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US 2010/0304037 A1Published application
Thermal Barrier Coatings and Application Methods
AssigneeUnited Technologies Corporation
InventorsBenjamin J. Zimmerman, David A. Litton, John F. Blondin
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Abstract
A gas turbine engine component has a metallic substrate. A coating is on the substrate. A barrier coat is applied while varying a speed of the component rotation so as to provide a corresponding microstructure to the barrier coat.
Claims16
A method for coating a gas turbine engine component, the method comprising:
- applying a barrier coat,
- wherein the applying of the barrier coat comprises:
- rotating the substrate as the barrier coat is applied;
- and
- varying a speed of the rotation.
2 more elements
A method for coating a gas turbine engine component, the method comprising:
- applying a bond coat to a substrate of the component;
- and
- applying a barrier coat atop the bond coat,
- wherein the applying of the barrier coat comprises:
- steps for obtaining a structure of the barrier coat characterized by a columnar microstructure having modulated density and directionality.
2 more elements
An apparatus comprising:
- a fixture for holding a component:
- a motor coupled to the fixture for rotating the fixture about a fixture axis;
- an electron beam physical vapor deposition source of a ceramic positioned to provide a vapor to the component on the fixture;
- and
- a controller coupled to the motor to control the rotation and configured to vary a speed of the rotation so that a buildup of the ceramic at a given location on the component is formed by passes at varied speed.
2 more elements
Dependencies are inferred from the claim text.