Patent ID: 7311940

Claim:
A method for coating a section selected from the group consisting of the under platform section, the dovetail section, and combinations thereof of a gas turbine engine blade the method comprising the steps of: providing a gas turbine blade comprising a superalloy selected form the group consisting of nickel-base superalloys, cobalt-base superalloys, iron-base superalloys, and combinations thereof, the blade further comprising: 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; masking a preselected portion of the gas turbine blade leaving the exterior surface of a non-masked section selected from the group consisting of the under platform section, the dovetail section, and combinations thereof, unmasked, applying a layer of corrosion resistant coating composition, the composition comprising a glass-forming binder and corrosion resistant particulates to the exterior surface of the non-masked section, the particulates comprising: from about 5 weight percent to about 100 weight percent non-alumina corrosion resistant particulates having a CTE greater than that of the alumina particulates; and balance alumina particulates; curing the layer of corrosion resistant coating composition forming a corrosion resistant coating layer; and removing the maskant; wherein the corrosion resistant coating composition further comprises a liquid carrier component and wherein the liquid carrier component is removed from the corrosion resistant coating composition during the step of curing.