Repair of worn component surfaces

Patent metadata

Field	Value
Publication number	US-10654137-B2
Application number	US-201615286898-A
Country	US
Kind code	B2
Filing date	Oct 6, 2016
Priority date	Oct 8, 2015
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

The present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components ( 1, 10 ) of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps:
preparing the area to be repaired, in order to provide a smooth and clean surface ( 4 ), applying an Ni-based braze ( 7 ) with a proportion of hard material particles ( 8 ) to the surface ( 4 ) to form a repair layer ( 15 ), wherein the hard material particles comprise hard alloys based on cobalt or nickel, heat treating the component to braze the repair layer onto the component under vacuum conditions.

First claim

What is claimed is:

1. A method for repairing a wear-damaged component of a turbomachine, wherein the method comprises:
preparing an area to be repaired to provide a smooth and clean surface,
applying a Ni-based braze comprising hard material particles to the surface to form a repair layer, the hard material particles comprising a hard alloy based on cobalt or nickel,
heat treating the component with the Ni-based braze thereon under vacuum conditions to braze the repair layer onto the component.

2. The method of claim 1 , wherein the wear-damaged component of a turbomachine comprises elements of a flow duct boundary.

3. The method of claim 1 , wherein, when preparing the area to be repaired, material is removed from the area to be repaired.

4. The method of claim 3 , wherein the material is removed by machining.

5. The method of claim 1 , wherein, when preparing the area to be repaired, blasting with silicon carbide particles and/or nickel particles is performed and/or nickel electroplating is performed.

6. The method of claim 5 , wherein blasting with silicon carbide particles and/or nickel particles is performed and/or nickel electroplating is performed following material removal.

7. The method of claim 1 , wherein the Ni-based braze is applied in the form of a tape or a foil.

8. The method of claim 7 , wherein the braze tape or the braze foil is flexible and/or of multilayer construction.

9. The method of claim 7 , wherein a two-layer braze tape is used, an outer layer of which comprises hard material particles and an inner layer of which, for arrangement on the area to be repaired, does not comprise any hard material particles.

10. The method of claim 9 , wherein the outer layer of the braze tape comprises from 50 to 30 wt. % of hard material particles.

11. The method of claim 9 , wherein the outer layer of the braze tape comprises from 45 to 35 wt. % of hard material particles.

12. The method of claim 7 , wherein the braze tape or the braze foil is applied by a bonding agent or a braze paste to the area to be repaired and/or is surrounded with a braze paste.

13. The method of claim 1 , wherein air-drying at temperatures of from 60° C. to 70° C. takes place prior to the heat treatment.

14. The method of claim 1 , wherein the heat treatment comprises storing at a temperature of from 1150° C. to 1200° C. for from 10 to 25 min.

15. The method of claim 1 , wherein the heat treatment comprises storing at a temperature of from 1170° C. to 1180° C. for from 10 to 25 min.

16. The method of claim 1 , wherein the heat treatment comprises storing at a temperature of from 1150° C. to 1200° C. for from 15 to 20 min.

17. The method of claim 1 , wherein the heat treatment comprises heating under vacuum conditions at a heating rate of from 5° C./min to 30° C./min and/or intermediate storage at temperatures of from 400° C. to 1100° C. for a period of from 5 to 40 min.

18. The method of claim 1 , wherein the hard alloy comprises a Co—Mo—Cr—Si alloy.

19. The method of claim 11 , wherein the hard alloy comprises a Co—Mo—Cr—Si alloy.

20. A component of a turbomachine with a repair layer thereon, wherein the repair layer comprises a matrix of an Ni-based braze which has hard material particles comprising a hard alloy based on cobalt or nickel incorporated therein.

Assignees

• MTU Aero Engines AG

Inventors

• Daniels Bernd
• Hillen Michael
• Werner André

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D11/12

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title

• C25D3/12

  of nickel or cobalt · CPC title

• F01D5/005

  Repairing methods or devices · CPC title

• B23K1/20

  Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating · CPC title