Patent ID: 6049978
Filing Date: 2000-04-18
Classification: B23K,B23P,C23C,F01D,Y02T,Y10T

Abstract:
A method of repairing a turbine engine airfoil part, comprising the steps of: determining dimensional differences between pre-repaired dimensions of a turbine engine airfoil part and desired post-repair dimensions of the turbine engine airfoil part, the turbine engine airfoil part having a metal alloy substrate; determining a build-up thickness of coating material required to obtain the desired post-repair dimensions of the airfoil part; performing a high-density coating process to coat the turbine engine airfoil part substrate with a coating material to build-up a thickness of coating material effective to obtain desired finished dimensions after performing a sintering heat treatment process and a hot isostatic pressing treatment; performing the sintering heat treatment on the turbine engine airfoil part to densify the coating material; and then performing the hot isostatic pressing treatment to obtain a post-repair turbine engine airfoil part having the desired post-repair dimensions and having diffusion bonding between the coating material and the turbine engine airfoil substrate.