Abstract: A turbomachine rotor having a radially inner hub element, a radially outer cover element, and rotor blades which extend between the hub element and the cover element and have rotor blade airfoils. The rotor blades are an integral component of the hub element and are bonded to the cover element according to a first alternative or are an integral component of the cover element and are bonded to the hub element according to a second alternative. The rotor blades have an integral socket adjacently to the cover element according to the first alternative or adjacently to the hub element according to the second alternative, and the rotor blades are bonded to the cover element according to the first alternative or to the hub element according to the second alternative via the socket.

Abstract: A turbomachine rotor having a radially inner hub element, a radially outer cover element, and rotor blades which extend between the hub element and the cover element and have rotor blade airfoils. The rotor blades are an integral component of the hub element and are bonded to the cover element according to a first alternative or are an integral component of the cover element and are bonded to the hub element according to a second alternative. The rotor blades have an integral socket adjacently to the cover element according to the first alternative or adjacently to the hub element according to the second alternative, and the rotor blades are bonded to the cover element according to the first alternative or to the hub element according to the second alternative via the socket.

Abstract: A radial compressor stage includes an impeller with multiple impeller blades on the rotor side and a diffuser with multiple guide blades on the stator side positioned downstream of the impeller. Between the impeller and the stator an impeller side gap is formed. Flow inlet edges of the guide blades on the stator side lie on a first circle contour such that the flow inlet edges of all guide blades on the stator side have an identical spacing to the flow inlet edges of the respective adjacent guide blades. Flow outlet edges of the guide blades on the stator side lie on a second circle contour such that in at least one first circumferential position the flow outlet edge of the respective guide blade on the stator side has a spacing to the flow outlet edge of at least one adjacent guide blade other than in second circumferential positions.

Abstract: A radial compressor stage includes: an impeller, rotatable relative to a stator, the impeller having multiple impeller blades on a rotor side; a diffuser positioned in a flow direction downstream of the impeller, the diffuser having multiple guide blades on the stator side; an impeller side gap formed between the impeller and the stator; and an intermediate flow channel extending between the impeller and the diffuser. A gap is formed between an outer edge of a downstream back side of the impeller and an opposite inner edge of the stator, the gap being sealed via a seal such that the seal seals the impeller side gap from the intermediate flow channel.