Patent ID: 7311940
Filing Date: 2007-12-25
Classification: C23C,F01D,F05D,Y02T

Abstract:
1. 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: 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: 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.