Abstract: A gas turbine engine including a rotor and a cooling fluid delivery system is presented. The rotor includes a disc and a plurality of blades extending radially therefrom. Each blade has a suction side and a pressure side and includes a shank, a platform and a main portion, the main portion being radially outward of the shank and separated therefrom by the platform. At least one cavity is defined, each radially inward of the platforms and between a suction side of the shank of one blade and a pressure side of the shank of an adjacent blade. The rotor includes at least one damper, the damper including a main body in contact with at least one blade and a deflector nose. The deflector nose extends from the main body into the cavity.

Abstract: A gas turbine engine including a rotor and a cooling fluid delivery system is presented. The rotor includes a disc and a plurality of blades extending radially therefrom. Each blade has a suction side and a pressure side and includes a shank, a platform and a main portion, the main portion being radially outward of the shank and separated therefrom by the platform. At least one cavity is defined, each radially inward of the platforms and between a suction side of the shank of one blade and a pressure side of the shank of an adjacent blade. The rotor includes at least one damper, the damper including a main body in contact with at least one blade and a deflector nose. The deflector nose extends from the main body into the cavity.