Systems and methods for deep tip crack repair

Patent metadata

Field	Value
Publication number	US-10174617-B2
Application number	US-201514964616-A
Country	US
Kind code	B2
Filing date	Dec 10, 2015
Priority date	Dec 10, 2015
Publication date	Jan 8, 2019
Grant date	Jan 8, 2019

Abstract

The present application provides a method of repairing a turbine blade. The method may include the steps of removing an existing tip cap from the turbine blade in whole or in part, machining the turbine blade to form a machined groove, positioning an insert in the machined groove, welding the insert to the turbine blade, and brazing the turbine blade.

First claim

We claim:

1. A method of repairing a turbine blade comprising an airfoil, the method comprising:
removing an existing tip cap from the airfoil of the turbine blade in whole or in part to repair a crack in or about the tip cap and the airfoil;
machining the airfoil about the crack to form a machined groove comprising an open end and a closed end in the airfoil;
positioning an insert in the machined groove against the closed end of the machined groove, wherein the insert is undersized relative to the machined groove to provide a space between the open end of the machined groove and an end of the inert, wherein the space comprises a vertical gap having a vertical height extending between a top end of the insert and a surface of the airfoil about the open end of the machined groove;
welding the insert within the machined groove via a welding alloy within the space between the open end of the machined groove and the end of the inert to fill the vertical gap, wherein the welding alloy extends from the top end of the insert to the surface of the airfoil about the open end of the machined groove to lock the insert in place within the machined groove and to fill the vertical gap; and
brazing the turbine blade about the machined groove, the insert, welding alloy, and the airfoil to lock the insert in place within the machined groove.

2. The method of claim 1 , wherein the step of removing an existing tip cap comprises machining the tip cap.

3. The method of claim 1 , further comprising the step of replacing the tip cap on the turbine blade.

4. The method of claim 1 , further comprising the step of forming the insert.

5. The method of claim 4 , wherein the step of forming the insert comprises forming the insert from a pre-sintered preform material.

6. The method of claim 4 , wherein the step of forming the insert comprises forming the insert from a superalloy material.

7. The method of claim 4 , wherein the step of forming the insert comprises forming the insert from a base material.

8. The method of claim 4 , wherein the step of forming the insert comprises an additive manufacturing process.

9. The method of claim 1 , wherein the step of machining the turbine blade to form a machined groove comprises machining the machined groove to accommodate the insert.

10. The method of claim 1 , wherein the step of machining the turbine blade to form a machined groove comprises machining the machined groove to accommodate the insert and the welding alloy.

11. The method of claim 1 , wherein the step of welding the insert to the turbine blade comprises the welding alloy on top of the insert.

12. The method of claim 1 , wherein the step of brazing the turbine blade comprises brazing a brazeable paste thereon.

13. The method of claim 1 , wherein the turbine blade comprises a stage one bucket.

14. A method of repairing a turbine blade comprising an airfoil, the method comprising:
removing an existing tip cap from the airfoil of the turbine blade in whole or in part to repair a crack in or about the tip cap and the airfoil;
machining the airfoil about the crack to form a machined groove comprising an open end and a closed end in the air foil;
positioning a pre-sintered preform insert in the machined groove against the closed end of the machined groove, wherein the pre-sintered insert is undersized relative to the machined groove to provide a space between the open end of the machined groove and an end of the pre-sintered preform inert, wherein the space comprises a vertical gap having a vertical height extending between a top end of the pre-sintered preform insert and a surface of the airfoil about the open end of the machined groove;
welding the pre-sintered preform insert within the machined groove via a welding alloy within the space between the open end of the machined groove and the end of the pre-sintered preform inert to fill the vertical gap, wherein the welding alloy extends from top end of the pre-sintered preform insert to the surface of the airfoil about the open end of the machined groove to lock the pre-sintered preform insert in place within the machine groove and to fill the vertical gap; and
brazing the turbine blade about the machined groove, the insert, the welding alloy, and the airfoil to lock the pre-sintered preform insert place within the machined groove.

15. The method of claim 14 , wherein the step of removing an existing tip cap comprises machining the tip cap.

16. The method of claim 14 , further comprising the step of replacing the tip cap on the turbine blade.

17. The method of claim 14 , wherein the step of welding the insert to the turbine blade comprises the welding alloy on top of the insert.

18. The method of claim 14 , wherein the step of brazing the turbine blade comprises brazing a brazeable paste.

Assignees

• Gen Electric

Inventors

• Whims Lawrence James
• Connor James Ryan
• Dorriety Daniel James
• Kretschmar Andrea Booher
• Cook Paul A
• Henderson Brian Leslie

Classifications

• F05D2230/237

  Brazing · CPC title

• F05D2300/175

  Superalloys · CPC title

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title

• B33Y10/00

  Processes of additive manufacturing · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title