In Situ Gas Turbine Prevention of Crack Growth Progression

• US 20170218764A1
• Filed: 02/03/2016
• Published: 08/03/2017
• Est. Priority Date: 02/03/2016
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Diwinsky, David Scott, Roberts, Herbert Chidsey, Grady, Wayne R.
• Granted Patent: US 10,094,221 B2
• Time in Patent Office: Days
• 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 2230/30 with deposition of material
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods

Abstract

Methods for remotely joining material a surface area of a component of a gas turbine engine are provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning a tip of the integrated repair interface adjacent to a defect defined within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface of the component; and supplying a new material to the area to fill the defect.

Claims

1. A method of remotely joining material 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 a tip of the integrated repair interface adjacent to a defect defined within a surface of the component;

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

supplying a new material to the area to fill the defect.

2. The method as in claim 1, wherein the new material is a liquid metal, and wherein supplying the material to the area to fill the defect comprises:

supplying the liquid metal from a material supply end of the repair tool to a tip end of the repair tool; and

expelling the liquid metal from the tip end of the repair tool in a direction of the defect such that the fillable volume is at least partially filled with the liquid metal.

3. The method as in claim 2, wherein the repair tool includes a high temperature conduit extending lengthwise between the material supply end of the repair tool and the tip end of the repair tool, wherein supplying the liquid metal from the material supply end of the repair tool to the tip end of the repair tool comprises supplying the liquid metal through the high temperature conduit to the tip end of the repair tool

4. The method of claim 3, wherein the high temperature conduit is formed from a ceramic material.

5. The method of claim 3, wherein the repair tool further includes a heating element provided in operative association with the high temperature conduit, further comprising generating heat within the high temperature conduit via the heating element as the liquid metal is being supplied through the high temperature conduit

6. The method of claim 2, wherein the repair tool includes a nozzle positioned at or adjacent to the tip end of the repair tool, wherein expelling the liquid metal from the tip end of the repair tool comprises expelling the liquid metal from the nozzle such that the liquid metal is directed into the fillable volume defined by the defect.

7. The method of claim 1, further comprising:

inserting an optical probe through the access port or an adjacent access port of the gas turbine engine, the optical probe being configured to provide a view of the defect within the gas turbine engine.

8. The method of claim 7, wherein positioning the tip end of the repair tool adjacent to the defect comprises positioning the tip end relative to the defect based on the view provided by the optical probe.

9. The method of claim 1, wherein the tip is attached using a tripod grip, a glue, or a vacuum sucker.

10. The method of claim 1, wherein the new material is supplied as a solid particle into the defect.

20. The method of claim 1, wherein the new material is supplied as a solid particle onto the surface.

11. A method of remotely joining material 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 joining material on the component;

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

supplying a new material to the area to build up a surface of the component.

12. The method as in claim 11, wherein the component is an airfoil.

13. The method as in claim 12, wherein the surface defines a tip of the airfoil.

14. The method as in claim 11, wherein the new material is a liquid metal, and wherein supplying the material to the area to build up the surface of the component comprises:

supplying the liquid metal from a material supply end of the repair tool to a tip end of the repair tool; and

expelling the liquid metal from the tip end of the repair tool in a direction of the surface.

15. The method as in claim 14, wherein the repair tool includes a high temperature conduit extending lengthwise between the material supply end of the repair tool and the tip end of the repair tool, wherein supplying the liquid metal from the material supply end of the repair tool to the tip end of the repair tool comprises supplying the liquid metal through the high temperature conduit to the tip end of the repair tool.

16. The method of claim 15, wherein the high temperature conduit is formed from a ceramic material.

17. The method of claim 11, further comprising:

inserting an optical probe through the access port or an adjacent access port of the gas turbine engine, the optical probe being configured to provide a view of the surface within the gas turbine engine.

18. The method of claim 17, wherein positioning the tip end of the repair tool adjacent to the surface comprises positioning the tip end relative to the surface based on the view provided by the optical probe.

19. The method of claim 11, wherein the tip is attached using a tripod grip, a glue, or a vacuum sucker.