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A rotor blade for a rotor of a gas turbine engine having an axis of rotation including a root portion, a platform portion connected to the root portion and having a damper pocket formed therein, an airfoil portion connected to the platform portion, a generally bar-shaped damping member loosely arran

A rotor blade for a rotor of a gas turbine engine having an axis of rotation including a root portion, a platform portion connected to the root portion and having a damper pocket formed therein, an airfoil portion connected to the platform portion, a generally bar-shaped damping member loosely arranged in the damper pocket having at least one scrubbing surface, and at least one leg extending from the bar-shaped damping member for retaining the bar-shaped damping member in the damper pocket. The bar-shaped damping member is slidably displaceable and rotatable within the damper pocket during rotation of the rotor. The damper pocket in the platform portion has a rear surface with an upper portion and a lower portion at an angle to the upper portion, a pair of spaced side surfaces, and a pair of spaced lower surfaces extending from the rear surface lower portion which are substantially coplanar. The damper pocket lower surfaces are provided by a first blade tab extending laterally inward from one of the side surfaces and a second blade tab extending laterally inward from the other side surface, where a leg connected to the bar-shaped damping member extends through a slot in at least one of the first and second blade tabs so as to retain the bar-shaped damping member within the damper pocket.

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[ What is claimed is:] [12.] A rotor assembly for a gas turbine engine, comprising:(a) a rotor disk including means for receiving a root portion of a rotor blade arranged on the outer circumference of said rotor disk;(b) at let one rotor blade, comprising:(1) a root portion received by said receivin

[ What is claimed is:] [12.] A rotor assembly for a gas turbine engine, comprising:(a) a rotor disk including means for receiving a root portion of a rotor blade arranged on the outer circumference of said rotor disk;(b) at let one rotor blade, comprising:(1) a root portion received by said receiving means of said rotor disk;(2) a platform portion connected to said root portion and having a damper pocket formed therein, said damper pocket having a substantially triangular cross-section and including:(a) a rear surface having an upper portion and a lower portion at an angle to said upper portion;(b) a pair of spaced side surfaces; and(c) a pair of spaced, substantially coplanar lower surfaces extending from said rear surface lower portion, said damper pocket lower surfaces being provided by a first blade tab extending laterally inward from one of said side surfaces and a second blade tab extending laterally inward from the other of said side surfaces;(3) an airfoil portion connected to said platform portion;(4) a generally bar-shaped damping member loosely arranged in said damper pocket having at least one scrubbing surface, said bar-shaped damp in member further comprising first and second legs extending from opposite ends of said bar-shaped damping member through said first and second blade tabs, respectively, so as to retain said bar-shaped damping member within said damper pocket.