Patent ID: 8221841

Claim:
A method for manufacturing a coated part comprising: burnishing a first surface of a metallic substrate to provide a first residual stress distribution; and applying a coating to at least a portion of said first surface, wherein the coated part is a gas turbine engine blade comprising: a platform; a root depending from the platform; an airfoil having: a leading edge and a trailing edge; and a pressure side and a suction side, wherein the blade comprises: said substrate; a compressive stress below a first region of the first surface, the first region extending over a majority of a streamwise perimeter of the airfoil at a location at a spanwise distance from the tip of more than 50% of a local tip-to-platform span; and said coating on at least a portion of the first region of the surface, the portion including said location, and wherein: the burnishing has an inboard boundary; and the coating is applied over a coating region having an inboard boundary outboard of the inboard boundary of the burnished continuous region.