Method of applying a nanocrystalline coating to a gas turbine engine component
OwnerBarry Barnett, Kin-Leung Cheung +3inventors
InventorsBarry Barnett, Kin-Leung Cheung, Thomas McDonough, Andreas Eleftheriou, Enzo Macchia
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Abstract
A method of applying a nanocrystalline coating to a gas turbine engine component is described. The method comprises the steps of applying an intermediate bond coat to at least a portion of the component, and then applying the nanocrystalline coating to at least the portion of the component overtop of the intermediate bond coat. The component may include, for example, a blade of which a dovetail portion of the blade root is protected by applying the intermediate bond coat and the nanocrystalline coating thereto.
Claims8
A method of protecting a blade of a gas turbine engine, the blade having a blade root and an airfoil extending therefrom, the method comprising the steps of:
- applying an intermediate bond coat to at least a dovetail portion of the blade root;
- selecting a nanocrystalline metal coating to be a metal having an average grain size of between 10 nm and 500 nm;
- and then applying a the nanocrystalline metal coating to at least said dovetail portion of the blade root, overtop of the intermediate bond coat, wherein the blade is a titanium or titanium alloy, and the intermediate bond coat is selected from the group consisting of Ni, nickel alloy, P, B, Tl and combinations thereof.
Dependencies are inferred from the claim text.