Hot corrosion-resistant coatings for gas turbine components
AssigneeBarson Composites Corporation
InventorsCharles Clifford BERGER, David John WORTMAN
Life of this patent
Estimating the term…
Abstract
A gas turbine component for use in a gas turbine engine includes a substrate a ceramic-based thermal barrier coating (TBC), and a diffusion chromide bond coat between the base material and the TBC. A thermally grown oxide (TGO) layer can be formed on the bond coat prior to application of the TBC. The TBC and the TGO include a common metal oxide. The oxide can be sacrificially in use and soluble in a molten sulfate salt, make the coating system particularly suitable for use in a marine environment.
Claims21
A gas turbine component for use in a gas turbine engine, comprising:
- a substrate comprising a metal base material;
- a ceramic-based thermal barrier coating disposed over the substrate, the thermal barrier coating defining at least a portion of an outer surface of the gas turbine component;
- and
- a bond coat disposed between the base material and the thermal barrier coating, the bond coat comprising a chromide diffusion coating.
A method of making a gas turbine component having a thermal barrier coating defining at least a portion of an outer surface of the gas turbine component, the method comprising the step of forming a diffusion bond coat on a component substrate, the diffusion bond coat comprising chromium interdiffused with a metal substrate material of the component substrate, wherein the thermal barrier coating is subsequently coated over the bond coat.
A gas turbine component for use in a gas turbine engine, comprising:
- a substrate comprising a metal base material;
- a metal bond coat formed on the base material;
- a thermally grown oxide layer formed on the bond coat and comprising an oxide of a metal element of the bond coat;
- and
- a ceramic-based thermal barrier coating disposed over the substrate and defining at least a portion of an outer surface of the gas turbine component, wherein the thermal barrier coating further comprises the oxide of the metal element of the bond coat.
A method of making a gas turbine component comprising the step of coating a turbine component substrate with a coating system comprising a ceramic-based thermal barrier coating comprising a sacrificial oxide that is soluble in a molten sulfate salt.
Dependencies are inferred from the claim text.