Method of applying a nanocrystalline coating to a gas turbine engine component
AssigneePratt & Whitney Canada Corp.
InventorsBarry Barnett, Kin-Leung Cheung, Thomas McDonough, Andreas Eleftheriou, Enzo Macchia
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Abstract
A method of applying a nanocrystalline metal coating to a titanium or titanium alloy blade of a gas turbine engine is described. The method includes selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, P, B, Tl and combinations thereof, and applying the intermediate bond coat to at least a portion of the blade. A nanocrystalline metal coating having an average grain size of between 10 nm and 500 nm is then applied to the portion of the blade overtop of the intermediate bond coat.
Claims15
A method of applying a nanocrystalline metal coating to a blade of a gas turbine engine, the blade composed of a first metallic material and extending between a blade root and a blade tip, opposed sides of the blade defining a pressure side surface and a suction side surface, wherein the first metallic material is titanium or titanium alloy, the method comprising the steps of:
- selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, P, B, Tl and combinations thereof, and applying the intermediate bond coat to a portion of the blade disposed only on the pressure side surface;
- selecting the nanocrystalline metal coating to be a metal having an average grain size of between 10 nm and 500 nm;
- and then applying the nanocrystalline metal coating to said portion of the blade overtop of the intermediate bond coat.
Dependencies are inferred from the claim text.