Abstract: A method of restoring a gas turbine engine component includes removing a defect section of a turbine engine component according to a template. The template has a standardized shape and is used in a standardized location on the turbine engine component. The template is produced based upon common defect sections from other turbine engine components. A laser cladding is used to build a replacement section in place of the defect section. Thus, the turbine engine component is restored to near its original shape.

Abstract: A method of restoring a gas turbine engine component includes repairing a turbine airfoil along a chordwidth dimension to rebuild a trailing edge of the turbine airfoil to near original dimensions. An eroded portion of the trailing edge of the turbine airfoil is removed and a filler material is deposited onto the trailing edge to produce a laser cladding. During the laser cladding process, a barrier member is inserted into a slot that extends through the trailing edge to prevent filler material from entering the slot and to act as a heat sink to remove heat from the trailing edge during the laser cladding process.