A method for laser shock peening a gas turbine engine blade includes laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and altering a root of the blade to counter the laser shock induced twist in the airfoil. The altering may be done after the laser shock peening. The altering may be done before the laser shock peening during casting or forging of the blade or during a machining or broaching procedure which cuts a shape of the root. One embodiment of the altering includes forming the root with an altered root centerline having an altered centerline angle with respect to a predetermined root centerline designed for a non-laser shock peened airfoil of the blade.