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US 8,708,658 B2Granted
Local application of a protective coating on a shrouded gas turbine engine component
AssigneeUnited Technologies Corporation
InventorTimothy A. Milleville
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component includes a blade section having an inner end and an outer end, a shroud section at the outer end, and a platform at the inner end. A protective coating is disposed on the shroud, where the blade section is substantially free of the protective coating. The protective coating may also be disposed on the platform.
Claims2
A gas turbine engine component comprising:
- a blade section having an inner end and an outer end;
- a shroud section at the outer end;
- a platform section at the inner end;
- and
- a protective coating disposed on the shroud section, wherein the blade section is substantially free of the protective coating, wherein the protective coating partially covers a fillet between the shroud section and the blade section, wherein the protective coating diminishes across the fillet.
2 more elements
A gas turbine engine component comprising:
- a blade section having an inner end and an outer end;
- a shroud section at the outer end;
- a platform section at the inner end;
- and
- a protective coating disposed on the shroud section, wherein the blade section is substantially free of the protective coating, wherein the protective coating partially covers a fillet between the topside of the platform section and the blade section, wherein the protective coating diminishes across the fillet.
2 more elements
Dependencies are inferred from the claim text.