Gas turbine blade and method of protecting same
AssigneePratt & Whitney Canada Corp.
InventorsEnzo Macchia, Barry Barnett, Andreas Eleftheriou, Tom McDonough, George Guglielmin, Joe Lanzino
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Abstract
An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.
Claims13
An airfoil blade of a gas turbine engine comprising a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root, the root defining a proximal end including a dovetail portion having pressure side and suction side surfaces, the root being composed of a first metal and having a nanocrystalline metal coating over at least a portion of the root, the nanocrystalline metal coating being composed of a second metal different from the first metal, the dovetail portion includes pressure side and suction side surfaces, said portion of the root having the nanocrystalline metal coating thereon being disposed on the dovetail portion, wherein the nanocrystalline metal coating is disposed exclusively on the pressure side surface of the dovetail portion.
Dependencies are inferred from the claim text.