Patent ID: 6228510
Filing Date: 2001-05-08
Classification: C23C,Y02T,Y10T

Abstract:
A superalloy turbine component for use in a gas turbine engine, comprising:a superalloy base material substrate;a diffusion barrier layer comprised of an element selected from the group consisting of Ni, Co and combinations thereof overlying the superalloy base material substrate;a diffusion aluminide coating overlying the superalloy base material substrate, the diffusion aluminide coating formed by exposing the diffusion barrier layer overlying the superalloy base material substrate surface to an aluminum source at an elevated temperature, so that the diffusion aluminide coating is substantially grown by diffusion of aluminum into an outer surface of the diffusion barrier layer exposed to the aluminum source while outward migration of alloying elements from the superalloy base material substrate is substantially reduced by the diffusion barrier layer and the dimensional and chemical integrity of the superalloy base material substrate is substantially maintained.