Patent ID: 6751863
Filing Date: 2004-06-22
Classification: C23C,F01D,F05D,Y10T

Abstract:
A method for providing a rotating structure of a gas turbine engine comprising the steps of:furnishing a rotor disk comprising a hub with a plurality of hub slots in a periphery of the hub, each hub slot having a hub slot surface; furnishing a plurality of rotor blades, wherein each rotor blade comprises an airfoil, and a root at one end of the airfoil, the root being shaped and sized to be received in one of the hub slots of the rotor disk; depositing a protective coating at a location which will be, upon assembly, disposed between the root of each rotor blade and the respective hub slot surface by a wire arc spray process, the protective coating being a protective alloy comprising, in weight percent, from about 6.0 to about 8.5 percent aluminum, from 0 to about 0.5 percent manganese, from 0 to about 0.2 percent zinc, from 0 to about 0.1 percent silicon, from 0 to about 0.1 percent iron, from 0 to about 0.02 percent lead, remainder copper and impurities; and assembling the roots of the rotor blades into the respective hub slots of the rotor disk to form the rotating structure.