Imparting deep compressive residual stresses into a gas turbine engine airfoil peripheral repair weldment

摘要

A gas turbine engine airfoil is repaired by machining away airfoil material along at least a portion of at least one of leading and trailing edges and a radially outer tip forming at least one cut back area and forming a weldment by welding successive beads of welding material into the cut back area. Desired finished dimensions of the repaired airfoil are obtained by machining away some of the weld bead material in the weldment and then deep compressive residual stresses are imparted in a pre-stressed region extending into and encompassing the weldment and a portion of the airfoil adjacent the weldment. The compressive residual stresses may be are imparted after either rough machining or final finishing thereafter of the weldment. The cut-back area may extend up to about 90% of the airfoil's span and have a maximum cut-back depth up to about.22 inches.