Methods of repairing integrally bladed rotors

Patent metadata

Field	Value
Publication number	US-9669489-B2
Application number	US-201514701164-A
Country	US
Kind code	B2
Filing date	Apr 30, 2015
Priority date	May 19, 2014
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A method of repairing an integrally bladed rotor includes removing a portion of the integrally bladed rotor to create a void in an airfoil, completely filling the void with a single replacement material, and laser shock peening the replacement material. Laser shock peening the replacement material imparts mechanical properties in the replacement material substantially the same as those in the forged material.

First claim

What is claimed is:

1. A method of repairing an integrally bladed rotor disk, comprising:
removing a portion of a integrally bladed rotor airfoil, thereby creating a void in the airfoil;
completely filling the void with a single replacement material; and
laser shock peening the replacement material, thereby imparting residual compressive stress in the replacement material.

2. A method as recited in claim 1 , wherein the step of laser shock peening includes laser shock peening both low-pressure and high-pressure sides of the airfoil.

3. A method as recited in claim 1 , wherein imparting residual compressive stress includes forming a compressive layer spanning from a high-pressure side to a low-pressure side of the airfoil.

4. A method as recited in claim 1 , further including the step of shaping the replacement material to conform the replacement material to a predetermined airfoil contour.

5. A method as recited in claim 1 , wherein the step of laser shock peening includes imparting mechanical properties in the replacement material substantially the same as those of an undamaged portion of the airfoil.

6. A method as recited in claim 5 , wherein the step of laser shock peening includes imparting mechanical properties in the transition portion substantially the same as those of the undamaged portion of the airfoil.

7. A method as recited in claim 1 , further including creating a heat-affected zone in a portion of the airfoil adjacent to the replacement material, and wherein the step of laser shock peening includes laser shock peening the replacement material and the heat-affected zone.

8. A method as recited in claim 1 , wherein the step of removing a portion of the integrally bladed rotor includes removing a stress riser.

9. A method as recited in claim 1 , wherein the step of removing a portion of the integrally bladed rotor includes removing a portion of a leading edge of the airfoil.

10. A method as recited in claim 1 , wherein filling the void with replacement material includes adding replacement material using a low-heat additive manufacturing process.

11. A method as recited in claim 1 , wherein filling the void with replacement material includes adding material using a laser welding process to add the replacement material.

12. A method as recited in claim 1 , wherein the step of removing a portion of the integrally bladed rotor includes removing damage associated with foreign object ingestion into a gas turbine engine.

13. A method of repairing an integrally bladed rotor disk, comprising:
removing a portion of a forged integrally bladed rotor airfoil, thereby creating a void in the airfoil;
completely filling the void with a single replacement material; and
laser shock peening the replacement material, thereby imparting residual compressive stress in the replacement material.

14. An integrally bladed rotor disk, comprising:
a rotor disk; and
a rotor blade with an airfoil extending from the rotor disk, the airfoil including:
a forged portion;
a replacement portion having uniform mechanical properties; and
a transition portion extending between the forged portion and the replacement portion, wherein mechanical properties in the replacement portion are substantially the same as those in the forged portion, and wherein mechanical properties in the transition portion are substantially the same as those in the forged portion.

15. An integrally bladed rotor as recited in claim 14 , wherein the replacement portion defines a low-pressure surface and a high-pressure surface of an airfoil.

16. An integrally bladed rotor as recited in claim 14 , wherein the transition portion is a heat-affected zone.

Assignees

• United Technologies Corp

Inventors

• Shepler Robert E
• Korn Nathan D

Classifications

• C21D10/005

  by laser shock processing · CPC title

• F05D2220/32

  in gas turbines · CPC title

• B23K26/356

  by shock processing · CPC title

• B22F3/24

  After-treatment of workpieces or articles {(B22F3/1146 takes precedence)} · CPC title

• B23K26/342 Primary

  Build-up welding · CPC title