Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending longitudinally between a root and a tip, and laterally between a leading edge and a trailing edge. The airfoil further includes a plurality of fine striations spaced laterally apart between the leading and trailing edges in the airfoil first side, and extending longitudinally between the root and the tip. A viscoelastic filler is bonded in the striations for damping torsional vibrations of the airfoil.

Abstract: The present invention provides a phase independent damper and damper assembly capable of damping rotor blade vibrations in the axial, circumferential, and radial directions. One embodiment, particularly useful in an aircraft gas turbine engine compressor rotor, provides a damper and damper assembly including a generally axially extending blade damper operable to fictionally engage a generally axially extending circumferentially facing surface of a disk and axially extending angled surface under the platform of the blade. The invention provides an additional advantage of allowing simple and easy modification of existing engines to incorporate the damper of the present invention.