Patent ID: 7189063

Claim:
A method for assembling a rotor assembly for gas turbine engine, said method comprising: providing a first rotor blade that includes an airfoil, a platform, a shank, and a dovetail, wherein the airfoil extends radially outward from the platform, the shank extends radially inward from the platform, and the dovetail extends from the shank; forming a recess within a portion of the shank; coupling the first rotor blade to a rotor shaft using the dovetail; coupling a second rotor blade to the rotor shaft such that a shank cavity is defined between the first and second rotor blade shanks, such that, during operation, cooling air may enter and pressurize the shank cavity through the recessed portion; and coupling the first rotor blade to the shaft such that during operation cooling air may be channeled from the shank cavity through a purge slot undercut within at least a portion of a platform radially inner surface.