SEALING SYSTEM WITH WELDED-ON SEALING PLATE, TURBOMACHINE, AND MANUFACTURING METHOD

Abstract

A sealing system (100) for a turbomachine is provided which includes a support (10) designed as a ring part, and a ring-like sealing plate (20, 30) that protrudes from the support in the axial direction (X). The support includes a fastening section (11) for fastening the sealing system to a stator part (200), and a retaining area (12), situated radially within the fastening section, for retaining a radial gap seal (40). The sealing plate (20, 30) is welded to the support (10) radially outside the retaining area (12). Also provided are a turbomachine that includes a sealing system (100), a support (10) for a sealing system, and a method for manufacturing a sealing system.

Claims

1. A sealing system for a turbomachine, the sealing system comprising: a support designed as a ring part, and having a fastening section for fastening the sealing system to a stator part, and a retaining area, situated radially within the fastening section, for retaining a radial gap seal; and a ring-shaped sealing plate protruding from the support in an axial direction and welded to the support radially outside the retaining area.

2. The sealing system as recited in claim 1 wherein the support is a turned part.

3. The sealing system as recited in claim 1 wherein an edge of the sealing plate protruding farthest from the support in the axial direction is bent radially inwardly.

4. The sealing system as recited in claim 1 wherein an average thickness of the sealing plate is at most 1.5 mm.

5. The sealing system as recited in claim 1 wherein an average thickness of the sealing plate is at most 1.0 mm.

6. The sealing system as recited in claim 1 wherein an average thickness of the sealing plate is at least 0.5 mm.

7. The sealing system as recited in claim 1 wherein an average thickness of the sealing plate is at least 0.6 mm.

8. The sealing system as recited in claim 1 wherein the fastening section includes an annular area configured for resting on one side against a first surface area of the stator part, while a second surface area of the stator part axially opposite from the first surface area is exposed.

9. The sealing system as recited in claim 8 wherein the annular area includes a surface section that extends radially outside the sealing plate in the radial direction.

9. The sealing system as recited in claim 1 wherein the sealing plate is a first sealing plate, and further comprising at least one second ring-shaped sealing plate welded to the support and protruding from the support in the axial direction, opposite from the first sealing plate.

10. The sealing system as recited in claim 9 wherein the first and the second sealing plates are welded on at a same distance from a center axis of the support.

11. The sealing system as recited in claim 9 wherein the first and the second sealing plates are welded on at different distances from a center axis of the support.

12. The sealing system as recited in claim 1 wherein an edge of the sealing plate or of a further sealing plate: is placed on a flat surface area of the support, is mounted on a radially outwardly situated support edge of the support, or is flush mounted on a protruding edge protruding from a support surface in the axial direction; and welded on.

13. A turbomachine comprising the sealing system as recited in claim 1, and at least one stator part fastened to the fastening section of the support of the sealing system.

14. A support for the sealing system, the support comprising: a ring part, and having a fastening section for fastening the sealing system to a stator part, and a retaining area, situated radially within the fastening section, for retaining a radial gap seal, the support designed as a turned part and having a weld area for a ring-shaped sealing plate protruding from the support in an axial direction, the weld area being radially outside the retaining area.

15. A method for manufacturing a sealing system as recited in claim 1, the method comprising: manufacturing the support; and welding the sealing plate to the support radially outside the retaining area so that the sealing plate protrudes from the support in the axial direction.

16. The method as recited in claim 15 wherein the manufacturing step takes place with the aid of turning.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Preferred exemplary embodiments of the present invention are explained in greater detail below with reference to the drawings. It is understood that individual elements and components may also be combined in a different way than described. Reference numerals for mutually corresponding elements are used throughout the figures, and are not described anew for each figure.

[0029] FIG. 1 schematically shows a sectional area of a meridian section of an example of a sealing system according to the present invention; and

[0030] FIG. 2 schematically shows a section of a turbomachine according to the present invention, with the sealing system illustrated in FIG. 1 in a meridian section.

DETAILED DESCRIPTION

[0031] FIG. 1 illustrates a sectional area of a meridian section of one specific embodiment of a sealing system 100 according to the present invention along a provided rotor axis that extends in axial direction X. It is understood that in the case that the sealing system forms a full ring, the entire meridian section includes an oppositely situated (relative to the rotor axis) second sectional area which preferably has an analogous design.

[0032] Sealing system 100 includes a (preferably monolithic) support 10 that includes a fastening section 11 and a retaining area 12. The support 10 is designed as a ring part (not discernible in the figure), and as such completely or partially surrounds a central axis that coincides with the provided rotor axis. The support is preferably designed as a turned part, i.e., is manufactured with the aid of cutting turning.

[0033] Fastening section 11 is configured for being fastened to a stator part such as a section of a guide vane, for example. The fastening section includes an annular groove 14 which protrudes radially into the support from the outside into the inside and into which the stator part may be inserted. A borehole 15 passes through the two side walls of the annular groove. A stator part that is inserted or is to be inserted preferably likewise includes a borehole at the corresponding location, so that, as shown in FIG. 2, a bolt 110 may be guided through the side walls of the annular groove and stator part 200 in order to fix the latter in annular groove 14. Bolt 110 may be riveted or screwed, for example, in this position.

[0034] The two side walls of annular groove 14 have different extensions in radial direction R: Thus, at one of the side walls an annular area 13 is formed which, as is once again apparent in FIG. 2, is configured for resting on one side against a first surface area 201 of an inserted stator part 200, while a second surface area 202 of the stator part axially opposite from surface area 201 is exposed.

[0035] Retaining area 12 is situated radially within fastening section 11 (i.e., farther inwardly than the fastening section, relative to radial direction R). The retaining area retains a radial gap seal 40 that is provided for sealing a radial gap between the stator and the rotor. In the illustrated example, radial gap seal 40 is designed as a honeycomb seal which may be soldered, for example, to retaining area 12 of support 10 (preferably under vacuum).

[0036] Sealing system 100 also includes two sealing plates 20, 30 that are welded to support 10 radially outside retaining area 12 and spaced apart from same, so that the sealing system includes corresponding weld seams 22, 32. The sealing plates protrude from support 10 on mutually opposite sides in axial direction X. At their edges 21, 31 opposite from respective weld seam 22, 32, which are axially farthest away from the support, the sealing plates are each bent radially inwardly. In this way, radial flows may be advantageously deflected inwardly, and leaks may thus be reduced overall.

[0037] Sealing plates 20, 30 each have an average thickness d1 and d2, respectively, that is preferably at most 1.5 mm or at most 1 mm and/or at least 0.5 mm or at least 0.6 mm. Thicknesses d.sub.1 and d.sub.2 of the two sealing plates 20, 30 may be the same or different.

[0038] In the illustrated exemplary embodiment, sealing plate 20 is welded on farther radially inwardly than second sealing plate 30. In particular, sealing plate 20 is placed on a flat surface area 16 of support 10 and welded on there, so that support 10 extends radial outwardly beyond weld seam 22. In the exemplary embodiment shown, the support forms annular area 13 there.

[0039] In contrast, sealing plate 30 is placed on an edge 17 that protrudes from support surface 10 in axial direction X and is welded on there, and thus protrudes from support 10 in the opposite direction from first sealing plate 20. An extension of edge 17 from support surface 18 in the axial direction is preferably at least 2.5 mm or at least 3 mm and/or at most 4.8 mm, preferably at most 4.1 mm.

[0040] FIG. 2 shows sealing system 100 in the interior of a turbomachine: the sealing system, as described above, is fastened to a stator part 200 in the form of a guide vane that includes a guide vane airfoil 210 and a platform 220. A rotor 300 includes sealing fins 330 that are configured for running into radial gap seal 40 of the sealing system, and together with same sealing off the radial gap between rotor 300 and stator part 200. It is understood that rotor 300 may be made up of multiple individual parts.

[0041] Radial flows that occur are deflected by sealing plates 20, 30 of sealing system 100 together with projections 320 at moving vanes 310 adjacent to guide vane 200, and with platform 220 of guide vane 200, and are thus decelerated, thereby reducing leaks.

[0042] A sealing system 100 for a turbomachine is provided which includes a support 10 designed as a ring part, and a ring-like sealing plate 20, 30 that protrudes from the support in axial direction X. The support includes a fastening section 11 for fastening the sealing system to a stator part 200, and a retaining area 12, situated radially within the fastening section, for retaining a radial gap seal 40. Sealing plate 20, 30 is welded to support 10 radially outside retaining area 12.

[0043] Also provided are a turbomachine that includes a sealing system 100, a support 10 for a sealing system, and a method for manufacturing a sealing system.

LIST OF REFERENCE NUMERALS

[0044] 10 support [0045] 11 fastening section [0046] 12 retaining area [0047] 13 annular area [0048] 14 annular groove [0049] 15 borehole [0050] 16 surface area of the support [0051] 17 edge protruding from support surface 18 [0052] 18 support surface [0053] 20, 30 sealing plate [0054] 21, 31 edge of the sealing plate [0055] 22, 32 weld seam [0056] 40 radial gap seal [0057] 100 sealing system [0058] 110 bolt [0059] 200 stator part (in the form of a guide vane) [0060] 201, 202 surface area of the stator part [0061] 210 guide vane airfoil [0062] 220 platform [0063] 300 rotor [0064] 310 moving vane [0065] 320 projection of the row of moving vanes [0066] 330 sealing fin [0067] d.sub.1, d.sub.2 average thickness of sealing plate 20, 30 [0068] R radial direction [0069] X axial direction