Repair method for gas turbine engine components
A method for repairing a gas turbine engine component includes applying a braze slurry to a first portion of the component, applying a pre-sintered preform to a second portion of the component that is different than the first portion, and brazing the component.
1. A method for repairing a gas turbine engine component, comprising the steps of:
a) applying a braze slurry that includes a pasty compound of metal powders to a first portion of the component, wherein the step of applying includes applying the braze slurry within a groove of the component;
b) applying a pre-sintered preform to a second portion of the component that is different from the first portion; and
c) brazing the component subsequent to said steps a) through b).
2. The method as recited in claim 1 , comprising the step of:
d) cleaning a surface of the component to be repaired.
3. The method as recited in claim 2 , wherein said step d) includes the steps of:
performing a fluoride ion cleaning operation on the component; and
performing an abrasive blast operation on the component subsequent to the fluoride ion cleaning operation.
4. The method as recited in claim 1 , comprising the step of:
d) performing a machining operation on the component subsequent to said steps a) through c).
5. The method as recited in claim 4 , wherein the machining operation includes a high-speed grinding operation.
6. The method as recited in claim 1 , wherein the braze slurry includes a mixture of a first alloy powder and a second alloy powder.
7. The method as recited in claim 6 , wherein the first alloy powder includes a composition having Ni—14% CR—10% Co—4% Al—3% B and the second alloy powder includes a composition having Ni—12% Co—7% Cr—6% Ta—6% Al—5% W—3% Ra—2% Hf—2% Mo.
8. The method as recited in claim 1 , wherein the pre-sintered preform includes a sintered mixture of two alloy powders.
9. The method as recited in claim 8 , wherein the two alloy powders include compositions of Ni—12% Co—7% Cr—6% Ta—6% Al—5% W—3% Ra—2% Hf—2% Mo with Ni—14% Cr—10% Co—4% Al—3% B.
10. The method as recited in claim 1 , wherein the component is made of a nickel-based superalloy.
11. The method as recited in claim 1 , wherein the braze slurry is applied between the pre-sintered preform and the component.
12. The method as recited in claim 1 , wherein said step c) includes the step of:
performing a vacuum furnace combination melt and diffusion cycle on the component.
13. The method as recited in claim 1 , wherein said step a) is performed prior to said step b).
14. The method as recited in claim 1 , wherein said step a) and said step b) are performed prior to removing any surface of the component.
15. The method as recited in claim 1 , wherein the pre-sintered preform is positioned at least partially over the groove such that the braze slurry is between the pre-sintered preform and the component.
16. A method for repairing a gas turbine engine component, comprising the steps of:
a) applying a braze slurry within a groove of the component, wherein the braze slurry includes a pasty compound of metal powders;
b) applying a pre-sintered preform to a second portion of the component that is different from the groove; and
c) brazing the component subsequent to said steps a) through b).