seal carrier according to the invention, which is also not shown in detail. <B> LIST OF REFERENCES </ b> sealing structures 1a, b longitudinal axis 2 cavities 3 direction of rotation 4 cavity walls 5 parted side 5aa, ba, reaching into other sealing structures 5ab, bb merging into each other 5ac, bc parting line 6 spring elements 50a, b storage areas 50aa, off contact surfaces 51a, b flow machine 60 compressor 60a combustion chamber 60b turbine 60c compressor stages 61a, b Blade ring turbine 62 seal carrier 63

Claims (15)

1. Seal support (63) preferably for a jet engine in the form of a turbomachine (60), which seal support has a first and a second seal support segment, which seal support segments are assembled successively in relation to a circumference about a longitudinal axis (2) of the turbomachine (60), the first seal support segment having a first sealing structure (1a) radially inwardly and the second seal support segment having a second sealing structure (1b) radially inwardly in relation to the longitudinal axis (2) of the turbomachine (60), characterized in that the first (1a) and the second sealing structure (1b) of the seal support (63) are interlocked with one another in relation to the circumference such that a section plane which comprises the longitudinal axis (2) of the turbomachine (60) intersects both the first (1a) and the second sealing structure (1b).
2. Seal support (63) according to claim 1, wherein a parting line (6) extends in the circumferential direction (4) between the first (1a) and the second sealing structure (1b), which parting line extends over its axial extent so as to be angled to the axial direction at least in portions, when viewed in the radial direction.
3. Seal support (63) according to claim 2, wherein the first (1a) and the second sealing structure (1b) form a cavity structure having a plurality of cavities (3) which are axially and circumferentially separated from one another by cavity walls (5) of the particular sealing structure (1a, b), the parting line (6) passing through at least one of the cavities (3), the at least one cavity therefore being formed by the first (1a) and the second sealing structure (1b) together, and the sealing structures (1a, b) therefore being at least partially open toward one another at the parting line (6).
4. Seal support (63) according to claim 2, wherein the first (1a) and the second sealing structure (1b) form a cavity structure having a plurality of cavities (3) which are axially and circumferentially separated from one another by cavity walls (5) of the particular sealing structure (1a, b), the parting line (6) being completely delimited by parting-line-side cavity walls (5aa, ba), the sealing structures (1a, b) therefore being closed toward one another at the parting line (6).
5. Seal support (63) according to either claim 3 or claim 4, wherein the cavities (3) of the cavity structure are arranged regularly at least in the circumferential direction (4), and over the parting line (6).
6. Seal support (63) according to any of the preceding claims, wherein the first (1a) and the second sealing structure (1b) form a cavity structure having a plurality of cavities (3) which are axially and circumferentially separated from one another by cavity walls (5) of the particular sealing structure (1a, b), a cavity wall (5ab) of the first sealing structure (1a) projecting, at the section plane, in the circumferential direction (4) into the second sealing structure (1b), and therefore being arranged axially between cavity walls (3) of the second sealing structure (16).
7. Seal support (63) according to claim 6, wherein the cavity wall (5ab) of the first sealing structure (1a), which wall projects into the second sealing structure (1b), finishes in the second sealing structure (1b) spaced apart from the cavity walls (5) thereof.
8. Seal support (63) according to any of the preceding claims, wherein the first (1a) and the second sealing structure (1b) form a cavity structure having a plurality of cavities (3) which are axially and circumferentially separated from one another by cavity walls (5) of the particular sealing structure (1a, b), a cavity wall (5ac) of the first sealing structure (1a) transitioning, at the section plane, into a cavity wall (5bc) of the second sealing structure (1b), the two cavity walls (5ac, bc) together specifically forming a form fit, preferably mutually engaging in a tongue-and-groove manner.
9. Seal support (63) preferably for a jet engine in the form a turbomachine (60), which seal support has a first and a second seal support segment, which seal support segments are assembled successively in relation to a circumference about a longitudinal axis (2) of the turbomachine (60), the first seal support segment having a first sealing structure (1a) radially inwardly and the second seal support segment having a second sealing structure (1b) radially inwardly in relation to the longitudinal axis (2) of the turbomachine (60), characterized in that the first (1a) and the second sealing structure (1b) abut one another.
10. Seal support (63) according to claim 9, wherein the first sealing structure (1a) has a tongue element (50a) and abuts the second sealing structure (1b) using said tongue element (50a), which tongue element (50a) therefore forms an abutment surface (51a) which is mounted so as to be elastically displaceable in the circumferential direction (4).
11. Seal support (63) according to claim 10, wherein a mounting region (50aa, ab) of the tongue element (50a) is slidably mounted in the remaining first sealing structure (1a) such that the elastically mounted displacement of the abutment surface (5a) in the circumferential direction (4) is partially converted into a displacement of the mounting region (50aa, ab).
12. Seal support (63) according to any of the preceding claims, wherein, in relation to the longitudinal axis (2) of the turbomachine (60), the first seal support segment has a first support structure radially outside of the first sealing structure (1a) and the second seal support segment has a second support structure radially outside of the second sealing structure (1b), the seal support shells being fastened to one another by the support structures, but nevertheless being movable relative to one another in the sealing structures (1a, b) thereof.
13. Seal support (63) according to any of the preceding claims, wherein the first seal support segment is a first seal support half-shell and the second seal support segment is a second seal support half-shell, the two seal support half-shells together forming the seal support (63) and being form-fittingly and/or force-fittingly assembled.
14. Seal support (63) according to any of the preceding claims, wherein the seal support segments are each rapidly manufactured parts.
15. Turbomachine (60), in particular a jet engine, having a seal support (63) according to any of the preceding claims.

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