Patent ID: 9017024
Filing Date: 2015-04-28
Classification: B23K,B23P,F01D,Y02T,Y10T

Abstract:
1. A method of restoring a gas turbine engine component, including the step of: (a) providing a turbine airfoil for repair along a chordwidth dimension to refurbish an eroded chordwidth dimension to a restored chordwidth dimension (b) inserting a barrier member into a slot in a trailing edge of the turbine airfoil to prevent a filler material from entering the slot, wherein a first portion of the barrier member extends past the eroded chordwidth dimension and into a portion of the slot defined by an original component, wherein a second portion of the barrier member protrudes beyond the trailing edge of the turbine airfoil; (c) depositing the filler material adjacent the barrier member to extend a slot length of the slot, wherein the filler material is the same material as the original component; and (d) laser cladding the trailing edge of the turbine airfoil along the chordwidth dimension with the filler material to form a cladded portion defining a restored portion of the trailing edge, wherein the cladded portion is disposed around the barrier member, wherein the second portion of the barrier member protrudes substantially in the chordwidth dimension beyond the cladded portion after the laser cladding.