Patent ID: 7993759

Claim:
A gas turbine engine blade comprising: a superalloy selected from the group consisting of nickel-base superalloys, iron-base superalloys, cobalt-base superalloys, and combinations thereof; an airfoil section having at least an exterior surface; a platform section having an exterior surface; an under platform section having an exterior surface; and a dovetail section having an exterior surface, the exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface; and a silicon-modified diffusion aluminide layer disposed on a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the silicon modified diffusion aluminide layer having a concentration of silicon in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum in the range of about 10 weight percent to about 20 weight percent.