Aerodynamically damping vibrations in a rotor stage of a turbomachine

摘要

A rotor stage for a gas turbine engine is provided which includes a rotor disk (34) and a plurality of rotor blades (36). The rotor disk includes a bore (38) centered on the axis of rotation and an outer radial surface. The rotor blades extend radially outward from, and are distributed around, the outer radial surface. At least one of the rotor blades is selectively skewed from an adjacent rotor blade. The skewed rotor blade(s) increases the aerodynamic damping of the rotor stage. <IMAGE>