A gas turbine engine component includes a static component, a seal body (68) associated with the static component, the seal body (68) having an end surface (70) configured to face a rotating seal seat (62), and a damper (102) positioned radially outward of the seal body (68). The damper (102) includes a contact (116) that engages the seal body (68) to dampen radial movement of the seal body (68) while accommodating axial movement of the seal body (68).