Method of repairing a turbine engine component

Patent metadata

Field	Value
Publication number	US-9643286-B2
Application number	US-69673907-A
Country	US
Kind code	B2
Filing date	Apr 5, 2007
Priority date	Apr 5, 2007
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component.

First claim

The invention claimed is:

1. A method of repairing a turbine engine, comprising the steps of:
a) identifying a turbine engine component having a damaged area;
b) removing a portion of the turbine engine component proximate the damaged area to accommodate an overlay;
c) placing the overlay in a location previously occupied by the removed portion; and
d) attaching the overlay to the turbine engine component, wherein the turbine engine component has an original shape prior to having the damaged area, and the overlay has a surface mimicking and conforming generally to at least a portion of the original shape of the turbine engine component, wherein the overlay is a strip of roll-formed material, wherein the overlay includes a first portion extending transversely from a second portion, the first portion having a planar shape, the second portion having a first area with a planar shape and a second area with a curved shape.

2. The method of claim 1 , wherein the overlay is selected from a variety of overlays having different dimensions.

3. The method of claim 2 , wherein each of the variety of overlays has a surface mimicking at least a portion of the original shape of the turbine engine component.

4. The method of claim 1 wherein the original shape is a shape of a finished outer surface of the turbine engine component prior to the turbine engine component having the damaged area.

5. The method of claim 1 , wherein the original shape has a first turbine engine component surface different than a second turbine engine component surface, the overlay having a first overlay surface mimicking the first turbine engine component surface and a second overlay surface mimicking the second turbine engine component surface.

6. The method of claim 1 , wherein the turbine engine component comprises a shroud segment of the turbine engine.

7. The method of claim 1 , wherein attaching comprises welding the overlay to the turbine engine component.

8. The method of claim 1 wherein attaching comprises brazing the overlay to the turbine engine component.

9. The method of claim 1 wherein attaching comprises adhering the overlay to the turbine engine component.

10. The method of claim 1 , wherein the overlay is made of the same material as the turbine engine component.

11. A method of repairing a turbine engine component, comprising the steps of:
a) identifying a shroud segment having a damaged area;
b) removing a portion of the shroud segment proximate the damaged area to accommodate an overlay;
c) placing the overlay in a location previously occupied by the removed portion; and
d) attaching the overlay to the shroud segment, wherein the shroud segment has an original shape prior to having the damaged area, the overlay having a surface mimicking at least a portion of the original shape of the shroud segment such that machining is not required to conform the surface to the original shape, wherein the overlay includes a first portion extending transversely from the second portion, the first portion including a planar surface area, the second portion including both a curved surface area and a planar surface area separate from the curved surface area.

12. The method of claim 11 wherein the overlay is selected from a variety of overlays having different dimensions.

13. The method of claim 12 wherein each of the variety of overlays has the surface mimicking at least a portion of the original shape of the shroud segment.

14. The method of claim 11 , wherein the original shape has a first shroud surface different than a second shroud surface, the overlay having a first overlay surface mimicking the first shroud surface and a second overlay surface mimicking the second shroud surface.

15. The method of claim 11 , wherein attaching comprises welding the overlay to the shroud segment.

16. The method of claim 11 , wherein attaching comprises brazing the overlay to the shroud segment.

17. The method of claim 11 , wherein attaching comprises adhering the overlay to the shroud segment.

18. The method of claim 11 , wherein the overlay is made of the same material as the shroud segment.

19. The method of claim 11 , wherein the overlay is roll-formed.

Assignees

• Reynolds George H
• Addis Mark E
• United Technologies Corp

Inventors

• Reynolds George H
• Addis Mark E

Classifications

• Y10T29/49737

  Metallurgically attaching preform · CPC title

• Y10T29/49734

  and removing damaged material · CPC title

• B23P6/005 Primary

  using only replacement pieces of a particular form · CPC title

• Y10T29/49318

  Repairing or disassembling · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title