Laser casting blade repair

Patent metadata

Field	Value
Publication number	US-9476304-B2
Application number	US-201313892058-A
Country	US
Kind code	B2
Filing date	May 10, 2013
Priority date	May 10, 2013
Publication date	Oct 25, 2016
Grant date	Oct 25, 2016

Abstract

A method for repairing a rotor wheel including an airfoil using a blade repair assembly is disclosed. The blade repair assembly includes a first block and a second block, each including a contact surface with a shape of at least a portion of the airfoil and a cavity surface adjacent the contact surface. The method includes pre-machining an airfoil edge to a uniform height. The method also includes clamping the first block and the second block to the airfoil forming a cavity with the cavity surfaces and the airfoil edge. The method also includes filling the cavity with a metal including metallurgically bonding the metal to the airfoil.

First claim

What is claimed is:

1. A method for repairing a rotor wheel airfoil including an airfoil edge using a blade repair assembly including a first block including a first contact surface with a shape of at least a portion of the airfoil and a first cavity surface adjacent the first contact surface, and including a second block including a second contact surface with a shape of at least a portion of the airfoil and a second cavity surface adjacent the second contact surface, the first block and the second block each including a thermal diffusivity of at least one-hundred millimeters squared per second, the method comprising:
pre-machining the airfoil edge to a uniform height;
clamping the first block and the second block to the airfoil forming a cavity with the first cavity surface, the second cavity surface, and the airfoil edge, wherein the first and second cavity surfaces have angles from about five to twenty degrees which diverge from the cavity;
filling the cavity with a metal including
melting the metal, and
metallurgically bonding the metal to the airfoil forming a bonded portion; and

unclamping the first block and the second block from the airfoil.

2. The method of claim 1 , further comprising cooling the first block and the second block with a liquid.

3. The method of claim 2 , wherein cooling the first block and the second block with the liquid includes directing water through cooling channels located in the first block and the second block.

4. The method of claim 1 , further comprising machining the airfoil to remove any overbuild from the bonded portion.

5. The method of claim 1 , wherein metallurgically bonding the metal to the airfoil includes welding the metal to the airfoil with a laser cladding process.

6. The method of claim 5 , further comprising melting the metal and metallurgically bonding the metal to the airfoil with a laser with a spot diameter larger than a width of the airfoil edge.

7. The method of claim 1 , wherein clamping the first block to the second block includes fastening a first block forward tab of the first block to a second block forward tab of the second block, and fastening a first block aft tab of the first block to a second block aft tab of the second block.

8. A method for remanufacturing a rotor wheel for a turbocharger, the rotor wheel including an airfoil with an airfoil edge using a blade repair assembly including a first block and a second block, the method comprising:
pre-machining the airfoil edge to a uniform height;
clamping the first block to the second block, the first block including copper, a first contact surface with a first shape of at least a first portion of the airfoil, and a first cavity surface adjacent the first contact surface and the second block including copper, a second contact surface with a second shape of at least a second portion of the airfoil, and a second cavity surface adjacent the second contact surface to the airfoil forming a cavity with the first cavity surface, the second cavity surface, and the airfoil edge, wherein the first and second cavity surfaces have angles from about five to twenty degrees which diverge from the cavity;
filling the cavity with a metal including
welding the metal to the airfoil forming a bonded portion;

cooling the first block and the second block when filling the cavity with the metal;
unclamping the first block and the second block from the airfoil; and
machining the airfoil including the bonded portion.

9. The method of claim 8 , wherein machining the airfoil including the bonded portion includes removing any overbuild from the bonded portion.

10. The method of claim 8 , further comprising removing the rotor wheel from a compressor housing prior to pre-machining the airfoil edge to a uniform height.

11. The method of claim 8 , further comprising removing the rotor wheel from a turbine housing prior to pre-machining the airfoil edge to the uniform height.

12. The method of claim 8 , wherein welding the metal to the airfoil forming the bonded portion includes laser cladding the metal to the airfoil.

13. A rotor wheel remanufactured by clamping a first block and a second block to the rotor wheel forming a cavity with a first cavity surface, a second cavity surface, and the rotor wheel and filling the cavity with a metal including metallurgically bonding the metal to the rotor wheel, the rotor wheel comprising:
a hub including an axial portion that curves to a radial portion; and
an airfoil extending from the hub, the airfoil including
an airfoil edge, and
a bonded portion metallurgically bonded to the airfoil edge, the bonded portion including
a first side extending from the airfoil edge at a first angle, the first angle corresponding to an angle of the first cavity surface diverging from the cavity at an angle of about five to twenty degrees, and
a second side extending from the airfoil edge at a second angle, the second angle corresponding to an angle of the second cavity surface diverging from the cavity at an angle of about five to twenty degrees.

14. The rotor wheel of claim 13 , wherein the airfoil includes a nickel based alloy.

15. The rotor wheel of claim 13 , wherein the airfoil includes titanium.

16. The rotor wheel of claim 13 , wherein the first side and the second side are machined flush to sides of the airfoil edge to form an airfoil profile.

17. The rotor wheel of claim 13 , wherein the bonded portion also includes a forward side, adjacent the first side and the second side, extending from a leading edge of the airfoil at a third angle and an aft side, adjacent the first side and the second side, extending from a trailing edge of the airfoil opposite the forward side at a fourth angle.

Assignees

• Caterpillar Inc

Inventors

• Marchione Thierry Andre

Classifications

• B23K2101/001

  Turbines · CPC title

• F05D2220/40

  in turbochargers · CPC title

• B23K9/044

  Built-up welding on three-dimensional surfaces · CPC title

• Y10T29/49318

  Repairing or disassembling · CPC title

• F05D2230/21

  by casting · CPC title