Abstract:
This arrangement relates to a moving blade (), cast in one piece, for a turbomachine, in particular a turbine or compressor, comprising an aerodynamically shaped profile body () which has a shroud band (). The shroud band () projects beyond the profile body () in the circumferential direction () and has a fin (). The fin () possesses a base portion (), a transitional portion () and a sealing portion (). An axially measured wall thickness decreases in a transitional portion () from the base portion () to the sealing portion (). To avoid a porous structure in the base portion (), two depressions (), which reduce the wall thickness of the base portion (), are integrally molded on the outside of the base portion ().