Situ Gas Turbine Prevention of Crack Growth Progression

• US 20170218762A1
• Filed: 02/03/2016
• Published: 08/03/2017
• Est. Priority Date: 02/03/2016
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Diwinsky, David Scott, Roberts, Herbert Chidsey
• Application Number:
  US15/014,086
• Publication Number:
  US 20170218762A1
• Time in Patent Office: Days
• CPC Class Codes: B23K 26/382 by boring
• CPC Class Codes: B23P 6/045 of turbine components, e.g. moving or stationary blades, rotors, etc.
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: F01D 5/12 Blades specially adapted for radial flow machines or engines F01D5/04; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/13 using lasers
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: F05D 2260/83 Testing, e.g. methods, components or tools therefor

Abstract

Methods provided for remotely stopping a crack in a component of a gas turbine engine are provided, along with methods of remotely cleaning a surface area of a component of a gas turbine engine. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; and drilling a hole into the base of the defect. An integrated repair interface is also provided.

Claims

1. A method of remotely stopping a crack in a component of a gas turbine engine, the method comprising:

inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine;

positioning the tip adjacent to a defect within a surface of the component;

temporarily attaching the tip adjacent to the defect within the surface on the component; and

drilling a hole into the base of the defect.

2. The method as in claim 1, wherein the hole is drilled using a fiber optic laser drill.

3. The method as in claim 1, wherein the hole is drilled using a water jet.

4. The method as in claim 1, wherein the hole is drilled using a bead blast.

5. The method as in claim 1, wherein the hole is drilled using a mechanical twist drill.

6. The method as in claim 1, wherein the hole is drilled using a grinding ball.

7. The method as in claim 1, wherein the hole is formed to be about 10% to about 50% of the size of the base of the defect.

8. The method as in claim 1, wherein the hole is defined by a curved inner surface.

9. The method as in claim 1, wherein the hole is drilled in a desired location with precision accuracy within about 0.5 mm or less.

10. The method as in claim 1, wherein the hole has a hole size of about 0.1 mm to 3.25 mm in diameter.

11. The method as in claim 1, wherein the tip is attached using a tripod grip, a glue, or a vacuum sucker.

12. An integrated repair interface, comprising:

a cable delivery system having a controllable tip;

an attachment mechanism located on the cable delivery system for temporarily positioning the controllable tip onto a component within a gas turbine engine; and

a drilling means for forming a hole within the component.

13. The integrated repair interface of claim 12, wherein the drilling means comprises a fiber optic laser drill.

14. The integrated repair interface of claim 12, wherein the drilling means comprises a water jet.

15. The integrated repair interface of claim 12, wherein the drilling means comprises a bead blast.

16. The integrated repair interface of claim 12, wherein the drilling means comprises a mechanical twist drill.

17. The integrated repair interface of claim 12, wherein the drilling means comprises a grinding ball.

18. The integrated repair interface of claim 12, wherein the attachment mechanism comprises a tripod grip, a glue, or a vacuum sucker.

19. A method of remotely cleaning a surface area of a component of a gas turbine engine, the method comprising:

inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine;

positioning the tip adjacent to the area for cleaning on the component;

temporarily attaching the tip adjacent to the area for cleaning on the component; and

cleaning the area.

20. The method of claim 19, wherein cleaning the area is accomplished via a water jet, a grit blast, or a chemical spray.