METHOD TO RESTORE AN AIRFOIL LEADING EDGE

摘要

The present invention provides methods and apparatus to restore a blade leading edge (17) on a gas turbine engine component such as an airfoil (10) of a turbine blisk. The method utilizes welding image technology and power control systems in order to provide effective welding with superalloy materials such as Inconel 713 and Inconel 625. The method includes machining away a damaged leading edge (17) and providing a repaired region through successive depositions of superalloy powder filler through laser fusion welding. Deposition material is added until the repaired region exceeds the original dimensions of the airfoil (10). The airfoil is then machined and finished to return it to original airfoil dimensions.