Pre-sintered preform repair of turbine blades
A process is provided for repairing a damaged portion of a gas turbine blade comprising: providing a preform comprising a low-melt alloy material and a base alloy material; locating the preform on the gas turbine engine blade damaged portion; and heat treating the preform and the blade such that the preform is brazed to the blade.
1. A process for repairing a damaged portion of a gas turbine blade comprising:
providing a preform comprising a low-melt alloy material and a base alloy material consisting essentially of materials forming the blade;
locating the preform on the gas turbine engine blade damaged portion;
heat treating the preform and the blade such that the preform is brazed to the blade; and
after heat treating, further comprising welding filler material to the preform.
2. The process of claim 1 , wherein said preform comprises about 70 to about 80% by weight base alloy material and about 30 to about 20% by weight low-melt alloy material based on the total weight of the preform prior to heat treating.
3. The process of claim 1 , prior to heat treating, further comprising spot-welding the preform to the blade.
4. The process of claim 1 , prior to heat treating, further comprising resistance welding the preform to the blade.
5. The process of claim 1 , further comprising grinding the damaged portion prior to locating the preform on the damaged portion.
6. The process of claim 1 , further comprising machining the preform and the blade after heat treating.
7. The process of claim 1 , further comprising adding a braze material to the blade damaged portion prior to locating the preform on the damaged portion.
8. A process for repairing a damaged contact surface of a tip shroud of a gas turbine blade comprising:
providing a preform comprising a low-melt alloy material and a base alloy material consisting essentially of materials forming the tip shroud;
locating the preform on the tip shroud contact surface;
heat treating the preform and the tip shroud such that the preform is brazed to the tip shroud; and
after heat treating, further comprising welding filler material to the preform.
9. The process of claim 8 , wherein the preform comprises about 70 to about 80% by weight base alloy material and about 30 to about 20% by weight low-melt alloy material based on the total weight of the preform prior to welding and heat treating.
10. The process of claim 8 , prior to heat treating, further comprising spot-welding the preform to the blade.
11. The process of claim 8 , prior to heat treating, further comprising resistance welding the preform to the blade.
12. The process of claim 8 , further comprising grinding the damaged section prior to locating the preform on the contact surface.
13. The process of claim 8 , further comprising adding a braze material to the tip shroud contact surface prior to locating the preform on the contact surface.
14. The process of claim 8 , wherein said heat treating comprises a low-melt heat treatment.