Back to results
US 2019/0195080 A1Published application
Ceramic coating system and method
AssigneeUnited Technologies Corporation
InventorsJose R. Paulino, Christopher W. Strock
Life of this patent
Estimating the term…
Abstract
A gas turbine engine article includes a substrate that has at least one step, and the step includes an undercut. A thermally insulating topcoat is disposed on the substrate. The thermally insulating topcoat includes at least one fault that extends from the step.
Claims20
A gas turbine engine article comprising:
- a substrate including at least one step, the at least one step having an undercut;
- and
- a thermally insulating topcoat disposed on the substrate, the thermally insulating topcoat including at least one fault extending from the at least one step.
A gas turbine engine comprising:
- a plurality of rotatable blades;
- and
- a seal arranged radially outwards of the plurality of rotatable blades, the seal including,
- a substrate including at least one step, the at least one step having an undercut;
- and
- a thermally insulating topcoat disposed on the substrate, the thermally insulating topcoat including at least one fault extending from the at least one step.
3 more elements
A method for fabricating a gas turbine engine article, the method comprising:
- forming at least one step in a substrate, the at least one step having an undercut;
- and
- depositing a thermally insulating topcoat on the substrate, the thermally insulating topcoat forming at least one fault during the depositing that extends from the at least one step.
Dependencies are inferred from the claim text.