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US 2026/0139600 A1Published application
Machinable coating for damping
AssigneeRtx Corporation
InventorsTimothy J. Harding, Robert A. White, III, John E. Holowczak
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Abstract
A gas turbine engine blade includes a platform, an airfoil section extending from the platform in a first direction, a mount extending from the platform in a second direction opposite the first direction, and a damper deposited on one of the platform, the airfoil section, and the mount. A method of sizing a damper for a gas turbine engine blade is also disclosed.
Claims20
A method of sizing a damper for a gas turbine engine blade, comprising:
- determining the mass of a blade;
- depositing a damper onto the blade;
- determining a mass of the damper after the depositing step;
- and
- machining the damper to remove mass.
2 more elements
Dependencies are inferred from the claim text.