Laser shock peening for gas turbine engine weld repair

• US 5,846,057 A
• Filed: 03/25/1997
• Issued: 12/08/1998
• Est. Priority Date: 12/12/1995
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Cowie, William D., Mannava, Seetharamaiah, Ferrigno, Stephen J.
• Primary Examiner(s): Denion, Thomas E.
• Assistant Examiner(s): WOO, RICHARD SUKYOON
• Application Number:
  US08/823,414
• Time in Patent Office: 623 Days
• Field of Search: 416/241 R, 219/128.85
• US Class Current: 416/241.00R
• CPC Class Codes: B23P 6/007 using only additive methods, e.g. build-up welding
• CPC Class Codes: B23P 6/045 of turbine components, e.g. moving or stationary blades, rotors, etc.
• CPC Class Codes: C21D 10/005 by laser shock processing
• CPC Class Codes: C21D 9/50 for welded joints
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling
• CPC Class Codes: Y10T 29/49339 Hollow blade

Abstract

A crack weld repair and method, particularly, for a gas turbine engine blade or other metallic component in the engine, providing a metallic substrate, a metallic filler bonded onto a substrate bond surface on the metallic substrate, and a region having deep compressive residual stresses imparted by laser shock peening extending into the substrate beneath the substrate bond surface. One embodiment provides a laser shock peened surface below the weld material filled void in a damaged area of the component forming a region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the component. Optionally, the surface over the repaired area of the weld filled void may also be laser shock peened forming a second region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the weld repair. Another embodiment provides a weld buildup tip overlay on a substrate bond surface of an airfoil tip having a laser shock peened region beneath the substrate bond surface.

Claims

1. A gas turbine engine component comprising:

a metallic substrate,

a metallic filler bonded onto a substrate bond surface on said metallic substrate, and

a region having deep compressive residual stresses imparted by laser shock peening extending into said substrate beneath said substrate bond surface.

2. A gas turbine engine component as claimed in claim 1 further comprising:

a metallic body having a filled void,

said filled void extending between said substrate bond surface comprising surface areas of said body that bounds said void,

said void filled with a metallic repair material which is bonded to said surface areas,

at least one laser shock peened surface on said body having a corresponding laser shock peened region that extends into said body and which substantially bounds said void along said surface areas, and

said laser shock peened region having deep compressive residual stresses imparted by laser shock peening extending into said body from said laser shock peened surface.

3. A gas turbine engine component as claimed in claim 2 further comprising at least one other laser shock peened surface extending at least in part over an exterior surface area of said filled void such that at least one other laser shock peened region having deep compressive residual stresses imparted by laser shock peening extends into said filled void from said one other laser shock peened surface.

4. A gas turbine engine component as claimed in claim 3 wherein said metallic body comprises a single crystal cast alloy.

5. A gas turbine engine component as claimed in claim 3 wherein said metallic body comprises a directionally solidified cast alloy.

6. A gas turbine engine component as claimed in claim 3 wherein said gas turbine engine component is a turbine blade.

7. A gas turbine engine component as claimed in claim 6 wherein said void includes is a crack in a tip of an airfoil of said blade, said blade extending between a platform and said tip of said blade.

8. A gas turbine engine component as claimed in claim 7 wherein said turbine blade is a squealer turbine blade further comprising a radially extending wall that includes said tip and circumscribes said airfoil at a radially outer end of said airfoil forming an open cavity within said wall wherein said at least one laser shock peened surface comprises a first laser shock peened surface located along an inner side of said wall with respect to said cavity and said corresponding laser shock peened region comprises a first region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into said wall from said first laser shock peened surface, and further comprising:

a second laser shock peened surface located on an outer side of said wall with respect to said cavity,

a second region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into said airfoil from said second laser shock peened surface, and

said first and second laser shock peened regions substantially bounding and not extending into said filled void along said surface areas.

9. A gas turbine engine component as claimed in claim 8 further wherein said at least one other laser shock peened surface extending at least in part over said exterior surface area of said filled void comprises a third laser shock peened surface and said at least one other laser shock peened region comprises a third laser shock peened region.

10. A gas turbine engine component as claimed in claim 1 wherein said component comprises a metallic airfoil having a pressure side, a suction side, and a radially outer tip extending chordwise between a leading edge and a trailing edge of said airfoil,

said tip having an overlay portion bonded on a substrate portion,

said substrate portion having a region of deep compressive residual stresses imparted by laser shock peening (LSP) extending into said substrate portion from a laser shock peened surface between said overlay portion and said bonded substrate portion.

11. A gas turbine engine airfoil as claimed in claim 10 further comprising a second laser shock peened surface extending over an exterior surface area of said substrate portion.

12. A gas turbine engine airfoil as claimed in claim 10 further comprising:

a filled void extending through at least a portion of said substrate portion,

said filled void extending between surface areas of said metallic airfoil that bounds said void,

said void filled with a metallic repair material which is bonded to said surface areas,

at least one second laser shock peened surface on said airfoil body having a corresponding second laser shock peened region that extends into said body and which substantially bounds said void along said surface areas, and

said second laser shock peened region having deep compressive residual stresses imparted by laser shock peening extending into said body from said second laser shock peened surface.

13. A gas turbine engine airfoil as claimed in claim 12 further comprising a third laser shock peened surface extending over an exterior surface area of said overlay portion.

14. A gas turbine engine airfoil as claimed in claim 12 wherein said turbine blade is a squealer turbine blade further comprising a radially extending wall that includes said tip and circumscribes said airfoil at a radially outer end of said airfoil forming an open cavity within said wall and said overlay and substrate portions are located along said wall.

15. A gas turbine engine airfoil as claimed in claim 14 further comprising a third laser shock peened surface extending over an exterior surface area of said overlay portion.