Article having corrosion resistant coating
AssigneeUnited Technologies Corporation
InventorsDilip M. Shah, Alan David Cetel
Life of this patent
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Abstract
According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant ceramic overlay coating such as a stabilized zirconia is located on the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blades in these regions.
Claims17
A turbine blade for a gas turbine engine comprising a superalloy substrate defining an airfoil, a root and a platform located between the blade and root, the platform has an underside adjacent the root, and a corrosion inhibiting, ceramic overlay coating on the underside of the platform.
In a superalloy gas turbine component which operates in an environment with gas temperatures in excess of 1,000° C., the component having a first, exposed portion which is directly exposed to hot gasses, a second, shielded section which is shielded form direct exposure to the gasses, and a third section between the airfoil and root and having an underside surface adjacent the root, the improvement which comprises a corrosion inhibiting ceramic coating applied to the third section.
Dependencies are inferred from the claim text.