Abstract: A securing device (20) for axially securing a blade root (12) of a blade in a groove (11) of a turbine engine. The outer contour (24) of the securing device (20) that faces a groove wall, in particular a groove base (33), is curved at least in some regions, the outer contour (24) having three different radii (R1, R2, R3) in some regions.

Abstract: A blade for a turbomachine, in particular a jet engine, including a shroud, having two opposite lateral edges, for delimiting a main flow channel and including a blade which extends away from the shroud, a rounded transition area being provided which encompasses the blade on its root side and is guided beyond the one lateral edge, a section of the transition area protruding beyond the one lateral edge being severed and situated in the area of the other lateral edge as an elevation offset in the transverse direction, a blade arrangement having at least two of such blades as well as a turbomachine having a plurality of such blades.

Abstract: A damper (2) for damping a blade movement of a turbomachine (1), and to a method for producing the damper (2). The damper (2) has at least one side surface (21, 21?) which can be brought into frictional contact with a friction surface of the turbomachine (1) in order to damp a blade movement. The side surfaces (21, 21?) are asymmetrically convex in shape.

Abstract: A blade for a turbomachine, in particular a jet engine, including a shroud, having two opposite lateral edges, for delimiting a main flow channel and including a blade which extends away from the shroud, a rounded transition area being provided which encompasses the blade on its root side and is guided beyond the one lateral edge, a section of the transition area protruding beyond the one lateral edge being severed and situated in the area of the other lateral edge as an elevation offset in the transverse direction, a blade arrangement having at least two of such blades as well as a turbomachine having a plurality of such blades.

Abstract: A securing device (20) for axially securing a blade root (12) of a blade in a groove (11) of a turbine engine. The outer contour (24) of the securing device (20) that faces a groove wall, in particular a groove base (33), is curved at least in some regions, the outer contour (24) having three different radii (R1, R2, R3) in some regions.