Method for repairing a receiving hook for guide vanes

Abstract

Disclosed is a method for repairing a receiving hook for guide vanes, wherein the receiving hook is arranged in a housing of a turbomachine. The method comprises removing first material in a region of the receiving hook, which region extends over the circumference of the housing and thereafter applying second material in or on a region which extends over the circumference of the housing. The application of second material is performed using localized heat.

Claims

1. A method for repairing a receiving hook for a guide vane, which receiving hook is arranged in a housing of a turbomachine, wherein the method comprises: removing first material in a region of the receiving hook, which region extends over a circumference of the housing; followed by applying second material in or on a region which extends over the circumference of the housing, and applying the second material using localized heat.

2. The method of claim 1, wherein application of localized heat performed by a welding method, or corresponds thereto.

3. The method of claim 2, wherein the welding method comprises a laser powder build-up welding method and/or a plasma arc welding method.

4. The method of claim 2, wherein the welding method comprises a laser powder build-up welding method.

5. The method of claim 2, wherein the welding method comprises a plasma arc welding method.

6. The method of claim 2, wherein a welding filler is used when applying the second material.

7. The method of claim 1, wherein application of second material is performed in multiple layers which are applied in circumferential direction.

8. The method of claim 7, wherein a layer is from 0.1 mm to 1 mm thick.

9. The method of claim 8, wherein a layer is from 0.5 mm to 2 mm wide.

10. The method of claim 8, wherein a layer is about 1 mm wide.

11. The method of claim 7, wherein a layer is about 0.3 mm thick.

12. The method of claim 11, wherein a layer is from 0.5 mm to 2 mm wide.

13. The method of claim 11, wherein a layer is about 1 mm wide.

14. The method of claim 7, wherein a layer is from 0.5 mm to 2 mm wide.

15. The method of claim 7, wherein a layer is about 1 mm wide.

16. The method of claim 1, wherein the method further comprises heat-treating the receiving hook or one or more sections thereof after application of the second material.

17. The method of claim 16, wherein the method further comprises finishing the receiving hook by a material-removing method.

18. The method of claim 1, wherein the method further comprises finishing the receiving hook by a material-removing method.

19. The method of claim 18, wherein the finishing of the receiving hook is in order to obtain structurally predefined shapes.

20. The method of claim 1, wherein a welding filler is used when applying the second material.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The present invention is explained by way of example with reference to the appended drawings, in which identical reference signs refer to identical or similar components. In the respectively schematically simplified figures:

(2) FIG. 1 shows a compressor housing of a gas turbine having a plurality of worn receiving hooks for guide vanes;

(3) FIG. 2 shows, in a detail view, a worn receiving hook from FIG. 1; and

(4) FIG. 3a-d show method steps according to the invention for repairing a worn receiving hook.

DETAILED DESCRIPTION OF THE PRESENT INVENTION

(5) The particulars shown herein are by way of example and for purposes of illustrative discussion of the embodiments of the present invention only and are presented in the cause of providing what is believed to be the most useful and readily understood description of the principles and conceptual aspects of the present invention. In this regard, no attempt is made to show details of the present invention in more detail than is necessary for the fundamental understanding of the present invention, the description in combination with the drawings making apparent to those of skill in the art how the several forms of the present invention may be embodied in practice.

(6) FIG. 1 shows a compressor housing 100 of a gas turbine, having a plurality of worn receiving hooks 200 for guide vanes. The guide vanes are inserted in annular fashion into the receiving hooks 200 and are connected thereto.

(7) The principal throughflow direction 1 of the gas turbine and of the compressor housing runs in the axial direction a, as shown by means of an arrow. The radial direction r is oriented radially outward from the central axis 3 of the gas turbine.

(8) A forward portion 5 and a rear portion 7 of the compressor housing may be distinguished. In this exemplary embodiment, worn receiving hooks 200 in the rear portion 7 of the compressor housing are in particular represented or discussed.

(9) FIG. 2 shows a worn receiving hook 200 from FIG. 1 in a detail view.

(10) Wear marks are represented by means of an abrasion region 11 at an inner diameter 9 (as seen in the radial direction r) of the upper region of the receiving hook 200.

(11) Equally, wear marks are represented by means of an abrasion region 15 at an outer diameter 13 of the receiving hook 200.

(12) FIG. 3a shows a lower region of a worn receiving hook 200, based on the view in FIG. 2, in a further detail view. The abrasion region 11 is represented at the inner diameter 9, and the abrasion region 15 at the outer diameter 13.

(13) The state of the receiving hook in FIG. 3a corresponds to the starting state for the method according to the invention.

(14) FIG. 3b shows the method step, according to the invention, of removing first material from the region 17 of the receiving hook 200. The shaded representation in the region 17 shows the first material which is to be removed or which has already been removed. The shading indicates a layer-by-layer removal of the first material.

(15) First material is removed both at the inner diameter 9 and at the outer diameter 13. The removal is performed over the entire circumference of the receiving hook.

(16) FIG. 3c shows the method steps, according to the invention, of applying second material in the region 17 of the receiving hook 200. The shaded representation in the region 17 shows the second material which is to be applied or which has already been applied.

(17) The second material is applied, for example, by means of a laser powder build-up welding method. The powder may be applied layer by layer, as indicated by the shading.

(18) FIG. 3d shows the contour 19 (the thick line) of the finished region 17 of the receiving hook 200. FIG. 3d represents the reconstructed region 17 after carrying out the method steps of the method according to the invention.

(19) While the present invention has been described with reference to exemplary embodiments, it is understood that the words which have been used herein are words of description and illustration, rather than words of limitation. Changes may be made, within the purview of the appended claims, as presently stated and as amended, without departing from the scope and spirit of the present invention in its aspects. Although the present invention has been described herein with reference to particular means, materials and embodiments, the present invention is not intended to be limited to the particulars disclosed herein; rather, the present invention extends to all functionally equivalent structures, methods and uses, such as are within the scope of the appended claims.

(20) TABLE-US-00001 List of reference signs Reference sign Description 100 Compressor housing of a gas turbine 200 Receiving hook a Axial direction r Radial direction 1 Principal throughflow direction 3 Central axis 5 Forward portion of the compressor housing 7 Rear portion of the compressor housing 9 Inner diameter 11 Abrasion region at the inner diameter 13 Outer diameter 15 Abrasion region at the outer diameter 17 Region of the receiving hook for the removal of first material and for the application of second material 19 Finished contour of the receiving hook