Patent ID: 7156621

Claim:
A gas turbine engine rotor assembly comprising a rotor disk having a plurality of blade mounting slots circumferentially distributed about a periphery of the rotor disk for receiving complementary blade fixing portions of swept blades, each of said blade mounting slots being bounded by a pair of opposed sidewalls extending longitudinally from a front side to a rear side of the rotor disk, a portion of the weight of said swept blades being cantilevered over front portions of said blade fixings, each swept blade having an airfoil portion with a center of gravity which is offset axially forwardly relative to the center of the blade fixing portion, and wherein a localized lateral play is provided between the sidewalls of each slot and the blade fixing portion of a respective one of the swept blades along a longitudinal front portion where contact stress is maximal, said longitudinal front portion being smaller than a length of the blade mounting slot and the blade fixing portion.