Countering laser shock peening induced airfoil twist using shot peening

摘要

A gas turbine engine blade (8) is laser shock peened by laser shock peening a thin airfoil (34) of the blade (8), forming a laser shock induced twist in the airfoil, and shot peening a portion of the airfoil (34) to counter the laser shock induced twist in the airfoil (34). The shot peening may be performed before or after the laser shock peening. The shot peening may be applied over a laser shock peened surface (54) formed by the laser shock peening. The shot peening may be performed asymmetrically on asymmetrically shot peened pressure and suction side areas of pressure and suction sides (46 and 48), respectively, of the airfoil (34). A shot peened patch (28) near a blade tip (38) may be formed on one of pressure and suction sides (46 and 48) of the airfoil (34) wherein the airfoil (34) extends radially outwardly from a blade platform (36) to the blade tip (38) of the blade (8).