ROTOR WITH SEALING RING AND FLOW MACHINE WITH THE ROTOR

Description

[0001] In a turbomachine, such as a gas turbine or a steam turbine, cooling air is conventionally injected to cool thermally stressed components. These components can include, for example, a combustion chamber, rotor blades, and / or guide vanes, especially the guide vanes and / or guide vanes in the first stage downstream of the combustion chamber. Additionally, sealing air is conventionally injected into the turbomachine to seal leaks in a flow channel. These leaks can occur, for example, between the rotor blades and a turbine casing and / or between the guide vanes and a rotor.

[0002] In addition, leaks can also occur in an air-cooled rotor of a gas turbine. For example, a rotor of this type with a seal for the gap between the platform and the cover element is known from DE 10 2018 218 942 A1, in which a T-shaped sealing ring seals the said gap.

[0003] Unwanted leaks of cooling air and / or sealing air lead to a reduction in the efficiency of the turbomachine. Segmented sealing rings, which have several segments that can shift relative to each other, can be used to seal these leaks. This allows the segmented sealing rings to adapt to changing cross-sections of the turbomachine caused by heating and / or cooling. The problem with this is that leaks can form in the area where two segments abut each other, which in turn can lead to a reduction in the turbomachine's efficiency. EP 1 944 471 A1 discloses that the cover element need not be a single, ring-shaped element, but can be formed from a plurality of flat sealing elements that can be individually attached to a turbine disk.

[0004] Furthermore, US 2012 / 034087 A1 discloses the use of a single sealing strip for sealing in the outward-facing edge of each plate-shaped element.

[0005] The object of the invention is therefore to create a rotor and a turbomachine with the rotor, whereby a turbomachine with a high efficiency can be achieved with the sealing ring.

[0006] The rotor according to the invention for a turbomachine comprises a rotor disk having a plurality of impeller blades arranged in a ring around its circumference, wherein the impeller blades comprise a blade platform with a platform projection, the underside of which faces an end face of the rotor disk, wherein a cover ring with a radially outwardly opening, circumferentially extending receiving groove is arranged radially and within the underside of the end face of the rotor disk, in which a sealing ring for sealing a radial gap between the underside and the cover ring is arranged, wherein the sealing ring comprises at least a first segment and a second segment, each having a first longitudinal end with respect to a circumferential direction of the sealing ring and a second longitudinal end with respect to the circumferential direction.wherein the first segment has a first recess and a first projection in a region of the first longitudinal end, with a first flank of the first projection limiting the first recess in the circumferential direction, and the second segment has a second recess and a second projection in a region of the second longitudinal end, with a first flank of the second projection limiting the second recess in the circumferential direction, wherein the first segment and the second segment are in a coupled state in which the first segment and the second segment are displaceable relative to each other in the circumferential direction, and the first projection is arranged in the second recess, the second projection is arranged in the first recess, and the first flank of the first projection and the first flank of the second projection are configured,to cause the first segment to collide with the second segment during its initial movement away from the first segment, thus limiting the initial movement.

[0007] A leakage flow passing through the sealing ring in an axial direction must flow circumferentially, passing over both the first and second projections. This results in high flow resistance for the leakage flow, leading to a low mass flow rate. Consequently, a high efficiency of the turbomachine can be achieved.

[0008] It is preferred that the first recess is longer in the circumferential direction than the second projection in the circumferential direction, and vice versa. This advantageously allows the first and second segments to be displaced relative to each other in the circumferential direction.

[0009] It is preferred that the first recess has an end face of the first recess and the second projection has an end face of the second projection, wherein the end face of the first recess limits it in an axial direction with respect to the sealing ring, and the end face of the second projection limits it in the axial direction, wherein in the coupling state the end face of the first recess and the end face of the second projection are arranged facing each other and define a first sealing gap.It is further preferred that the second recess has an end face of the second recess and the first projection has an end face of the first projection, wherein the end face of the second recess limits it in an axial direction with respect to the sealing ring, and the end face of the first projection limits it in the axial direction, wherein in the coupled state the end face of the second recess and the end face of the first projection are arranged facing each other and define a second sealing gap. By providing the first sealing gap and / or the second sealing gap, the flow resistance can be further increased and thus the efficiency of the turbomachine can be increased.

[0010] The first segment preferably has a first recess flank that limits the first recess in the circumferential direction, and the second projection preferably has a second flank of the second projection, wherein in the coupling state the first recess flank and the second flank of the second projection are arranged to abut each other when the first segment is moved a second time towards the second segment, thus limiting the second movement.

[0011] It is particularly preferred that the second flank of the second lead and the second longitudinal end coincide.

[0012] The second segment preferably has a recess radial boundary that limits the second recess in a radial direction with respect to the sealing ring, wherein, in the coupled state, the first projection and the recess radial boundary define a third sealing gap. The provision of this third sealing gap allows the flow resistance to be increased even further.

[0013] It is preferred that the second segment has a circumferential projection extending in the direction of the remaining second segment and that the first segment has a receptacle in which the circumferential projection is arranged in the coupled state.

[0014] The sealing ring preferably has a T-shaped profile.

[0015] It is preferred that all segments are of identical construction.

[0016] It is preferred that all segments have, in the region of the first longitudinal end, the first recess and the first projection with the first flank of the first projection defining the first recess, and in the region of the second longitudinal end, the second recess and the second projection with the first flank of the second projection defining the second recess, wherein the sealing ring has an assembly state in which all pairs of those segments that are adjacent in the sealing direction are arranged in the coupling state.

[0017] The turbomachine according to the invention includes the sealing ring. The sealing ring is preferably configured to seal off cooling air and / or sealing air within the turbomachine. The turbomachine can be, for example, a steam turbine or a gas turbine. The sealing ring can be arranged in a compressor section of the gas turbine and / or a turbine section of the gas turbine.

[0018] The invention will be explained in more detail below with reference to the attached schematic drawings. These show Figure 1 a perspective view of a first embodiment of the sealing ring, Figure 2 a perspective view of a first segment of the first embodiment, Figure 3 a perspective view of a second embodiment of the sealing ring, Figure 4 a perspective view of a first segment of the second embodiment, Figure 5a perspective view of a second segment of the second embodiment and Figure 6 The sealing arrangement with the sealing ring in longitudinal section with rotor disc, cover ring and impeller blade.

[0019] How it looks Figures 1 to 6 As can be seen, a sealing ring 1 for a turbomachine has at least a first segment 2 and a second segment 3. The first segment 2 and the second segment 3 each have a first longitudinal end 4 with respect to a circumferential direction 31 (see Figure 1The first segment 2 has a first recess 6 and a first projection 8 in a region of the first longitudinal end 4, with a first flank 10 of the first projection 8 that bounds the first recess 6 in the circumferential direction 31. The second segment 3 has a second recess 7 and a second projection 9 in a region of the second longitudinal end 5, with a first flank 13 of the second projection 8 that bounds the second recess 7 in the circumferential direction 31. The first segment 2 and the second segment 3 have a coupling state which is described in Figure 1 and 3is shown and in which the first segment 2 and the second segment 3 are displaceable relative to each other in the circumferential direction 31 and the first projection 8 is arranged in the second recess 7, the second projection 9 is arranged in the first recess 6 and the first flank 10 of the first projection 8 and the first flank 13 of the second projection 9 are arranged to abut each other when the first segment 2 is first displaced away from the second segment 3 and thus limit the first displacement.

[0020] The area of ​​the first longitudinal end 4 can extend, for example, from the first longitudinal end 4 in the circumferential direction 31 up to 50%, in particular 25% or 15%, of the total length of the respective segment 2, 3 in the circumferential direction 31 towards the second longitudinal end 5 of the respective segment 2, 3. The first recess 6 can, for example, be located entirely within the area of ​​the first longitudinal end 4. The area of ​​the second longitudinal end 5 can, for example, extend from the second longitudinal end 5 in the circumferential direction 31 up to 50%, in particular 25% or 15%, of the total length of the respective segment 2, 3 in the circumferential direction 31 towards the first longitudinal end 5 of the respective segment 2, 3. The second recess 7 can, for example, be located entirely within the area of ​​the second longitudinal end 5.

[0021] All segments 2, 3 can each have, in the region of the first longitudinal end 4, the first recess 6 and the first projection 8 with the first flank 10 of the first projection 8 that bounds the first recess 6, and can each have, in the region of the second longitudinal end 5, the second recess 7 and the second projection 9 with the first flank 13 of the second projection 8 that bounds the second recess 7. The sealing ring 1 can be in an assembled state in which all pairs of those segments 2, 3 that are adjacent in the sealing direction 1 are in the coupled state. All segments 2, 3 can be of identical construction. The in Figure 1 The circumferential direction 31 shown with respect to the sealing ring 1, the radial direction 32 with respect to the sealing ring 1 and the axial direction 33 with respect to the sealing ring 1 can refer to the sealing ring 1 in its assembled state.

[0022] Figure 1 and 3 Show that the first recess 6 in the circumferential direction 31 can be longer than the second projection 9 in the circumferential direction 31, and that the second recess 7 in the circumferential direction 31 can be longer than the first projection 8 in the circumferential direction 31. In particular, a minimum extent of the first recess 6 in the circumferential direction 31 can be longer than a maximum extent of the second projection 9 in the circumferential direction, and in particular, a minimum extent of the second recess 7 in the circumferential direction 31 can be longer than a maximum extent of the first projection 8 in the circumferential direction 31.

[0023] How it looks Figure 1 and 3 As can be seen, the first recess 6 can form an end face 16 (see Figures 2 and 4 ) the first recess 6 and the second projection 9 can have an end face 15 (see Figure 5) of the second projection 9, wherein the end face 16 of the first recess 6 limits it in the axial direction 33 with respect to the sealing ring 1, and the end face 15 of the second projection 9 limits it in the axial direction 33, wherein in the coupled state the end face 16 of the first recess 6 and the end face 15 of the second projection 9 are arranged facing each other and define a first sealing gap 25. In addition, the second recess 7 can have an end face 17 (see Figure 5 ) the second recess 7 and the first projection 8 can have an end face 12 (see Figures 2and4) of the first projection 8, wherein the end face 17 of the second recess 7 limits it in the axial direction 33 with respect to the sealing ring 1, the end face 12 of the first projection 8 limits it in the axial direction 33, wherein in the coupling state the end face 17 of the second recess 7 and the end face 12 of the first projection 8 are arranged facing each other and limit a second sealing gap 26.

[0024] How it looks Figures 1 to 5As can be seen, the sealing ring 1 can have a T-shaped profile. The first segment 2 and the second segment 3 can have a first projection 20, which is arranged on the outside of the first segment 2 and the second segment 3 in the radial direction 32 (see the figures) or on the inside of the radial direction 32 and projects from the remaining segment 2, 3 in the axial direction 33. Furthermore, the first segment 2 and the second segment 3 can have a second projection 21, which is arranged on the outside of the radial direction 32 (see the figures) or on the inside of the radial direction 32 and projects from the remaining segment 2, 3 in the axial direction 33 and on a side facing away from the first projection 20.

[0025] Figures 1 to 5Show that the first segment 2 can have a first recess flank 18 that bounds the first recess 6 in the circumferential direction 31, and the second projection 9 can have a second flank 14 of the second projection 9, wherein in the coupled state the first recess flank 18 and the second flank 14 of the second projection 9 are arranged to abut each other during a second displacement of the first segment 2 towards the second segment 3, thus limiting the second displacement. The first recess flank 18 can be arranged facing the first flank 10 of the first projection 8. Furthermore, the second segment 3 can have a second recess flank 19 that bounds the second recess 7 in the circumferential direction 31 and is arranged facing the first flank 13 of the second projection 9.

[0026] Figures 1 and 2show that according to a first embodiment of the sealing ring 1, the second flank 14 of the second projection 9 and the second longitudinal end 5 can coincide.

[0027] Figure 5 Figure 1 shows that, according to a second embodiment of the sealing ring 1, the second segment 2 can have a recess radial boundary 22 that limits the second recess 7 in a radial direction 32 with respect to the sealing ring 1, wherein, in the coupled state, the first projection 8 and the recess radial boundary 22 limit a third sealing gap. Furthermore, according to the second embodiment (see Figure 1), the second segment 2 can have a recess radial boundary 22 that limits the second recess 7 in a radial direction 32 with respect to the sealing ring 1, wherein, in the coupled state, the first projection 8 and the recess radial boundary 22 limit a third sealing gap. Figures 3 to 5) the second segment 3 has a circumferential projection 24 extending in the direction of the remaining second segment 4, and the first segment 2 can have a receptacle 23 in which the circumferential projection 24 is arranged in the coupled state. It is also conceivable that the circumferential projection 24 is aligned with the radial boundary of the recess 22 in the circumferential direction 31, compare Figure 5 .

[0028] In the Figure 6 An exemplary embodiment of a rotor according to the invention is sketched in longitudinal section. Only a portion of the area of ​​a sealing arrangement is shown here, the design of which is well known to those skilled in the art and requires no further explanation.

[0029] The rotor disk 30 is visible in sections, and it has a plurality of blade-holding grooves distributed along its circumference. A rotor blade 37 with a blade root 36 is arranged in each of these blade-holding grooves. The rotor blades, arranged radially, form a blade ring. As is typical, the blade platform 38 adjoins the blade root 36 and extends circumferentially and axially. The blade platform 38 projects beyond an end face 39 of the rotor disk 30 with a platform overhang 34 and has a bottom surface 35.

[0030] Adjacent to the rotor disk 30 at its end face is a rotor component 41, which, according to this embodiment, integrally forms the cover ring 42, extending substantially circumferentially and radially. Apart from thermal and / or centrifugal expansion, no relative displacements or movements occur between the rotor disk 30 and the rotor component. They are to be considered static components in relation to each other, even though the rotor as a whole is rotatably mounted in a known manner. As an alternative to the integral design shown, the cover ring can also be modular and thus comprise a plurality of sealing plates distributed along the circumference, which are held at the end face of the rotor disk 30.

[0031] The cover ring 42 has a radially outwardly opening, circumferentially extending receiving groove 43. The segmented sealing ring 1 described above is mounted in this groove 43. The essentially T-shaped profile of the sealing ring 1 is visible. The sealing ring 1 comprises a bearing section 11 ( Figure 2 ), arranged in the receiving groove 43, and on the radially outward-facing side a contact section 38. The contact section 38 comes into contact with the underside 15 of the platform overhang 14 at least when the rotor is rotating, thus sealing the radial gap inherent in the design between the underside 35 and the cover ring 42 in order to reduce or even prevent the flow of cooling air or sealing air through the radial gap.

Claims

1. A rotor for a turbomachine, with a rotor disc (30), which has a plurality of rotor blades (37) arranged in a circle on the circumference, wherein the rotor blades (37) comprise a blade platform (38) with a platform projection (34), whose (34) underside (35) faces an end face (39) of the rotor disc (30), wherein a cover ring (42) having a receiving groove (43) that opens radially outward and extends in a circumferential direction is arranged on the end face of the rotor disc (30) and radially inside the underside (35), in which (43) a sealing ring (1) is arranged for sealing a radial gap between the underside (35) and the cover ring (42), wherein the sealing ring comprises at least one first segment (2) and one second segment (3), each having a first longitudinal end (4) with respect to a circumferential direction (31) of the sealing ring (1) and a second longitudinal end (5) with respect to the circumferential direction (31), characterized in that the first segment (2) in a region of the first longitudinal end (4) has a first recess (6) and a first protrusion (8) with a first flank (10) of the first protrusion (8) delimiting the first recess (6) in the circumferential direction (31), and the second segment (3) in a region of the second longitudinal end (5) has a second recess (7) and a second protrusion (9) with a first flank (13) of the second protrusion (8) delimiting the second recess (7) in the circumferential direction (31), wherein the first segment (2) and the second segment (3) have a coupling state in which the first segment (2) and the second segment (3) are displaceable relative to one another in the circumferential direction (31), and the first protrusion (8) is arranged in the second recess (7), the second protrusion (9) is arranged in the first recess (6), and the first flank (10) of the first protrusion (8) and the first flank (13) of the second protrusion (9) are configured to abut against one another during a first displacing of the first segment (2) away from the second segment (3), and thus to delimit the first displacing.

2. The rotor according to claim 1, wherein the first recess (6) is longer in the circumferential direction (31) than the second protrusion (9) in the circumferential direction (31) and the second recess (7) is longer in the circumferential direction (31) than the first recess (8) in the circumferential direction (31).

3. The rotor according to claim 1 or 2, wherein the first recess (6) has an end face (16) of the first recess (6) and the second protrusion (9) has an end face (15) of the second protrusion (9), wherein the end face (16) of the first recess (6) delimits it in an axial direction (33) with respect to the sealing ring (1), the end face (15) of the second protrusion (9) delimits it in the axial direction (33), wherein in the coupling state the end face (16) of the first recess (6) and the end face (15) of the second protrusion (9) are arranged facing each other and delimit a first sealing gap (25).

4. The rotor according to one of claims 1 to 3, wherein the second recess (7) has an end face (17) of the second recess (7) and the first protrusion (8) has an end face (12) of the first protrusion (8), wherein the end face (17) of the second recess (7) delimits it in an axial direction (33) with respect to the sealing ring (1), the end face (12) of the first protrusion (8) delimits it in the axial direction (33), wherein in the coupling state the end face (17) of the second recess (7) and the end face (12) of the first protrusion (8) are arranged facing each other and delimit a second sealing gap (26).

5. The rotor according to one of claims 1 to 4, wherein the first segment (2) has a first recess flank (18) delimiting the first recess (6) in the circumferential direction (31), and the second protrusion (9) has a second flank (14) of the second protrusion (9), wherein in the coupling state the first recess flank (18) and the second flank (14) of the second protrusion (9) are configured to abut against one another during a second displacing of the first segment (2) towards the second segment (3), and thus to delimit the second displacing.

6. The rotor according to claim 5, wherein the second flank (14) of the second protrusion (9) and that the second longitudinal end (5) coincide.

7. The rotor according to one of claims 1 to 6, wherein the second segment (2) has a recess radial limit (22) that delimits the second recess (7) in a radial direction (32) with respect to the sealing ring (1), wherein in the coupling state the first protrusion (8) and the recess radial limit (22) delimit a third sealing gap.

8. The rotor according to one of claims 1 to 5 and 7, wherein the second segment (3) has a circumferential protrusion (24) protruding in the direction of the remaining second segment (4), and the first segment (2) has a receptacle (23) in which the circumferential protrusion (24) is arranged in the coupling state.

9. The rotor according to one of claims 1 to 8, wherein the sealing ring (1) has a T-shaped profile.

10. The rotor according to one of claims 1 to 9, wherein all segments (2, 3) are of an identical design.

11. The rotor according to one of claims 1 to 10, wherein all segments (2, 3) each have, in the region of the first longitudinal end (4), the first recess (6) and the first protrusion (8) with the first flank (10) of the first protrusion (8) delimiting the first recess (6), and have, in the region of the second longitudinal end (5), the second recess (7) and the second protrusion (9) with the first flank (13) of the second protrusion (8) delimiting the second recess (7), wherein the sealing ring (1) has an assembly state in which all pairs of those segments (2, 3) that are arranged adjacent in the sealing direction (1) are arranged in the coupling state.

12. A turbomachine with a rotor according to one of claims 1 to 11.

13. The turbomachine according to claim 12, wherein the sealing ring (1) is configured to seal a cooling air and / or a sealing air in the turbomachine.