Abstract: The invention relates to a guide vane for a gas turbine, comprising an airfoil, a platform arranged at a radial end of the airfoil, an upstream flange extending radially from the platform, and a downstream flange extending radially from the platform, wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element. A surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove. The invention further relates to a guide vane cluster, a housing for a gas turbine, as well as to a gas turbine.

Abstract: A damper ring (1) for reducing unwanted vibrations of a blisk (2), which damper ring (1) is disposable at the radially inner side of a blade ring (3) of the blisk (2). The damper ring (1) features at least one damper element (4) configured to dissipate vibrational energy of the blisk (2) and/or to transfer vibrational modes of the blisk into vibrational modes different from the vibrational modes of the blisk. The invention also relates to a blisk (2) and to a turbomachine (13).