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US 2019/0316479 A1Published application
Air seal having gaspath portion with geometrically segmented coating
AssigneeUnited Technologies Corporation
InventorDmitriy A. Romanov
Life of this patent
Estimating the term…
Abstract
A blade outer air seal for a gas turbine engine includes a seal arc-segment that defines a gaspath side, a non-gaspath side, leading and trailing ends, and first and second circumferential sides. A portion of the gaspath side has a geometrically segmented coating section. The geometrically segmented coating section includes a wall that has an array of cells, and a coating disposed in the array of cells.
Claims20
A blade outer air seal for a gas turbine engine, comprising:
- a seal arc-segment defining a gaspath side, a non-gaspath side, leading and trailing ends, and first and second circumferential sides, a portion of the gaspath side having a geometrically segmented coating section, the geometrically segmented coating section including
- a wall including an array of cells, and
- a coating disposed in the array of cells.
A gas turbine engine comprising:
- a compressor section;
- a combustor in fluid communication with the compressor section;
- and
- a turbine section in fluid communication with the combustor, the turbine section having a blade outer air seal including a seal arc-segment defining a gaspath side, a non-gaspath side, leading and trailing ends, and first and second circumferential sides, a portion of the gaspath side having a geometrically segmented coating section, the geometrically segmented coating section including
- a wall including an array of cells, and
- a coating disposed in the array of cells.
3 more elements
Dependencies are inferred from the claim text.