EP3324002A1 - Axial turbomachine and sealing system for an axial turbomachine - Google Patents

Abstract

The invention relates to a sealing system (100) for an axial flow machine, in particular for a gas turbine, comprising an impeller (3) with a shroud (4) arranged radially on the outside and a housing (30) surrounding the impeller (3), between which Shroud (4) and the housing (30) a gap (6) is arranged, and wherein the gap (6) by means of a housing (30) connected to the seal (12) and at least one of the shroud (4), opposite the seal (12) arranged sealing tip (5) for reducing the flow losses through the gap (6) is limited. At the downstream end portion of the seal (12) is another static sealing tip (20) connected to the housing (30) for influencing the flow through the gap and / or influencing the flow downstream of the static sealing tip (20). Furthermore, the present invention relates to an axial flow machine, in particular a gas turbine, with at least one low-pressure turbine stage, wherein the low-pressure turbine stage comprises a sealing system (100) according to the invention.

Description

The present invention relates to a sealing system for an axial flow machine according to the preamble of claim 1. Furthermore, the present invention relates to an axial flow machine according to claim 14.

In axial flow machines, especially in multi-stage axial flow machines, the pressure in the working fluid (or fluid) changes from stage to stage. In a turbomachine designed as a gas turbine, the pressure in the compressor is usually downstream of a row of blades higher than the pressure upstream, in the turbine, however downstream of a row of blades less than the pressure upstream. To achieve high efficiency of the turbomachine, it is necessary that the working medium is passed through the blading of the individual stages, and not as a leakage flow (or bypass flow), with no work output, which bypasses rows of blades. For this purpose, a sealing system is provided in the region of an outer annular space boundary, which is designed for example as a labyrinth system.

Such sealing systems have the task of keeping a leakage current through a sealing gap between the rotating blading and a housing minimal and thus to allow a stable operating behavior with high efficiency. Usually, the rotating components of a turbine on sealing fins or sealing tips, which can strip or shrink against honeycomb seals. The seals are designed as a squint and inlet coverings. By minimizing the radial gaps above the sealing fins, it is attempted to minimize the leakage flows through the cavities in these regions, in particular in regions above shrouds of rotor blades and the resultant losses in efficiency. Nevertheless, when the leakage flow enters the so-called main flow of the turbomachine, mixing losses often occur due to different orientations and speeds of the main flow and the leakage flow.

An object of the present invention is to propose a further sealing system for an axial flow machine. It is another object of the present invention to provide an axial flow machine with a sealing system according to the invention.

The object of the invention is achieved by a sealing system having the features of claim 1. It is further achieved by an axial flow machine having the features of claim 14.

According to the invention, a sealing system for an axial flow machine is thus proposed which comprises at least one impeller with a shroud arranged radially on the outside and a housing surrounding the impeller. Between the shroud and the housing, a gap is arranged. The gap is bounded on the one hand by means of a seal connected to the housing and on the other hand by means of at least one sealing tip arranged on the cover band. This arranged on the shroud sealing tip can be referred to as a rotating sealing tip, as it rotates with the impeller. The seal is, viewed in the radial direction, arranged opposite the shroud. The limitation of the gap by the seal and the shroud can reduce the flow losses of the slit flow. At the downstream end portion of the housing-side seal another, connected to the housing, static sealing tip is arranged. By means of this static sealing tip, the flow through the gap is influenced, in particular reduced. Alternatively or additionally, the flow downstream of the static sealing tip is influenced by means of the static sealing tip.

An influence, in particular a reduction of the flow through the gap by means of the static sealing tip, can be caused by flow losses of the static sealing tip.

Alternatively or additionally, a possible vortex formation downstream of the static sealing tip can be influenced by the static sealing tip. The gap flow between the static sealing tip and the shroud may cause a vortex or vortex region downstream, the direction of rotation of which has primarily the same flow direction as the adjacent main flow. As a result, the flow losses and / or the disturbance of the main flow through these vortices can be reduced. This can advantageously increase the efficiency of the axial flow machine by the sealing system according to the invention.

A reduced main flow disturbance due to the described direction of rotation of the vortices may be referred to as a low loss mixing with the main flow. In contrast, can a sealing system without static sealing tip lead to a vortex formation whose primary direction of rotation is opposite to the main flow. This would lead to a lossy mixture with the main flow and could contribute to a reduction in the efficiency of the turbomachine.

The shroud arranged radially on the outside of the impeller can be referred to as an outer shroud or as a shovel outer shroud.

The arranged between the shroud and the housing gap may be referred to as a running gap.

The axial flow machine according to the invention comprises at least one low-pressure turbine stage with a sealing system according to the invention. The axial flow machine may further comprise at least one high-pressure turbine stage, a low-pressure compressor stage and a high-pressure compressor stage. Each of said stages may comprise a sealing system according to the invention.

The axial flow machine may be a gas turbine, in particular an aircraft gas turbine or an aircraft engine.

Advantageous developments of the present invention are the subject of subclaims and embodiments.

Inventive exemplary embodiments may have one or more of the following features.

A static and / or a circumferential sealing tip can be referred to as Dichtfin.

In some exemplary embodiments of the invention, the seal associated with the housing may be an inlet seal. An inlet seal can be called an abradable seal. An inlet seal may have an insertable coating or an insertable layer into which, for example, a sealing tip can penetrate to form a sealing gap. This sealing gap can be made small by the penetration or shrinkage of a sealing tip, in particular during an intended operating state and thus contribute advantageously to optimize the efficiency of the turbomachine. The inlet seal may comprise a honeycomb structure for penetrating a sealing tip.

The inlet seal may be connected to the housing cohesively and / or positively. The inlet seal may be glued, soldered, riveted or clamped, or otherwise attached to the housing.

In some exemplary embodiments of the invention, the inlet seal is attached only to the housing. In this embodiment, no inlet seal on the impeller, in particular attached to the shroud of the impeller. The inlet seal is thus arranged only on one side of the gap.

In some exemplary embodiments of the invention, the shroud may include at least two sealing tips. Two sealing tips can engage in two opposite inlet seals on the housing and form a sealing gap. The at least two sealing tips can be arranged axially one behind the other on a radius or at a radial height. Alternatively, the two sealing tips can be arranged axially one behind the other at different radii or at radially different heights, that is, offset radially.

In some exemplary embodiments of the invention, the shroud has no seal, in particular no inlet seal.

In some exemplary embodiments of the invention, the shroud has three or more sealing tips. The sealing tips may be arranged radially at a height or at different heights. For example, two axially successively arranged sealing tips have the same radius, whereas a third sealing tip is arranged radially further outside.

In some exemplary embodiments of the invention, the at least one sealing tip of the shroud is arranged inclined upstream. The angle of inclination between the radial direction and the axial direction may be, for example, at least 15 degrees. A non-sloped sealing tip in the radial direction would be zero degrees. An inclined sealing tip can favor the flow losses due to a smaller flow through the gap influence. An inclined sealing tip can also be advantageous in terms of the shroud configuration, for example, in an arrangement of multiple sealing tips on the shroud. Likewise, the structural strength of the shroud with an inclined sealing tip can be advantageously higher. In particular, the upstreammost sealing tip of the shroud can be inclined. The incline can be twenty degrees, twenty-five degrees, thirty degrees or more.

In some exemplary embodiments of the invention, the shroud has wear protection in the opposite region of the static sealing tip. The wear protection can advantageously prevent direct contact of the static sealing tip with the base material of the shroud. Direct contact could damage the shroud causing more damage.

In some exemplary embodiments of the invention, the wear protection of the shroud extends beyond the opposite region of the static sealing tip, in particular at least to the adjacent shroud end. The wear protection can extend over more area of the shroud.

In some exemplary embodiments according to the invention, the wear protection is a, at least in sections, coating of the shroud. Alternatively, the wear-resistant layer can also be understood as a flake-like element fastened to the shroud in a material- and / or non-positive manner, for example of a material with the trade name "stellite".

In some exemplary embodiments according to the invention, the wear protection is arranged in regions over the circumference of the shroud. For example, the wear protection can be arranged only at individual points of the shroud.

In some exemplary embodiments of the invention, the material of the static sealing tip has a lower hardness than the hardness of the wear protection layer. The hardness of the material can be a measure of the resistance of the material to wear. The material of the wear protection layer preferably differs from the base material of the shroud and, in particular, also has a greater hardness relative to this base material. By the term "greater hardness" in the sense of the present invention is meant in particular a "greater wear resistance".

In some exemplary embodiments of the invention, the wear protection is superior to the rest of the shroud surface, or in other words, the height of the wear protection extends beyond the surface of the shroud. The wear protection thickness can have, for example, 5 μm, 10 μm, 20 μm or another thickness.

In some exemplary embodiments according to the invention, a wear protection is produced by means of a local surface layer hardening, in particular by means of a laser-supported method.

In some exemplary embodiments according to the invention, the static sealing tip is fastened to the housing with a positive-locking component, in particular a holding element. The static sealing tip can be materially connected to the holding element.

In some exemplary embodiments of the invention, the static sealing tip is secured to the housing with a positive fit component, particularly a retainer, on the downstream baffle, or the baffle connection. The static sealing tip can be materially connected to the holding element.

In some exemplary embodiments of the invention, the impeller is a turbine runner, particularly a low-pressure turbine runner.

In some exemplary embodiments of the invention, the shroud is segmented about the circumference of the impeller. In particular, the segments are designed as z-shroud segments. By means of z-shroud segments, the impeller blades can advantageously be braced with one another.

In some exemplary embodiments according to the invention, the contact regions of the shroud segments have wear protection in the circumferential direction. This wear protection can be designed as wear protection in the opposite region of the static sealing tip. In particular, this wear protection projects as a wear protection layer beyond the shroud surface, so that in the event of contact of the static sealing tip with the shroud, initially only the wear protection layer touches becomes. In particular, the hardness of the wear protection layer is greater than the hardness of the static sealing tip. This advantageously allows the shroud to be protected from contact with the static sealing tip. Such contact could damage the shroud.

The wear protection can be integrally connected to the shroud, for example by means of welding (for example by laser deposition welding). The material of the wear protection can be a cobalt-based hard alloy, for example a cobalt-chromium alloy, or have such. The hardness of the wear-resistant coating can be greater than 600 Vickers hardness (HV for short) purely by way of example.

In some exemplary embodiments according to the invention, the static sealing tip is connected in a form-fitting and / or material-locking manner to the housing by means of a holding element.

In some exemplary embodiments according to the invention, the static sealing tip on the side opposite the shroud has a circumferentially variable, in particular wave-shaped structure. By means of the variable or wave-like structure, when the sealing tip contacts the shroud, or with a wear protection layer on the shroud, an axially larger area of a contact surface of the sealing tip can be used in comparison with a non-variable or wavy, ie straight, structure over the circumference. By means of an axially larger region of the contact surface, the heat input during a contact process or a rubbing process between the sealing tip and the shroud (or the wear protection layer) can advantageously be distributed over a larger area and a larger volume of material. As a result, the load, in particular the thermal material stress, of the wear protection layer can be locally reduced.

Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.

By means of the sealing system according to the invention, the leakages, that is to say the bypass flow or the gap flow, can advantageously be reduced. The leaks can be referred to as primary losses. In particular, by means of the static sealing tip, the gap flow can be reduced.

Furthermore, by means of the sealing system according to the invention, the main flow less disturbed and thus the efficiency of the turbomachine can be increased. The disturbances of the main flow can be called secondary losses. In particular, the vortex formation can be influenced downstream of the static sealing tip and thus the vortex rotation direction of the main flow direction can be adjusted. As a result, a low-loss mixture of the vortices resulting from the slit flow can be achieved with the main flow.

Fig. 1

zeigt ein aus dem Stand der Technik bekanntes Dichtungssystem einer Turbinenstufe mit einer Einlaufdichtung und zwei umlaufenden Dichtspitzen im Längsschnitt;

Fig. 2

zeigt ein erfindungsgemäßes Dichtungssystem einer Turbinenstufe mit einer Einlaufdichtung, zwei umlaufenden Dichtspitzen und einer mit einem Gehäuse verbundenen statischen Dichtspitze im Längsschnitt;

Fig. 3

zeigt das erfindungsgemäße Dichtungssystem in einer Querschnittsebene mit der statischen Dichtspitze, einem Laufrad mit Deckband und einer Verschleißschutzschicht zwischen zwei Deckbandsegmenten;

Fig. 4

zeigt das Deckband in einer Ansicht von radial außen mit zwei Verschleißschutzschichten; und

Fig. 5a,b

zeigen zwei unterschiedliche Verläufe einer Innenkante der statischen Dichtspitze in Umfangsrichtung.

The present invention will be explained in the following with reference to the accompanying drawings, in which identical reference numerals designate identical or similar components, by way of example. In each case greatly simplified schematic figures:

Fig. 1

shows a known from the prior art sealing system of a turbine stage with an inlet seal and two circumferential sealing tips in longitudinal section;

Fig. 2

shows a sealing system according to the invention a turbine stage with an inlet seal, two circumferential sealing tips and connected to a housing static sealing tip in longitudinal section;

Fig. 3

shows the sealing system according to the invention in a cross-sectional plane with the static sealing tip, an impeller with shroud and a wear protection layer between two shroud segments;

Fig. 4

shows the shroud in a view from the radially outside with two wear protection layers; and

Fig. 5a, b

show two different courses of an inner edge of the static sealing tip in the circumferential direction.

Fig. 1 shows a known from the prior art sealing system 100 'of a turbine stage with an inlet seal 12 and two rotating (rotating) sealing tips 5 in longitudinal section. A sealing system 100 'may be synonymously referred to as a sealing system. The inlet seal 12 may be referred to as inlet lining.

Between an upstream stator 1 and a downstream stator 2, a housing portion 10 is shown on the housing side, in which a seal carrier 11 is mounted. The housing portion 10 could also be referred to as a static sealing part. On the seal carrier 11, the inlet seal 12 is fixed, for example, materially by means of soldering or gluing. In the inlet seal 12 engage two sealing tips 5, which can be referred to as sealing fins. A running gap 6 between the inlet seal 12 and the sealing tips 5 is generated or generated by means of shrinkage or cutting in of the sealing tips 5. The sealing tips 5 are arranged on a radially outer shroud 4, which in turn is connected to an impeller 3. The shroud 4 may be integrally connected to the impeller 3, for example by means of a laser sintering process.

The flow direction of a leakage flow (the leakage flow may be referred to as a split flow or bypass flow) is shown by the arrow of the reference numeral 6 of the nip 6. In a turbine stage shown here, the pressure of the flow medium in the flow direction of the main flow H, in Fig. 1 from left to right, from. Consequently, the pressure upstream of the blade 3 is higher than the pressure downstream of the blade 3. Thus, the flow direction is in the arrow direction of the reference character of the nip 6.

Downstream of the second sealing tip 5 (in Fig. 1 right), the leakage flow forms a vortex W. At the mixing point with the main flow H, high mixing losses result since the direction of rotation of the vortex W results in a flow whose direction of flow of the main flow H is opposite.

Furthermore, a stiffening structure 13 is optionally shown on the shroud 4.

The moving blade 3 is unambiguously positioned with respect to the inlet seal 12, and thus with respect to the surrounding housing 30 and the guide wheels 1, 2, which may be referred to as stator. However, the rotor connected to the impeller 3 (in Fig. 1 not shown) move axially within certain limits relative to the stator, for example due to a play of the bearings, thermal expansions and other factors. Due to these axial movements of the rotor and the impeller 3, only a few sealing tips 5 can be arranged on the shroud 4. In the embodiment of Fig. 1 are two sealing tips 5 are arranged as an example. Due to this limited number of sealing tips 5, the sealing effect, depending on the running gap 6, limited.

Fig. 2 shows a sealing system according to the invention 100 a turbine stage with an inlet seal 12, two circumferential sealing tips 5 and connected to a housing 30 static sealing tip 20 in longitudinal section.

The arrangement of the upstream stator 1, the downstream stator 2, the blade 3, the housing portion 10 and the seal carrier 11 (which is shown in FIG Fig. 2 designed differently than in Fig. 1 ) is analogous to the description of Fig. 1 , The two rotating sealing tips 5 are axially offset on the shroud 5 relative to the arrangement of Fig. 1 arranged. In addition, a case-side static sealing tip 20 is installed opposite to the downstream end portion of the shroud 4. The static sealing tip 20 is in the exemplary embodiment of Fig. 2 fixed by means of a holding element 21 on the static housing section 10 and the housing-side holder of the downstream stator 2. The fixation can be designed as a clamp. An additional cohesive fixation of the static sealing tip 20 on the holding element 21 and / or of the holding element 21 on the housing section 10, for example by means of a soldered or welded connection, is optionally possible.

Furthermore, in Fig. 2 a so-called Raumbegrenzer 22 introduced into the housing 30 inside. The room delimiter 22 can for example contribute to the reduction of flow losses.

The additional static sealing tip 20 can advantageously reduce the leakage resulting from the running gap 6. Furthermore, the direction of rotation of the downstream of the static sealing tip 20 forming vortex W with respect to the direction of rotation of the sealing system 100 'from the Fig. 1 reverse, so that a low-loss mixture with the main flow H is advantageously possible. The low-loss mixture with the main flow H is through the same parallel flow direction of the main flow H with the flow direction of the immediately emerging vortex in Fig. 2 shown. Due to these two effects of the static sealing tip 20, reduction of the leakage and low-loss mixing of the vortex W with the main flow H, the total losses of the turbine stage can be advantageously reduced.

The static sealing tip 20, together with the rear portion of the shroud 4, an additional sealing point to the two sealing points formed by the sealing tips 5 and the inlet seal 12.

The front upstream seal tip 5 is inclined, with respect to the radial direction r, against the main flow direction aligned in the axial direction. The inclination is about 30 degrees. By means of an inclined sealing tip 5, for example, the leakage flow can be influenced by the running gap 6.

The two sealing tips 5 are arranged radially offset and thus approximately form the widening flow channel of the turbine stage.

The shroud 4 is executed segmented over the circumference u. The segments are often executed as so-called z-shrouds (see Fig. 4 that look as View B Fig. 2 is shown), since their peripheral edges are not rectilinear in the axial direction of the turbomachine, but are formed substantially z-fömig. With this z-shape, it is possible to clamp in the mounted state, the circumferentially adjacent blades 3 a rotor stage with each other. In the view of Fig. 2 one looks orthogonally on the peripheral edge of a segment of the shroud 4. The downstream half of this peripheral edge is provided with a wear protection layer 8, which in the Figures 2 . 3 and 4 is shown dark. The wear protection view 8 is applied in the axial direction of the turbomachine not only in the central region of the z-fömigen peripheral edge of the shroud 4, in which by contact substantially the bracing forces between two circumferentially adjacent blades 3 are transmitted to the shroud 4, but the wear protection layer extends axially even further to the rear. In particular, the wear protection layer 8 extends in the axial direction of the turbomachine at least up to the axial position of the static sealing tip 20 to the rear. In the present embodiment, the wear protection layer 8 extends even to the downstream end of the shroud. 4

In the radial direction r, the wear protection layer 8 projects beyond the surface of the shroud 4. This has the advantage that in case of an unwanted contact of the static sealing tip 20 with the shroud 4, for example in the case of a hard landing of an aircraft provided with the turbomachine as an engine, the static sealing tip 20 does not If the material of the wear protection layer 8 has a higher hardness than the material of the static sealing tip 20, the static sealing tip 20 is removed from the rotating impeller 3 or abraded. The static sealing tip 20 may be slightly shortened, for example, in the radial direction r. In this way, damage to the impeller 3 is prevented. A grinding of the static sealing tip 20 through the wear protection layer 8, however, is much less critical and the static sealing tip 20 can also be replaced relatively easily and inexpensively.

Fig. 3 shows the sealing system 100 according to the invention in a cross-sectional plane (section A - A, see Fig. 2 ) with the static sealing tip 20, the seal carrier 11, the impeller 3 with shroud 4 and a wear protection layer 8 between the shroud segments.

The shroud 4 is segmented. The so-called z-shroud has wear protection layers 7, 8 at the contact points of the abutting segments. In particular, the wear protection layer 8, which extends in the axial direction further downstream than the wear protection layer 7, projects slightly beyond the radial extent of the shroud surface. In Fig. 3 this is represented by the heel height 23. Due to this increase of the wear protection layer 8 over the surface of the shroud 4, the static sealing tip 20, for example, in the aforementioned case, first the increased wear protection layer 8 touched at a lower hardness of the material of the static sealing tip 20 against the hardness of the material of the wear protection layer 8 the static sealing tip 20 ground or deformed, but without touching the shroud 4 itself and damage. In other words, the wear-resistant layer 8 used for the contact of two circumferentially adjacent shrouds 4 can be synergistically used here in order to prevent possible damage to the base material of the shroud 4 by contact with the static sealing tip 20. For this purpose, the wear protection layer 8 in the axial and radial directions of the turbomachine is to be dimensioned only slightly larger than would otherwise be the case.

Fig. 4 shows the shroud 4 in a view B from the radial outside (see Fig. 2 ) with the wear protection layers 7, 8. The profile shape of the blade shape of the impeller 3 is schematically indicated below the shroud.

The sealing tips 5 of the shroud 4 project out of the plane of representation. The wear protection layers 7, 8 are located at the contact surfaces of the z-shroud to the circumferentially adjacent (not shown) segments of other bucket cover strips. The shaded anti-wear layer 8 was already in the cutting plane of Fig. 2 opposite the static sealing tip 20.

Fig. 5a, b show two different courses of the radially inner edge, or inner edge of the static sealing tip 20 in the circumferential direction u in a view C (see Fig. 3 ). In Fig. 5a is a straight waveform and shown in Fig. 5b a waveform. The waveform has the advantage that in the case of contact of the static sealing tip 20 with the wear protection layer 8 of the shroud 4, an axially larger area of the wear protection layer 8 for a grinding or deformation of the static sealing tip 20 is available. As a result, upon contact of the static sealing tip 20 with the wear protection layer 8, the heat input is distributed over a larger volume of material, as a result of which the wear protection layer 8 is loaded less locally.

LIST OF REFERENCE NUMBERS

a

axially; axially

r

radial; radial direction

u

circumferentially

H

Flow direction, main flow

W

whirl

100, 100 '

sealing system

1

upstream stator

2

downstream stator

3

Impeller, blade

4

shroud

5

Sealing tip of the shroud

6

running gap

7, 8, 13

wear protection

10

Housing section (static seal part)

11

seal carrier

12

Inlet seal, inlet lining

20

static sealing tip

21

retaining element

22

Raumbegrenzer

23

Heel height of the wear protection layer

30

casing

Claims (15)

Sealing system (100) for an axial flow machine, in particular for a gas turbine, comprising an impeller (3) with a radially outer shroud (4) and a surrounding the impeller (3) housing (30), wherein between the shroud (4) and the housing (30) a gap (6) is arranged, and wherein the gap (6) by means of a housing (30) connected to the seal (12) and at least one on the shroud (4), with respect to the seal (12) arranged sealing tip (5) is limited to reduce the flow losses through the gap (6),
characterized in that
another static sealing tip (20) connected to the housing (30) for influencing the flow through the gap and / or for influencing the flow downstream of the static sealing tip (20) is arranged at the downstream end region of the seal (12). The sealing system (100) of claim 1, wherein the seal (12) is an inlet seal (12). Sealing system (100) according to claim 1 or 2, wherein the shroud (4) has at least two sealing tips (5). Sealing system (100) according to one of the preceding claims, wherein the at least one sealing tip (5) of the shroud (4) is inclined upstream. A sealing system (100) according to the preceding claim, wherein the angle (w) between the radial direction (r) and the axial direction (a) is at least 15 degrees. Sealing system (100) according to one of the preceding claims, wherein the shroud (4) in the radial direction (r) opposite region of the static sealing tip (20) has a wear protection (8). Sealing system (100) according to the preceding claim, wherein the wear protection (8) is a coating of the shroud (4). Sealing system (100) according to one of the two preceding claims, wherein the material of the static sealing tip (20) has a lower hardness compared to the hardness of the wear protection layer (8). Sealing system (100) according to one of the preceding claims, wherein the impeller (3) is a turbine runner, in particular a low-pressure turbine runner. Sealing system (100) according to one of the preceding claims, wherein the shroud (4) over the circumference (u) of the impeller (3) is segmented. Sealing system (100) according to the preceding claim, wherein the contact areas of the segments (13) in the circumferential direction (u) have the wear protection (8). Sealing system (100) according to one of the preceding claims, wherein the static sealing tip (20) by means of a holding element (21) is positively and / or materially connected to the housing (30). Sealing system (100) according to any one of the preceding claims, wherein the static sealing tip (20) on the side opposite the shroud (4) side in the circumferential direction (u) varying, in particular wave-shaped structure (15). An axial flow machine, in particular a gas turbine, with at least one low-pressure turbine stage, wherein the low-pressure turbine stage comprises a sealing system (100) according to one of the preceding claims. Axial flow machine according to the preceding claim, wherein the turbomachine is an aircraft engine.

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