Method for repairing a gas turbine engine component
A method of repairing a stator assembly of a gas turbine engine includes removing a worn surface of the stator assembly to provide a revealed area, and securing additional material to the stator assembly utilizing gas metal arc welding.
1. A method for repairing a stator assembly of a gas turbine engine, comprising the steps of:
a) removing a worn surface of the stator assembly to provide a revealed area; and
b) securing additional material to the stator assembly utilizing gas metal arc welding.
2. The method as recited in claim 1 , wherein said step a) includes the step of:
machining the worn surface down to a predefined dimension.
3. The method as recited in claim 2 , wherein the step of machining the worn surface down to the predefined dimension includes removal of sufficient material to remove any damaged portion of the stator assembly.
4. The method as recited in claim 1 , wherein the gas metal arc welding includes cold metal transfer.
5. The method as recited in claim 1 , wherein said step b) includes the step of:
securing the additional material to the revealed area of the stator assembly.
6. The method as recited in claim 1 , wherein the step of removing is performed prior to the step of securing.
7. The method as recited in claim 1 , comprising the step of:
c) removing a portion of the additional material.
8. The method as recited in claim 7 , wherein said step c) includes the step of:
machining the additional material down to a predefined dimension.
9. The method as recited in claim 7 , wherein the step of removing the portion of the additional material includes machining the additional material down to an original dimension of the component.
10. The method as recited in claim 1 , wherein the stator assembly is a component of a high pressure compressor of the gas turbine engine.
11. The method as recited in claim 1 , wherein the worn surface is a flange of the stator assembly.
12. The method as recited in claim 1 , wherein the worn surface is a featherseal slot of the stator assembly.
13. The method as recited in claim 1 , wherein the worn surface is a crack in the stator assembly.
14. The method as recited in claim 1 , wherein the additional material is applied manually to the stator assembly.
15. The method as recited in claim 1 , wherein the additional material is applied robotically to the stator assembly.
16. A method for repairing a gas turbine engine component, comprising the steps of:
removing a damaged portion of the component in a first machining operation to provide a revealed area;
securing additional material to the revealed area of the component using gas metal arc welding, wherein the gas metal arc welding includes a cold metal transfer process; and
removing at least a portion of the additional material in a second machining operation.