Sealing device for a flow machine, sealing support ring element for a sealing device and flow machine

Description

[0001] The invention relates to a sealing device for a turbomachine, comprising at least one guide vane component, which comprises at least one inner shroud element and at least one blade element connected to the at least one inner shroud element, and comprising at least one sealing component, which has at least one seal carrier ring element coupled to the at least one guide vane component. Further aspects of the invention relate to a seal carrier ring element for a sealing device and a turbomachine.

[0002] To optimize the efficiency of turbomachines, such as gas turbines, it is particularly useful to minimize leakage flows between a rotating rotor and the stationary sealing device. In particular, a leakage gap between the radially inner ends of the stationary guide vanes—in other words, the area between the ends of the stationary guide vanes located inside the radial direction of the sealing device—and the rotating rotor is sealed. The sealing component is secured to the guide vane component by a sliding block, which is attached, for example, by 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] Guide vane components are known from the documents US2019390558A1, EP2824282A1, EP3121379A1, US2019368360A1.

[0004] The object of the present invention is to provide a sealing device, a seal carrier ring element and a turbomachine of the type mentioned at the outset, which have a particularly low weight and can be manufactured with little effort.

[0005] This object is achieved by a sealing device having the features of patent claim 1, by a seal carrier ring element having the features of patent claim 11, and by a turbomachine having the features of patent claim 13. Advantageous embodiments with expedient further developments of the invention are specified in the respective subclaims.

[0006] A first aspect of the invention relates to a sealing device for a turbomachine, having at least one guide vane component, which comprises at least one inner shroud element and at least one blade element connected to the at least one inner shroud element, and having at least one sealing component, which has at least one seal carrier ring element coupled to the at least one guide vane component. The at least one blade element can be designed, in particular, as an airfoil and referred to as a guide vane. The sealing component can also be referred to as an "inner air seal" or "inner air seal," abbreviated to "IAS." The sealing component can be designed to seal a leakage gap between the guide vane component and a rotor, in particular rotor blades of the rotor, of the turbomachine. For this purpose, the sealing component can comprise a run-in lining.The run-in lining can limit the leakage gap in the radial direction of the sealing device. Therefore, when the sealing device is used as intended, the run-in lining can directly border the leakage gap in the radial direction of the sealing device.

[0007] According to the invention, it is provided that the at least one seal carrier ring element comprises at least one ring body element and at least one projection which is connected in one piece, in particular in a one-piece, monolithic and / or integral manner to the at least one ring body element, protrudes from the at least one ring body element in the radial direction of the sealing device and is inserted into at least one opening of the at least one guide vane component. This is advantageous because, due to the one-piece connection between the ring body element and the at least one projection, particularly few individual parts are required to assemble the sealing device, whereby the sealing device can be manufactured with particularly little effort. The at least one projection can protrude from the ring body in particular radially, i.e. in the radial direction of the sealing device. The projection can also be referred to as a nose.The at least one opening can preferably extend through the at least one inner shroud element. The opening can preferably also be designed as a pocket, for example, as a depression, which can extend at least partially in the radial direction through the guide vane component, in particular through the inner shroud element. An opening or pocket extending through the guide vane component, in particular through the inner shroud, can be manufactured with particularly little effort. The opening can in particular be referred to as an assembly opening. Accordingly, the pocket can also be referred to as an assembly pocket.

[0008] In the guide vane component, the blade element(s), in particular one or more guide vane blades, and the in particular common inner shroud element, in particular inner shroud segment, are preferably connected and / or formed to one another in one piece, integrally and / or monolithically, for example cast as a common piece.

[0009] The preferably integrally formed guide vane component can in particular be a guide vane cluster or guide vane cluster segment which comprises one or more guide vanes, e.g. exactly one, exactly two, exactly three, exactly four, exactly five, exactly six or exactly seven or more, and which forms or is intended to form a part or a segment of a guide vane ring.

[0010] Particularly preferably, the seal carrier ring element is free of additional projections arranged next to the projection in the axial direction of the sealing device. Thus, it can be provided that only the at least one projection protrudes into the at least one opening. If the seal carrier ring element has several projections connected to the ring body element, these projections can be arranged, in particular, in a row, whereby it is possible to dispense with the corresponding additional projections being arranged next to the projections in the axial direction of the sealing device.

[0011] The at least one inner shroud element and the at least one annular body element can preferably be supported against one another in the radial direction, in particular directly against one another. This allows any tilting between the inner shroud element and the annular body element to be counteracted particularly reliably.

[0012] The seal carrier ring element can also be referred to as a seal carrier ring and can have a plurality of projections. The inner shroud element can have a plurality of openings. The projections and the openings can each be arranged in a row in the circumferential direction of the sealing device, in particular in a circular arrangement. The term "circular" in the context of the present disclosure can be understood to mean that the projections—analogous to a hole circle—can together form a circle. For example, it can be provided that the seal carrier ring element has, for example, 20 projections arranged in a circular arrangement in the circumferential direction, each of which can be inserted into one of 20 openings on the inner shroud element. Thus, one of the projections can be inserted into each of the openings.In the circumferential direction of the sealing device, several projections, at least three, are inserted into correspondingly at least three openings on the inner shroud element. If three projections of the seal carrier ring element are inserted into correspondingly three openings on the inner shroud element, a particularly secure coupling between the seal carrier ring element (and thus the sealing component) and the guide vane component can be achieved.

[0013] In an advantageous development of the invention, at least the sealing component is designed without sliding blocks. This is advantageous because the design without sliding blocks eliminates the use of sliding blocks, thereby enabling simplified assembly of the sealing device. It is conceivable for the at least one projection to have at least one wear protection layer on the inner shroud element and additionally or alternatively on surface regions of the projection facing the blade element. This wear protection layer can be provided instead of the sliding blocks. Simplified assembly of the sealing device can also be achieved if the guide vane component is also designed without sliding blocks. Particularly simple assembly of the sealing device can be achieved if the entire sealing device is designed without sliding blocks.

[0014] In a further advantageous development of the invention, at least one of the openings opens into at least one cavity of the at least one blade element. This is advantageous because, on the one hand, the cavity of the blade element allows for weight savings and, on the other hand, a particularly simple connection between the opening and the cavity can be created if the opening is created as an easily produced opening through the inner shroud element.

[0015] In a further advantageous development of the invention, at least one of the projections is spaced apart from at least one cavity floor of the at least one cavity in the radial direction of the sealing device. This is advantageous because it enables a particularly free, in particular collision-free, expansion of the projection in the radial direction of the sealing device, for example, due to heating of the projection.

[0016] The seal carrier ring element comprises at least three projections and is spoke-centered radially within the guide vane components via the projections. In an advantageous development of the invention, the seal carrier ring element comprises at least as many projections as there are guide vane components in the form of integrally formed guide vane cluster segments.

[0017] In such a spoke centering, in which at least three projections pointing in pairs in different radial directions are introduced into a guide vane component (each the same or different) and are each guided radially in an associated opening of a guide vane component, the seal carrier ring element, which is designed in particular as an integral ring or circular ring, is held via the radial guides and centered within a plane perpendicular to the axis of rotation of the turbomachine, so that in particular the ring center point lies on or in the region of the axis of rotation.

[0018] In the spoke centering, each radial guide of the spoke centering is radially unfixed, ie in the area of ​​the guide it is not secured against displacement in the respective radial direction, e.g. radially inwards.

[0019] Preferably, each of the projections, when inserted into an opening in the guide vane component, forms, together with the opening, a radial guide in precisely one specific radial direction, which coincides with the radial direction at the location of the inserted projection. In other words, the projection extends quasi-one-dimensionally or linearly in the respective radial direction and is guided completely along its circumferential surface in this radial direction, at least on one radial section.

[0020] In the area of ​​the radial guide, the projection in question is secured against displacement perpendicular to the relevant radial direction.

[0021] The projection(s) may have a constant cross-section in the radial direction at least in sections and / or taper in the radially outward direction at least in sections.

[0022] In some embodiments of the invention, the guide vane component has no projections projecting radially inward from its inner shroud element, in particular at least no projections for radial guidance, and / or no fixing elements or guide elements projecting radially inward. As a result, the guide vane components can have a comparatively simple structure. Spoke centering can thus be provided solely via the projections of the seal carrier ring element, without the need for additional projections or radially inward-projecting guide elements of the guide vane component.

[0023] In some embodiments of the invention, the one or more projections of the seal carrier ring element extend through the respective inner shroud element and in particular into a respective guide vane or are provided and designed to do so.

[0024] In a further advantageous development of the invention, the wall regions of the sealing device delimiting at least one opening and the at least one projection form at least one positive connection, by means of which a relative movement between the at least one guide vane component and the at least one sealing component in the circumferential direction and / or in the axial direction of the sealing device is prevented. This is advantageous because it enables a secure coupling between the guide vane component and the sealing component in a particularly simple manner. The relative movement between the guide vane component and the sealing component can be particularly largely restricted if the guide vane component and the sealing component form the positive connection both in the circumferential direction and in the axial direction.The guide vane component and the sealing component can, in particular, be connected to one another without bolts, pins, and additionally or alternatively without screws. In other words, the guide vane component and the sealing component can be connected to one another without bolts, pins, and additionally or alternatively without screws. In particular, the guide vane component and the sealing component can be coupled to one another exclusively in a form-fitting manner and thus connected to one another. The wall regions can be formed by the inner shroud element. In other words, the wall regions can be assigned to the inner shroud element. The inner shroud element can therefore comprise the wall regions.

[0025] In a further advantageous development of the invention, the at least one seal carrier ring element comprises at least one sealing flange element, which is connected to the at least one annular body element and spaced apart from the at least one projection in the axial direction of the sealing device. This is advantageous because it allows for particularly high tightness against leakage flows. The sealing flange element and the annular body element can, in particular, be connected to one another in one piece. This allows for particularly low-complexity assembly of the sealing device.

[0026] According to one embodiment, the seal carrier ring element is formed as an integral, closed ring or comprises such a ring. Accordingly, the seal carrier ring element can be a non-segmented solid ring that is formed in one piece, monolithically, or can comprise such a ring.

[0027] In a further advantageous development of the invention, the at least one guide vane component comprises at least one flange element which protrudes from the at least one inner shroud element in the radial direction of the sealing device and is inserted into an intermediate space which extends in the axial direction of the sealing device between the at least one sealing flange element and the at least one projection. This is advantageous because it allows a particularly high sealing effect against leakage flows. This arrangement therefore allows the flange element to engage in the intermediate space between the sealing flange element and the projection, whereby - similar to a labyrinth seal - an improved seal can be achieved. The inner shroud element can protrude in particular in the direction of the annular body element.

[0028] In a further advantageous development of the invention, the at least one guide vane component comprises at least one additional flange element, which protrudes from the at least one inner shroud element in the radial direction of the sealing device and is spaced apart from the at least one flange element in the axial direction of the sealing device, forming at least one gap. This is advantageous because it further improves the sealing effect against leakage flows. The additional flange element can protrude in the radial direction, in particular, toward the at least one annular body element. The gap can be designed, in particular, as an annular gap. The term "gap space" can therefore be understood to mean a gap-shaped, in particular annular gap-shaped, gap. The at least one opening can also extend between the flange element and the additional flange element.

[0029] In an advantageous development of the invention, the at least one projection is inserted into the at least one gap. This advantageously results in a rear-facing arrangement of the sealing flange element, flange element, projection, and additional flange element, which, on the one hand, creates a particularly good sealing effect against leakage flows and, on the other hand, a particularly durable, in particular positive-locking, connection between the guide vane component and the sealing component.

[0030] A second aspect of the invention relates to a seal carrier ring element for a sealing device according to the first aspect of the invention. The seal carrier ring element comprises at least one ring body element and at least three projections, which are integrally connected to the at least one ring body element and protrude from the at least one ring body element in the radial direction of the sealing device. The at least three projections are designed for insertion into at least one opening of the at least one guide vane component of the sealing device and thus for receiving the guide vane component.

[0031] A third aspect of the invention relates to a turbomachine comprising at least one sealing device according to the first aspect of the invention and / or at least one seal carrier ring element according to the second aspect of the invention. This turbomachine is particularly lightweight and can be manufactured with little effort.

[0032] In an advantageous development of the invention, the turbomachine is designed as an aircraft engine. This is advantageous because the turbomachine's low weight makes it particularly suitable for use as an aircraft engine.

[0033] The features presented in connection with the sealing device according to the first aspect of the invention and the seal carrier ring element according to the second aspect of the invention as well as their advantages apply accordingly to the turbomachine according to the invention according to the third aspect of the invention and vice versa.

[0034] Further features of the invention emerge from the claims and the exemplary embodiments. The features and feature combinations mentioned above in the description, as well as the features and feature combinations mentioned below in the exemplary embodiments and / or shown alone, can be used not only in the respective combination specified, but also in other combinations or on their own, without departing from the scope of the invention. Thus, embodiments are also to be considered encompassed and disclosed by the invention that are not explicitly shown and explained in the exemplary embodiments, but which emerge and can be generated through separate feature combinations from the explained embodiments. Embodiments and feature combinations are also to be considered disclosed that therefore do not have all the features of an originally formulated independent claim. Here, Fig. 1 shows a partial area of ​​a sealing device in a schematic sectional view when viewed along a circumferential direction of the sealing device, wherein the sealing device comprises a guide vane component and a sealing component and is arranged in a highly abstracted turbomachine; Fig. 2 shows a further sectional view of an enlarged segment of the sealing device when viewed along an axial direction of the sealing device; Fig. 3 shows a schematic plan view of a seal carrier ring element of the sealing component when viewed along the axial direction of the sealing device, wherein the seal carrier ring element comprises an annular body element and a plurality of projections projecting from the annular body element in the radial direction of the sealing device; Fig. 4 shows a schematic plan view of the sealing device when viewed along the axial direction;Fig. 5 shows a further schematic sectional view of the partial region of the sealing device when viewed along the circumferential direction, wherein a run-in coating of the sealing component can be seen; Fig. 6 shows a schematic exploded view of the partial region of the sealing device, wherein the guide vane component and the sealing component are separated from one another; and Fig. 7 shows a schematic sectional view of a partial region of a variant of the sealing device.

[0035] FIG. 1 shows a highly abstracted turbomachine 100 designed as an aircraft engine, which comprises at least one sealing device 10. The sealing device 10 comprises a plurality of guide vane components 20, of which only one guide vane component 20 is shown below. The respective guide vane components 20 can together form a guide vane ring of the turbomachine 100, which, however, is not shown here. The individual guide vane component 20 can form a segment of the guide vane ring, as exemplified by FIG. Fig. 4 can be seen and is also referred to as a guide vane ring segment.

[0036] The guide vane component 20 comprises at least one inner shroud element 30, which is enlarged in Fig. 2 can be seen, and at least one blade element 40 in the form of a guide vane blade connected to the at least one inner shroud element 30. The guide vane component 20 also comprises at least one sliding block-free sealing component 50, which has at least one seal carrier ring element 60 coupled to the at least one guide vane component 20. The seal carrier ring element 60 can in particular be designed as an unsegmented inner ring.

[0037] The at least one seal carrier ring element 60 comprises at least one ring body element 70 and projections 80, which are integrally connected to the at least one ring body element 70, protrude from the at least one ring body element 70 in the radial direction R of the sealing device 10 and are inserted into an opening 32 in the guide vane component 20, which can extend in particular through the at least one inner shroud element 30. Each of the projections 80, which can also be referred to as lugs, is thus inserted into one of the openings 32. Both the projections 80 and the openings 32 are arranged uniformly in the circumferential direction U of the sealing device 10. The projections 80, as well as their regular arrangement in the circumferential direction U of the sealing device 10, are Fig. 3 as well as in Fig. 4 This can be seen particularly clearly. Preferably, for example, the projections 80 can be provided with at least one wear-resistant layer. The wear-resistant layer can serve to directly and wear-resistantly support the seal carrier ring element 60 and thus the sealing component 50 on the guide vane component 20. Fig. 5 und Fig. 6 Each shows that the sealing component 50 comprises at least one run-in lining 72, which is arranged on the inside of the annular body element 70 in the radial direction R. The run-in lining can enable a so-called "rubbing" by a rotor, in particular a run-in 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 device 10, but also to the seal carrier ring element 60 and the turbomachine 100.

[0038] The openings 32 open into respective cavities 42 of the at least one blade element 40. In each case, one of the openings 32 opens into one of the cavities 42. The openings 32 and the cavities 42 can be formed by respective core extracts or - preferably by machining - can be incorporated into the guide vane component 20.

[0039] The projections 80 are spaced apart from the respective cavity bottoms of the cavities 42 in the radial direction R of the sealing device 10. The cavity bottoms represent outer boundaries of the respective cavities in the radial direction R and are not shown further here.

[0040] Each wall region 34 of the sealing device 10 delimiting the openings 32 and each projection 80 form a positive connection 90, by which a relative movement between the at least one guide vane component 20 and the at least one sealing component 50 in the circumferential direction U and in the axial direction A of the sealing device 10 is at least limited. Preferably, the wall regions 34 can be provided with at least one additional wear protection layer. The additional wear protection layer can serve to directly and wear-resistantly support the projections 80 of the seal carrier ring element 60 and thus the sealing component 50 on the guide vane component 20. The additional wear protection layer can be provided in addition to or as an alternative to the wear protection layer (on the projections 80). The wear protection layer and the additional wear protection layer can be formed from the same material.

[0041] The at least one seal carrier ring element 60 may also comprise at least one sealing flange element 62, as in Fig. 7 can be seen. The at least one sealing flange element 62 is connected to the at least one annular body element 70 and is spaced apart in the axial direction A of the sealing device 10 from the projections 80 arranged in a row in the circumferential direction U of the sealing device 10. The at least one guide vane component 20 can also comprise at least one flange element 22 which protrudes from the at least one inner shroud element 30 in the radial direction R of the sealing device 10 and is inserted into an intermediate space 52 which extends in the axial direction A of the sealing device 10 between the at least one sealing flange element 62 and the at least one projection 80.

[0042] At least one in Fig. 7The guide vane component 20 shown can further comprise at least one additional flange element 24, which protrudes from the at least one inner shroud element 30 in the radial direction R of the sealing device 10 and is spaced from the at least one flange element 22 in the axial direction A of the sealing device 10, forming at least one gap space 26. The projections 80 are inserted into the at least one gap space 26. The gap space 26 is designed as a gap-shaped, in particular annular gap-shaped, space.

[0043] The present sealing device 10 makes it possible to dispense with "inner air seals" known from the prior art, in which a front flange and rear flange are manufactured in a complex manner (for example by turning and grinding) and are usually fastened by a rivet or lockbolt with a sliding block.

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

[0045] 10Sealing device 20Guide vane component 22Flange element 24Additional flange element 26Gap space 30Inner shroud element 32Opening 34Wall area 40Vacuum element 42Cavity 50Sealing component 52Gap 60Seal carrier ring element 62Sealing flange element 70Ring body element 72Run-in lining 80Protrusion 90Form fit 100Turbo machine AAxial direction RRadial direction UCircumferential direction

Claims

1. A sealing device (10) for a turbomachine (100), comprising at least one guide vane component (20) which comprises at least one inner shroud element (30) and at least one vane element (40) connected to the at least one inner shroud element (30), and at least one seal component (50) which has at least one seal-carrier ring element (60) coupled to the at least one guide vane component (20), wherein the at least one seal-carrier ring element (60) comprises at least one ring body element (70) and at least one projection (80) which is connected integrally to the at least one ring body element (70), protrudes from the at least one ring body element (70) in the radial direction (R) of the sealing device (10) and is inserted into at least one opening (32) of the at least one guide vane component (20), characterized in that the seal-carrier ring element (60) comprises at least three projections (80), each of which is guided radially in an associated opening of one of the at least one guide vane component (20), and the seal-carrier ring element (60) is spoke-centered by the projections (80) radially within the at least one guide vane component (20), in which spoke centering the seal-carrier ring element is held via the radial guides, which are radially unfixed, and the seal-carrier ring element is centered within a plane perpendicular to the axis of rotation of the turbomachine, wherein the projections (80) are secured against displacement perpendicular to the corresponding radial direction.

2. The sealing device (10) according to claim 1, characterized in that at least the seal component (50) is formed without sliding blocks.

3. The sealing device (10) according to claim 2, characterized in that the at least one opening (32) leads into at least one cavity (42) of the at least one vane element (40).

4. The sealing device (10) according to claim 3, characterized in that the at least one projection (80) is spaced apart in the radial direction (R) of the sealing device (10) from at least one cavity bottom of the at least one cavity (42).

5. The sealing device (10) according to any of the preceding claims, characterized in that the seal-carrier ring element (60) comprises at least as many projections (80) as there are guide vane components (20) in the form of integrally formed guide vane cluster segments, and the seal-carrier ring element (60) is spoke-centered by the projections (80) radially within the guide vane components (20).

6. The sealing device (10) according to any of the preceding claims, characterized in that the wall regions (34) of the sealing device (10) bounding the at least one opening (32), and the at least one projection (80), form at least one interlocking fit (90) preventing a relative movement between the at least one guide vane component (20) and the at least one seal component (50) in the circumferential direction (U) and / or in the axial direction (A) of the sealing device (10).

7. The sealing device (10) according to any of the preceding claims, characterized in that the at least one seal-carrier ring element (60) comprises at least one sealing flange element (62) which is connected to the at least one ring body element (70) and, in the axial direction (A) of the sealing device (10), is spaced apart from the at least one projection (80), and / or in that the seal-carrier ring element (60) is formed as an integral, full ring or comprises one.

8. The sealing device (10) according to claim 7, characterized in that the at least one guide vane component (20) comprises at least one flange element (22) which protrudes from the at least one inner shroud element (30) in the radial direction (R) of the sealing device (10) and is inserted into an intermediate space (52) extending in the axial direction (A) of the sealing device (10) between the at least one sealing flange element (62) and the at least one projection (80).

9. The sealing device (10) according to claim 8 characterized in that the at least one guide vane component (20) comprises at least one additional flange element (24) which protrudes from the at least one inner shroud element (30) in the radial direction (R) of the sealing device (10) and is spaced apart from the at least one flange element (22) in the axial direction (A) of the sealing device (10) while forming at least one gap space (26).

10. The sealing device (10) according to claim 9, characterized in that the at least one projection (80) is inserted into the at least one gap space (26).

11. A seal-carrier ring element (60) for a sealing device (10) according to any of claims 1 to 10, wherein the seal-carrier ring element (60) comprises at least one ring body element (70) and at least three projections (80) which are integrally connected to the at least one ring body element (70) and protrude from the at least one ring body element (70) in the radial direction (R) of the sealing device (10), characterized in that the at least three projections (80) are each formed for insertion into an associated opening (32) of a guide vane component (20) of the sealing device (10) and thereby for receiving the corresponding guide vane component (20) and for forming a spoke centering, in which spoke centering the at least three projections (80) are each guided radially in the associated opening and the seal-carrier ring element is held via the radial guides, which are radially unfixed, and the seal-carrier ring element is centered within a plane perpendicular to the axis of rotation of the turbomachine, wherein the projections (80) are secured against displacement perpendicular to the corresponding radial direction.

12. The seal-carrier ring element (60) according to claim 11, wherein the seal-carrier ring element (60) is formed as an integral closed ring or comprises such a ring and / or comprises at least three projections (80) or at least as many projections (80) as there are guide vane components in the form of integrally formed guide vane cluster segments.

13. A turbomachine (100) comprising at least one sealing device (10) according to any of claims 1 to 10 and / or at least one seal-carrier ring element (60) according to claim 11 or 12.

14. The turbomachine (100) according to claim 13, characterized in that the turbomachine (100) is formed as an aircraft engine.