Rotor damper with contact biasing feature for turbine engines

A rotor assembly for a gas turbine engine comprising:

• a rotor extending circumferentially about a central axis, wherein the rotor includes a ring that extends around the central axis and a mount that extends axially away from the ring, the ring including an axially facing engagement surface,
• a blade extending radially outward from the ring of the rotor, and
• a damper coupled with the mount of the rotor with a fastener and engaged with the engagement surface to minimize vibrations of the rotor assembly, the damper including an inner band fixed with the mount, a damper body that extends radially outward and axially into engagement with the engagement surface of the rotor, and a projection that extends axially from the damper body away from the engagement surface such that the projection is located axially between the engagement surface and the inner band to urge the damper body into the engagement surface as a result of centripetal forces in response to rotation of the rotor assembly about the central axis,
• wherein the damper body further includes an outer band and an intermediate band, the outer band extends substantially radially and is engaged with the engagement surface, and the intermediate band extends radially and axially to interconnect the inner band and the outer band,
• wherein the damper further includes a locator lip that extends axially away from the inner band and is engaged with a radially outward facing contact surface of the mount such that the locator lip is located radially outward of the contact surface, and
• wherein the intermediate band is spaced apart from the rotor such that the damper body is not engaged with the rotor radially between the outer band and the locator lip such that the projection urges a radial outer end of the damper axially toward the ring causing the intermediate band to act as a lever arm due to a weight of the projection being acted on by centripetal forces during use of the rotor assembly.