Sealing assembly for a flow machine, sealing support element for the sealing assembly, guide vane element and turbomachine

Abstract

The invention relates to a sealing arrangement 10 for a turbomachine, comprising a sealing carrier element 60, an integral ring body element 70, and at least three projections 80. The guide vane element 20 has an opening 32, which points radially inwards, for receiving a projection 80 of the sealing carrier element 60 for spoke centering and a sealing rib 22 extending radially inwards. In the operating state during sealing contact, each projection 80 is movably received in the respective opening 32 in the axial direction A. Either the sealing carrier element 60 has a sealing carrier web 36 extending in the circumferential direction U with a sealing surface 24 pointing towards the sealing web 22 which is offset in the axial direction, or the sealing web 22 extending in the circumferential direction U of the guide vane element 20 has a sealing surface 24 pointing towards the sealing carrier web 36 which is offset relative to an axially rear surface 38 of the opening 32.

Description

[0001] The invention relates to a sealing arrangement for a turbomachine comprising a seal carrier element and a guide vane element. Further aspects of the invention relate to a seal carrier element and a guide vane element for the sealing arrangement, as well as a turbomachine.

[0002] To optimize the efficiency of turbomachinery, such as gas turbines, it is particularly advantageous to minimize leakage between a rotating rotor and the stationary sealing assembly. This involves sealing a leakage gap between the radially inner ends of stationary guide vanes and the rotating rotor. The sealing component is secured to the guide vane element by a sliding block, for example, fastened with a rivet or bolt. A sealing component for sealing the leakage gap between the radially inner ends of the stationary guide vanes and the rotating rotor can also be referred to as an "inner air seal."

[0003] The object of the present invention is to create a sealing arrangement, a sealing support element and a turbomachine of the type mentioned above, which have a particularly low weight and can be manufactured with minimal effort.

[0004] This problem is solved by a sealing arrangement with the features of claim 1, by a sealing support element with the features of claim 9, by a guide vane element with the features of claim 10, and by a turbomachine with the features of claim 11. Advantageous embodiments with expedient further developments of the invention are specified in the respective dependent claims.

[0005] A first aspect of the invention relates to a sealing arrangement for a turbomachine, comprising a seal carrier element and a guide vane element. The seal carrier element has an inlet lining at a radially inner end, an integral ring body element, and at least three projections for radially centering the seal carrier element within guide vane elements. The guide vane elements have at least three openings for the at least three projections, and the spoke centering is achieved by means of radial guides for the at least three projections in the at least three openings, each projection having a front surface and a rear surface in the flow direction.

[0006] The guide vane element has an opening, which points radially inwards, to receive a projection of at least three projections of the sealing carrier element for spoke centering. Furthermore, the guide vane element has a sealing rib extending radially inwards, which forms the radially innermost section of the guide vane element.

[0007] In the operating state, or when a sealing contact exists between the sealing carrier element and the guide vane element or between their sealing surfaces, each projection of the at least three projections of the sealing carrier element is received in a respective opening of the guide vane element and is thereby movably in the axial direction and / or, in particular, is received with clearance on both sides.

[0008] In particular, each of the at least three projections has an axial clearance to an axially front or rear surface of the opening on both the upstream and downstream sides and / or is axially spaced from these surfaces on both the upstream and downstream sides.

[0009] Furthermore, as a first alternative, the sealing carrier element has a circumferentially extending sealing carrier web with a sealing surface facing the sealing web (of the guide vane element), which is offset in the axial direction, particularly downstream, relative to both the axially front and the axially rear surfaces of the projections.

[0010] Alternatively or additionally, as a second alternative, which may but does not have to be combined with the first alternative, the circumferentially extending sealing rib of the guide vane element has a sealing surface facing the sealing carrier rib, which is offset in the axial direction, particularly upstream, relative to an axially rear surface of the opening.

[0011] The guide vane element can be designed, in particular, as a blade and can be referred to as a guide vane. The sealing component can be designed to seal a leakage gap between the guide vane element and a rotor, in particular the rotor blades of the turbomachine. The sealing component can also be referred to as an "inner air seal" or "IAS." For this purpose, the sealing component can include an inlet lining. The inlet lining can limit the leakage gap in the radial direction of the sealing arrangement. Thus, during normal use of the sealing arrangement, the inlet lining can directly adjoin the leakage gap in the radial direction of the sealing arrangement. Furthermore, other elements or components, such as air deflectors or flow guides, can be attached to the sealing component.

[0012] According to the invention, the sealing support element comprises an annular body element and at least three projections, which are integrally, in particular integrally, monolithically and / or in one piece, connected to the annular body element, project from the annular body element in the radial direction of the sealing arrangement, and are each inserted into at least one opening of the guide vane element. This is particularly advantageous because the one-piece connection between the annular body element and the at least three projections means that very few individual parts are required for assembling the sealing arrangement, thus enabling particularly cost-effective manufacturing of the sealing arrangement. The sealing support element can also be referred to as a sealing support ring. The at least three projections can, in particular, project radially, i.e., in the radial direction of the sealing arrangement, from the annular body. Each projection can also be referred to as a nose or spoke.

[0013] In a preferred embodiment, the projections border the sealing support web in a radial direction, in particular directly, and / or are integrally, in particular in one piece, connected monolithically and / or integrally with the sealing support web.

[0014] The projections and the sealing support web can be aligned in the radial direction, in particular substantially or partially. In particular, they can be aligned completely or partially such that a radial offset corresponds to at most 1.5 times, 1 time, or 0.9 times an axial cross-sectional dimension of the sealing support web and / or a projection, in particular a maximum, mean, or minimum dimension.

[0015] The inner deck band element can have multiple openings and at least one opening for each projection. This provides at least three openings. Each of the at least three openings can preferably extend through the inner deck band element. Preferably, the opening can also be designed as a pocket, for example, as a recess, which can extend at least partially in the radial direction through the guide vane element, in particular through the inner deck band element. An opening or pocket extending through the guide vane element, in particular through the inner deck band element, can be manufactured with particularly low effort. The opening can also be referred to as an assembly opening. Similarly, the pocket can also be referred to as an assembly pocket.

[0016] The projections and openings can each be arranged in a circular pattern around the circumference of the sealing arrangement. In the context of this disclosure, the term "circular" can be understood to mean that the projections—analogous to a circle of holes—can together form a circle. For example, the sealing support element may have 20 projections arranged in a circular pattern around the circumference, each projection being inserted into one of 20 openings on the inner cover strip element. Thus, each of the projections can be inserted into one of the openings.

[0017] However, only the minimum number of protrusions and openings may be provided, meaning three protrusions and three openings. When the three protrusions of the sealing carrier element are inserted into the respective openings on the inner cover band element, a secure coupling and spoke centering between the sealing carrier element (and thus the sealing component) and the guide vane element can be achieved.

[0018] A guide vane element can be a guide vane, a guide vane cluster, or a guide ring. In the case of a single guide vane, an inner cover band element is attached to its radially inner end. In the case of a guide vane cluster, for example, three to five guide vanes are connected to each other by a common inner cover band element and are similarly connected by a radially outer element. Furthermore, the term guide vane element can also refer to an entire guide ring, which may comprise several guide vane clusters or several guide vanes. However, the number of guide vanes connected by a common inner cover band element is not limited and can be any technically feasible value.

[0019] According to the technology disclosed herein, the sealing arrangement comprises a seal carrier element and a guide vane element. In an operating state in which the seal carrier element and the guide vane element are mounted, a pressure acts on the seal carrier element, pressing it against the guide vane element such that a seal is formed between the seal carrier element and the guide vane element by a circumferentially extending sealing carrier web of the seal carrier element with a sealing surface facing the sealing web that is offset upstream in the axial direction relative to both the axially leading and the axially trailing surfaces of the projections. However, even in this position of the seal carrier element, the projections are movably mounted on both sides in the respective opening of the guide vane element in the axial direction.This means that the projections in the openings are mounted with clearance and are movable in the axial direction both downstream and upstream. This prevents the projections of the sealing support element from contacting the openings in the axial direction, and thus an axial compressive force on the sealing support element does not act on the axially leading and trailing surfaces of the projections or on the axially trailing surface of the openings. The force acting on the sealing support element is therefore directed to the sealing surface, which is offset in the axial direction, particularly downstream, relative to both the axially leading and trailing surfaces of the projections.

[0020] Alternatively, the circumferentially extending sealing rib of the guide vane element, which has the sealing surface facing the seal carrier rib, can be offset in the axial direction, particularly upstream, relative to the axially rear surface of the opening. This also prevents the seal carrier element from contacting the guide vane element with its projections and thus prevents a pressure force from acting on the sealing surfaces of the seal carrier element.

[0021] The invention comprises further advantageous embodiments, which are described below.

[0022] According to a further advantageous embodiment, the projections in the sealing arrangement are guided with axial and / or circumferential play within the radial guide, wherein, in particular, the axial play is greater than the circumferential play. In other words, the projections can be guided radially within the openings, exhibiting axial and / or circumferential play, i.e., they are movably guided radially in the axial and / or circumferential directions, with, in particular, the axial play being greater than the circumferential play. This ensures that an axial force acts on the sealing carrier element and not on the projections. This preferably achieves a seal between the sealing carrier element and the guide vane element.

[0023] According to a further advantageous embodiment, the sealing arrangement provides that, in one, several, or all guide vane elements, the respective sealing rib extends circumferentially over the entire circumferential length of the guide vane element. In other words, the sealing rib extends circumferentially over the entire circumferential length of all guide vane elements combined, and a particularly good sealing effect can be achieved.

[0024] According to a further advantageous embodiment, the sealing arrangement is provided that the projections in the radial guide in the opening of the guide vane element have sufficient axial play so that the sealing carrier element can be pressed against the sealing rib in the flow direction during operation. In other words, a force exerted on the sealing carrier element by the flowing gas acts on the sealing rib with the sealing surface or on the sealing carrier element with the sealing surface, and the projections in the radial guide in the opening of the guide vane element have sufficiently large axial play, that is, they have sufficient mobility.

[0025] According to a further advantageous embodiment, the projections in the radial guide in the opening of the guide vane element have axial play and / or are axially spaced in the receptacle when the sealing surfaces are in sealing contact. In other words, the sealing surfaces of the seal carrier element and the guide vane element lie planarly against each other and form a sealing contact, whereby in this position the projections in the radial guide in the opening of the guide vane element have axial play, are axially spaced in the opening, or are movable in the axial direction within the guide in the opening. This allows for a particularly advantageous seal between the guide vane element and the seal carrier element.

[0026] In an advantageous embodiment of the invention, at least the sealing component is designed without sliding blocks. This is advantageous because the sliding block-free design eliminates the need for sliding blocks, thus simplifying the assembly of the sealing arrangement. It is conceivable that the at least three projections on the inner cover band element and, additionally or alternatively, the surface areas of the projection facing the blade element, could have at least one wear-resistant layer. This wear-resistant layer can be provided instead of the sliding blocks. Simplified assembly of the sealing arrangement can also be achieved if the guide vane element is also designed without sliding blocks. Particularly simple assembly of the sealing arrangement can be achieved if the entire sealing arrangement is designed without sliding blocks.

[0027] In a further advantageous embodiment of the invention, the at least one opening can lead into at least one cavity of the at least one blade element. This is advantageous because the cavity of the blade element allows for weight savings and a particularly simple connection between the opening and the cavity can be created if the opening is produced as an easily manufactured penetration through the inner cover band element. This embodiment represents a possible further development of the technology described above and can be combined with other advantageous embodiments, insofar as this is technically feasible.

[0028] In a further advantageous embodiment of the invention, the at least one projection in the radial direction of the sealing arrangement is spaced apart from at least one cavity floor of the at least one cavity. This is advantageous because it allows for a particularly free, and especially collision-free, expansion of the projection in the radial direction of the sealing arrangement, for example, when caused by heating of the projection.

[0029] A second aspect of the invention relates to a sealing support element, in particular for a sealing arrangement according to the preceding description, with an inlet lining at a radially inner end, an integral ring body element, at least three projections for spoke centering of the sealing support element radially within guide vane elements with at least three respective openings for the at least three projections, wherein the sealing support element is configured such that the spoke centering is achieved by means of radial guides of the at least three projections in the at least three openings, wherein each projection of the at least three projections has a front surface and a rear surface in the flow direction in the axial direction, and each projection is configured toIn the operating state, the sealing support element and the guide vane element are movably mounted in the opening in the axial direction when in tight contact. In particular, the sealing support element has a circumferentially extending sealing support web with a sealing surface facing the sealing web, which is offset in the axial direction relative to both the axially front and the axially rear surfaces of the projections.

[0030] In other words, the sealing carrier element comprises an annular body element with at least three projections or spokes, which enable radial spoke centering of the sealing carrier element within the guide vane elements, guide vane clusters, or guide vane ring. Each projection is integrally connected to the annular body element and extends radially from the at least one annular body element in the sealing arrangement. The guide vane elements each have openings for the at least three projections, with the projections guided radially within the openings. The projections each have axially leading and axially trailing surfaces in the flow direction, and each projection is designed to be movably mounted in the opening in the operating state when there is a sealing contact between the sealing carrier element and the guide vane element.For this purpose, the sealing carrier element has a circumferentially extending sealing carrier web with a sealing surface that faces the sealing web of the guide vane element and, in the operating state, makes full planar contact with the sealing surface of the guide vane element during sealing contact. To ensure that a force on the sealing carrier element acts on the sealing surface and not on the projections, the projections within the openings are radially guided in such a way that they are movable in both directions axially (i.e., upstream and downstream). For this purpose, the front and rear surfaces of the projections are offset in the flow direction or against the flow direction relative to the sealing surface. This allows for a decoupling or separation between the sealing action and the spoke centering. Thus, a better sealing effect can be achieved, resulting in improved efficiency of the entire turbomachine.

[0031] According to a third aspect of the present technology, a guide vane element, particularly for a sealing arrangement as described above, is provided, wherein the guide vane element has an opening that points radially inwards to receive a projection of the at least three projections of the sealing carrier element for spoke centering, and has a sealing rib extending radially inwards that forms a radially innermost section of the guide vane element. In particular, the opening is configured to movably receive the projection in the opening in the axial direction during the operating state when there is sealing contact between the sealing carrier element and the guide vane element, and the circumferentially extending sealing rib of the guide vane element has a sealing surface facing the sealing carrier rib that is offset in the axial direction relative to an axially rearward surface of the opening.

[0032] In other words, the guide vane element has radially inward-facing openings, with one opening provided for each projection of the seal carrier element. The projections inserted into the openings enable spoke centering of the seal carrier element. The sealing rib forms the radially innermost section of the guide vane element. Here, the sealing rib is offset upstream relative to a downstream edge of the guide opening, and the sealing rib of the guide vane element has a sealing surface that is offset in the flow direction relative to the axially rearward surface of the opening. In other words, the opening has an approximately rectangular cross-section in a section perpendicular to the radial direction, and thus a downstream surface is formed in the axial direction, with this axially rearward surface of the opening being offset in the flow direction relative to the sealing surface.This ensures that a force on the sealing support element results in a force on the sealing surface, and that the projections in the opening are guided to move in the axial direction.

[0033] A fourth aspect of the invention relates to a turbomachine comprising at least one sealing arrangement according to the preceding description, at least one sealing support element according to the preceding description, and / or at least one guide vane element according to the preceding description. This turbomachine is particularly lightweight, can be manufactured with minimal effort, and exhibits particularly high efficiency due to the exceptionally good sealing effect.

[0034] In a further advantageous embodiment of the invention, the turbomachine is designed as an aircraft engine. This is advantageous because the turbomachine, due to its low weight, is particularly suitable for use as an aircraft engine.

[0035] The features and advantages presented in connection with the sealing arrangement according to the first aspect of the invention, the sealing support element according to the second aspect of the invention, and the guide vane element according to the third aspect of the invention apply accordingly to the turbomachine according to the fourth aspect of the invention and vice versa.

[0036] Further features of the invention will become apparent from the claims and the exemplary embodiments. The features and combinations of features mentioned above in the description, as well as the features and combinations of features mentioned and / or shown individually in the exemplary embodiments below, can be used not only in the combinations specified, but also in other combinations or on their own, without departing from the scope of the invention. Thus, embodiments that are not explicitly shown and explained in the exemplary embodiments, but which can be derived and generated from the explained embodiments by separate combinations of features, are also to be considered as encompassed and disclosed by the invention. Embodiments and combinations of features that do not exhibit all the features of an originally formulated independent claim are also to be considered disclosed. This is shown in: Fig. 1 shows a schematic sectional view of a portion of a sealing arrangement viewed along a circumferential direction of the sealing arrangement, wherein the sealing arrangement comprises a guide vane element and a sealing support element; Fig. 2 shows a further sectional view of an enlarged segment of the sealing arrangement viewed along an axial direction of the sealing arrangement according to section BB in Fig. 1 ; Fig. 3 a schematic view of an opening of the guide vane element in the viewing direction along the radial direction of the sealing arrangement according to section CC in Fig. 1 , wherein a projection of the sealing support element is inserted into the opening; Fig. 4 a schematic top view of the sealing support element in the direction of view along the axial direction; Fig. 5 a further schematic sectional view of the partial area of ​​a sealing arrangement according to a further embodiment.

[0037] Fig. 1 Figure 1 shows a schematic sectional view of a section of a sealing arrangement 10, viewed along a circumferential direction (U) of the sealing arrangement 10, wherein the sealing arrangement 10 comprises a guide vane element 20 and a sealing component 50. The sealing arrangement 10 comprises a plurality of guide vane elements 20, of which only one guide vane element 20 is shown below. The respective guide vane elements 20 can together form a guide vane ring of the turbomachine, however, this is not shown in Fig. 1 not shown. The individual guide vane element 20 can, in this case, form a segment of the guide vane ring and can also be referred to as a guide vane ring segment.

[0038] The guide vane element 20 comprises at least one inner cover band element 30 and at least one blade element 40 in the form of a guide vane blade connected to the inner cover band element 30. The guide vane element also comprises at least one sealing component 50 designed without sliding blocks, which has at least one sealing carrier element 60 coupled to the at least one guide vane element 20. The sealing carrier element 60 can, in particular, be designed as an unsegmented inner ring.

[0039] The at least one sealing support element 60 comprises at least one annular body element 70, at the inner end of which an inlet lining 72 is formed, and furthermore the sealing support element 60 comprises at least three projections 80, which are integrally connected to the at least one annular body element 70. The projections 80 extend radially from the at least one annular body element 70 in the sealing arrangement 10 and are each inserted into an opening 32 of the guide vane element 20, the opening 32 being able to extend, in particular, through the at least one inner cover band element 30. Each of the projections 80, which can also be referred to as lugs, is thus inserted into each of the openings 32. Both the projections 80 and the openings 32 are arranged uniformly in the circumferential direction of the sealing arrangement 10.The sealing assembly 10 comprises a plurality of guide vane elements 20, of which only one guide vane element 20 is shown below. The respective guide vane elements 20 can together form a guide vane ring of the turbomachine 100, which is not shown here. The individual guide vane element 20 can, in this case, form a segment of the guide vane ring and can also be referred to as a guide vane ring segment. The turbomachine 100 can be configured as an aircraft engine and may comprise at least one sealing assembly 10.

[0040] The projections 80, as well as their regular arrangement in the circumferential direction U of the sealing arrangement 10, are in Fig. 4 particularly clearly visible. Preferably, for example, the projections 80 can be provided with a wear-resistant layer. The wear-resistant layer can serve for direct and low-wear support of the sealing carrier element 60, for example in the circumferential direction. Furthermore, other elements or components, such as air deflectors or flow guides, can be attached to the sealing component. Furthermore, they show Fig. 1 and Fig. 5 In each case, the sealing component 50 comprises at least one inlet layer 72, which is arranged radially R on the inside of the ring body element 70. The inlet layer can enable so-called "scraping" by a rotor, in particular the engagement of a hub-side sealing fin of the rotor, and preferably has a honeycomb structure. The radial direction R generally refers not only to the sealing arrangement 10, but also to the sealing carrier element 60 and the turbomachine 100.

[0041] The openings 32 lead into respective cavities 42 of the at least one blade element 40. Each opening 32 leads into one of the cavities 42. The openings 32 and the cavities 42 can be formed by core extractions or – preferably by machining – machined into the guide blade element 20. Each of the wall regions of the guide blade element 20 that bound the opening 32 and each of the projections 80 form a positive fit, which at least restricts relative movement between the guide blade element 20 and the sealing component 50 in the circumferential direction U. Preferably, the wall regions can be provided with at least one wear-resistant layer. The wear-resistant layer can serve to directly and with low wear support the projections 80 of the sealing carrier element 60 and thus the sealing component 50 on the guide blade element 20.

[0042] The at least one sealing support element 60 can also comprise a sealing support web 36. The sealing support web 36 is connected to the ring body element 70 and is spaced in the axial direction A of the sealing arrangement 10 from the projections 80 arranged in a row in the circumferential direction U of the sealing arrangement 10. The guide vane element 20 can also comprise the sealing web 22, which projects radially inwards in the radial direction R of the sealing arrangement 10 from the at least one inner cover band element 30.

[0043] The present sealing arrangement 10 makes it possible to do without "inner air seals" known from the prior art, in which a front flange and rear flange are elaborately manufactured (for example by turning and grinding) and are usually fastened by a rivet or locking bolt with a sliding block.

[0044] In the sealing arrangement 10, the projections 80 form a single web on the ring body element 70, with the locking between the guide vane element 20 and the sealing component 50 being achieved by the projections 80, which are inserted into the respective openings 32. The sealing arrangement 10 eliminates the need for sliding blocks, which can also be referred to as "keys". Furthermore, the sealing arrangement 10 is lighter and requires less machining to manufacture than prior art inner air seals. For example, the sealing arrangement has a simpler design and fewer parts, eliminating the need for rivets or lock bolts.

[0045] In Fig. 1 The sealing support element 60 is shown, which includes the circumferentially extending (U) sealing support web 36, in particular the completely circumferential one, with a sealing surface 24 facing the sealing web 22 of the guide vane element, wherein the sealing surface 24 is offset in the axial direction, in particular downstream, relative to both the axially forward and the axially rear surfaces 34 of the projections 80. This means that the entire part 60 above the ring body element is not plate-shaped, but forms an offset, with the projections being offset relative to the sealing surface.

[0046] Fig. 2 shows a sectional view along the section line BB according to Fig. 1 is, Fig. 2 Figure 1 shows a sectional view in an axial direction through a sealing arrangement according to the technology disclosed herein. The blade element 40, which is formed with a cavity 42, has an opening 32 in which a projection 80 of the sealing carrier element 60 is received. The projection 80 has a positive fit in the circumferential direction U with the opening 32.

[0047] Fig. 3 shows a view of the sealing arrangement 10 in radial direction R, along the section line CC according to Fig. 1 . It should be noted that the cutting line CC has an offset approximately in the middle of the sealing arrangement 10. Fig. 3 The opening 32 is shown, which has an approximately rectangular shape in the plane opposite the radial direction. A surface of the opening 32 located at the rear in the axial direction within the guide vane element 20 is designated by reference numeral 38. A projection 80 is inserted in the opening 32. The projection 80 has axial mobility and can therefore be moved in both directions within the opening 32, so that the projection 80 has play in both axial directions. In the circumferential direction U, the projection 80 is guided radially through the opening 32 and has a positive fit in the circumferential direction U. Here, the projections in the radial guide in the opening 32 of the guide vane element 20 have sufficient axial play so that the sealing carrier element 60 can be pressed against the sealing rib 22 in the flow direction during operation when sealing contact is established.Furthermore, the projections 80 in the radial guide in the opening 32 of the guide vane element 20 have axial play, or are axially spaced in the opening 32 such that the sealing surfaces 24 can be in planar sealing contact. The at least one opening 32 opens into at least one cavity 42 of the at least one guide vane element 20. Furthermore, the at least one projection 80 can be spaced in the radial direction R of the sealing arrangement 10 from at least one cavity floor of the at least one cavity 42. Fig. 3 The shovel element 40, located behind the inner deck band element 30, can also be seen.

[0048] Fig. 4 Figure 1 shows the sealing support element 60, which has the ring body element 70 and the inlet lining 72 at its inner end. The ring body element 70 has several projections 80, which are distributed uniformly, particularly in the circumferential direction. The sealing support element 60 can have at least three projections 80 for radially centering the sealing support element 60 within guide vane elements 20, each with openings 32 for the projections 80, by means of radial guides for the projections 80 in the openings 32. The sealing support element 60 has a circumferentially extending, in particular completely circumferential, sealing support web 36, with a sealing surface 24 (not shown) facing the sealing web 22, which is offset in the flow direction relative to both the axially front and the axially rear surfaces 34 of the projections 80. It should be noted that in Fig. 4 The offset is not shown. This offset allows for a separation or decoupling of the sealing effect and spoke centering, resulting in an overall improved sealing effect and increased efficiency.

[0049] Fig. 5 In particular, it shows a further preferred embodiment of the technology disclosed herein. Fig. 5A sealing arrangement 10 is shown, comprising a guide vane element 20 and a sealing carrier element 60. During operation, these elements are in sealing contact due to a pressure difference between the axially front and rear sides of the sealing arrangement 10, thereby exerting a sealing force on the sealing surfaces 24. For the sealing force to be exerted on the sealing surfaces 24, the projections 80 must be guided in the openings 32 so as to be movably axially displaceable. The guide vane element 20 has a blade element 40, which may be hollow with a cavity 42. The inner cover band element 30 is formed on the radially inner side of the blade element 40.The sealing web 22 projects radially inwards from the inner cover band element 30, the sealing web 22 being designed such that the sealing surface 24 has an offset in the axial direction, particularly upstream, relative to the axially rear surface 38 of the opening 32. Furthermore, additional elements or components, such as air guide plates or flow guides, can be attached to the sealing carrier element 60.

[0050] The sealing support element 60 can have the sealing support web 36, which, according to the present embodiment, is planar. The axially rear surface 34 of the projection 80 cannot be offset from the sealing surface 24 according to the present embodiment. However, the sealing surface 24 of the guide vane element 20 has an offset in the axial direction, particularly upstream, from the surface 38 of the opening 32 that is rearward in the flow direction. Thus, a sealing force can act on the sealing surfaces 24, and a better sealing effect can be achieved.

[0051] The invention relates to a sealing arrangement 10 for a turbomachine, comprising a sealing carrier element 60, an integral ring body element 70, and at least three projections 80. The guide vane element 20 has an opening 32, which points radially inwards, for receiving a projection 80 of the sealing carrier element 60 for spoke centering and a sealing rib 22 extending radially inwards. In the operating state during sealing contact, each projection 80 is movably received in the respective opening 32 in the axial direction A. The sealing carrier element 60 has a sealing carrier web 36 extending in the circumferential direction U with a sealing surface 24 facing the sealing web 22 which is offset in the axial direction, and / or the sealing web 22 extending in the circumferential direction U of the guide vane element 20 has a sealing surface 24 facing the sealing carrier web 36 which is offset relative to an axially rear surface 38 of the opening 32. Reference symbol list:

[0052] 10 Sealing arrangement 20 Guide vane element 22 Sealing web 24 Sealing surface 30 Inner cover band element 32 Opening 34 Surface 36 Sealing carrier web 38 Surface 40 Blade element 42 Cavity 50 Sealing component 60 Sealing carrier element 70 Ring body element 72 Inlet lining 80 Projection 100 Turbomachine A Axial direction R Radial direction U Circumferential direction

Claims

1. Sealing arrangement (10) for a turbomachine, comprising: - a seal carrier element (60) with an inlet lining (72) at a radially inner end, an integral ring body element (70), and at least three projections (80) for spoke centering of the seal carrier element (60) radially within guide vane elements (20) with at least three respective openings (32) for the at least three projections (80), wherein the seal carrier element (60) is configured such that the spoke centering is achieved by means of radial guides of the at least three projections (80) in the at least three openings (32), wherein each projection (80) of the at least three projections (80) has a flow-direction leading surface (34) and a flow-direction trailing surface (34), and - the guide vane element (20) with the opening (32) that points radially inwards,for receiving a projection (80) of the at least three projections (80) of the sealing carrier element (60) for spoke centering and with a radially inward extending sealing web (22) which forms a radially innermost section of the guide vane element (20), , characterized by the fact that- in the operating state, with sealing contact between the sealing carrier element (60) and the guide vane element (20), each projection (80) is movably received in the respective opening (32) in the axial direction (A), and - the sealing carrier element (60) has a circumferentially extending (U) sealing carrier web (36) with a sealing surface (24) facing the sealing web (22), which is offset in the axial direction relative to both the axially front and the axially rear surfaces (34) of the projections (80), and / or - the circumferentially extending (U) sealing web (22) of the guide vane element (20) has a sealing surface (24) facing the sealing carrier web (36), which is offset in the axial direction relative to an axially rear surface (38) of the opening (32).

2. Sealing arrangement (10) according to claim 1, in which the projections (80) are guided axially and / or circumferentially (U) with clearance within the radial guide, wherein in particular an axial clearance in the axial direction (A) is greater than a clearance in the circumferential direction (U).

3. Sealing arrangement (10) according to one of the preceding claims, wherein in one, several or all guide vane elements (20) the respective sealing web (22) extends in circumferential direction (U) over the entire circumferential length of the guide vane element (20).

4. Sealing arrangement (10) according to one of the preceding claims, wherein the projections (80) in the radial guide in the opening (32) of the guide vane element (20) have sufficient axial play so that the sealing carrier element (60) can be pressed against the sealing rib (22) in the direction of flow during operation.

5. Sealing arrangement (10) according to one of the preceding claims, characterized by the fact thatthe projections (80) in the radial guide in the opening (32) of the guide vane element (20) have axial play and / or are axially spaced in the opening (32) when the sealing surfaces (24) are in sealing contact.

6. Sealing arrangement (10) according to one of the preceding claims, characterized by the fact that the sealing arrangement (10) is designed without sliding blocks.

7. Sealing arrangement (10) according to one of the preceding claims, characterized by the fact that which opens at least one opening (32) into at least one cavity (42) of the at least one guide vane element (20).

8. Sealing arrangement (10) according to one of the preceding claims, characterized by the fact that which is spaced at least one projection (80) in radial direction (R) of the sealing arrangement (10) from at least one cavity floor of the at least one cavity (42).

9. Sealing support element (60), in particular for a sealing arrangement according to one of claims 1 to 5, comprising an inlet lining (72) at a radially inner end, an integral ring body element (70), and at least three projections (80) for spoke centering of the sealing support element (60) radially within guide vane elements (20) with at least three respective openings (32) for the at least three projections (80), wherein the sealing support element (60) is configured such that the spoke centering is achieved by means of radial guides of the at least three projections (80) in the at least three openings (32), wherein each projection (80) of the at least three projections (80) has a front surface (34) and a rear surface (34) in the axial direction in the flow direction, and each projection (80) is configured toin the operating state, the sealing carrier element (60) and the guide vane element (20) are movably mounted in the opening (32) in the axial direction (A). characterized by - a circumferentially extending sealing carrier web (36) with a sealing surface (24) facing the sealing web (22), which is offset in the axial direction relative to both the axially front and the axially rear surfaces (34) of the projections (80).

10. Guide vane element (20), in particular for a sealing arrangement according to one of claims 1 to 5, comprising - with the opening (32) which points radially inwards, for receiving a projection (80) of the at least three projections (80) of the sealing carrier element (60) for spoke centering and with a sealing web (22) extending radially inwards, which forms a radially innermost section of the guide vane element (20), characterized by the fact thatthe opening (32) is designed to - in the operating state, with sealing contact between the sealing carrier element (60) and the guide vane element (20), to movably receive the projection (80) in the opening (32) in the axial direction (A), and - the circumferentially extending sealing web (22) of the guide vane element (20) has a sealing surface (24) pointing towards the sealing carrier web (36), which is offset in the axial direction relative to an axially rear surface (38) of the opening (32).

11. Turbomachine (100) comprising at least one sealing arrangement (10) according to one of claims 1 to 8, at least one sealing support element (60) according to claim 9 and / or at least one guide vane element (20) according to claim 10.

12. Turbomachine (100) according to claim 11, characterized by the fact that the turbomachine (100) is designed as an aircraft engine.

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