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US 2014/0154082 A1Published application
Pre-sintered preform repair of turbine blades
AssigneeSiemens Energy, Inc.
InventorsBrandon W. Shinn, Atul L. Navale, James A. Yarbrough
Life of this patent
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Abstract
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.
Claims20
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;
- 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 more element
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;
- locating the preform on the tip shroud contact surface;
- and
- heat treating the preform and the tip shroud such that the preform is brazed to the tip shroud.
1 more element
A turbine blade comprising:
- an airfoil comprising upper and lower ends;
- a root coupled to said airfoil lower end, said root adapted to couple said blade to a rotatable disk;
- a tip shroud coupled to said airfoil upper end, said tip shroud having first and second spaced-apart contact surfaces;
- and
- a preform coupled to one of said tip shroud contact surfaces.
2 more elements
Dependencies are inferred from the claim text.