Patent ID: 6471484
Filing Date: 2002-10-29
Classification: F01D,Y10S

Abstract:
A method of fabricating a rotor assembly for a gas turbine engine to facilitate damping vibrations induced to the rotor assembly, the rotor assembly including a radially outer rim and a plurality of rotor blades that extend radially outward from the radially outer rim, each of the rotor blades including an airfoil including a pair of opposing sidewalls, said method comprising the steps of:forming a cavity in each rotor blade airfoil that extends radially inward from the airfoil first sidewall towards the airfoil second sidewall; embedding a first layer of damping material within the airfoil cavity adjacent the airfoil; and attaching a constraining layer to the airfoil with adhesive, such that the constraining layer is adjacent the first layer of damping material; and attaching a cover sheet to the airfoil with adhesive, such that the cover sheet extends around a periphery of the airfoil cavity in sealing contact with the airfoil.