Loading patent…
AssigneeSiemens Energy, Inc.
InventorsHang Li, Mark A. Garcia, Somesh J. Ghunakikar, William J. Lowe
Estimating the term…
A process for repairing combined heavy erosion and thermal fatigue cracks and/or other defects, such as large cracks, in a high temperature superalloy component, such as a vane in a turbine section of a gas turbine engine, that does not require mechanical grinding to prepare the defect site. The process includes depositing a loose finely granulated superalloy powder or a low viscosity superalloy slurry in the crack up to a suitable level and then depositing a superalloy putty layer on the superalloy powder or slurry at the top of the crack A braze putty layer is then deposited over the superalloy putty layer and the component is sintered in a vacuum furnace to harden the superalloy putty and powder or slurry to repair the defect.
A method for repairing a defect in a high temperature component, said defect including a crack having a wide top portion and a narrow bottom portion, said method comprising:
The method according to clam 1 wherein depositing a finely granulated superalloy powder or a superalloy slurry includes depositing a superalloy powder if the crack does not extend completely through the component and depositing a superalloy slurry if the crack does extend completely through the component
A method for repairing damage to a high temperature vane in a gas turbine engine, said damage including a cavity having a wide top portion and a narrow bottom portion, said method comprising:
A method for repairing a crack in a high temperature vane in a gas turbine engine, said method comprising:
Dependencies are inferred from the claim text.