Laser shock peened dovetails for disks and blades

A dovetail assembly component of a gas turbine engine for mounting blades around a rotor disk periphery, said dovetail assembly component comprising:

• a metallic body having at least a portion of said body subject to a stress field due to forces generated by the engine's operation,
• at least one stress riser located in said portion that causes stress concentration in said stress field when the rotor is rotating,
• at least one region of the component around said stress riser having deep compressive residual stresses imparted by laser shock peening,
• said stress riser is a transition portion of the component between an area of minimum width, in cross section, and a pressure face of the component wherein said pressure face is a contact surface between a complementary dovetail blade slot and dovetail blade root formed between adjacent disk posts circumferentially disposed around a centerline axis of the disk,
• wherein said region extends inward from a laser shocked surface of the component along said transition portion of the component,
• wherein the component comprises a blade, said pressure face lies on an exterior facing surface of a dovetail blade root of said blade, and said region and said laser shocked surfaces are radially outward of said face on a shank of said blade which generally connects said root to an airfoil of said blade, and
• wherein said transition portion is a transition fillet at a root-to-shank interface between said shank and said root.