System and Method for Rejuvenating Coated Components of Gas Turbine Engines
AssigneeGeneral Electric Company
InventorsBhupendra Kumar Gupta, Mark Rosenzweig
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Abstract
The present disclosure is directed to a method for rejuvenating a damaged coated component of a gas turbine engine. The method includes uninstalling the damaged coated component from the gas turbine engine. The method also includes isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component. In addition, the method includes simultaneously depositing a first coating material on the first coated portion of the component and a different, second coating material on the second coated portion of the component. The method also includes reinstalling the rejuvenated coated component into the gas turbine engine.
Claims20
A method for rejuvenating a damaged coated component of a gas turbine engine, the method comprising:
- uninstalling the damaged coated component from the gas turbine engine;
- isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component;
- simultaneously depositing a first coating material on the first coated portion of the component and a different, second coating material on the second coated portion of the component;
- and,
- reinstalling the rejuvenated coated component into the gas turbine engine.
A kit for rejuvenating a damaged coated component of a gas turbine engine, the kit comprising:
- a first coating material;
- a second coating material, the first and second coating materials being different;
- a maskant for isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component;
- and
- a coating system configured to simultaneously deposit the first and second coating materials on the first and second coated portions of the component, respectively.
A method for rejuvenating a damaged coated turbine blade of a gas turbine engine, the method comprising:
- uninstalling the damaged coated turbine blade from the gas turbine engine;
- placing a coated shank of the turbine blade in a masking chamber having a masking lid so as to isolate the shank from a coated airfoil of the turbine blade;
- filling a masking chamber with a chromium-based powder coating;
- and
- simultaneously depositing an aluminum-based coating on the airfoil via diffusion coating.
Dependencies are inferred from the claim text.