Abstract: A return stage through which a process fluid is designed to flow along a throughflow direction of a radial turbomachine, wherein the return stage extends in annular fashion about an axis and is defined radially inwardly by an inner delimiting contour and radially outwardly by an outer delimiting contour. At least one guide vane stage including guide vanes extends at least along a part of the third section and segments the return stage in the circumferential direction into flow channels, wherein in each case a profile midline of a profile cross section defines an inner track on the side of the inner delimiting contour and an outer track on the side of the outer delimiting contour. A radial turbomachine includes at least one such return stage.

Abstract: A rotor of a multi-staged axial compressor which extends along an axis of rotation. The rotor has a shaft which has rotor blade slots. Rotor blades of the rotor are arranged next to one another in the circumferential direction and are each secured to the rotor blade slots by a blade root to form a respective rotor blade stage. At least two rotor blade stages are provided in axial succession and an interspace slot, extending in the circumferential direction, is provided in the shaft axially between the two rotor blade stages. The rotor blade slots open into the interspace slots and blade roots of the rotor blades are insertable radially into the interspace slots and can be pushed into the rotor blade slots. The rotor has an interspace cover which covers the interspace slots, wherein the interspace cover is designed segmented into interspace cover segments in the circumferential direction.

Abstract: A centrifugal compressor having a stator which is designed as an inlet stator, in particular for a compressor, with at least one vane having a vane airfoil around which a fluid can flow, with a plurality of vanes arranged in the form of a ring, with an adjustment device for adjusting the vane, wherein a curvature of a profile center line of the vane airfoil has at least one inflection point.

Abstract: A return stage through which a process fluid is designed to flow along a throughflow direction of a radial turbomachine, wherein the return stage extends in annular fashion about an axis and is defined radially inwardly by an inner delimiting contour and radially outwardly by an outer delimiting contour. At least one guide vane stage including guide vanes extends at least along a part of the third section and segments the return stage in the circumferential direction into flow channels, wherein in each case a profile midline of a profile cross section defines an inner track on the side of the inner delimiting contour and an outer track on the side of the outer delimiting contour. A radial turbomachine includes at least one such return stage.

Abstract: A backfeed stage of a radial turbo fluid energy machine for deflecting a flow direction of a process fluid issuing from a rotor, rotating around an axis, from radially outward to radially inward, having a backfeed duct which has three adjacent sections in the flow direction, wherein a first section is designed for conducting the process fluid radially outward, wherein a second section is designed for deflecting the process fluid from the radially outward to radially inward direction, wherein a third section is designed for conducting the process fluid radially inward, wherein the second section and third section, or only the third section, have/has first guide vanes which define flow passages of the backfeed duct in relation to each other in the circumferential direction.

Abstract: A backfeed stage of a radial turbo fluid energy machine for deflecting a flow direction of a process fluid issuing from a rotor, rotating around an axis, from the radially outward to the radially inward, having a backfeed duct which has three adjacent sections in the flow direction, wherein a first section is designed for conducting the process fluid radially outward, wherein a second section is designed for deflecting the process fluid from radially outward to radially inward direction, wherein a third section is designed for conducting the process fluid radially inward, wherein the second section and third section, or only the third section, have/has first guide vanes which define flow passages of the backfeed duct in relation to each other in the circumferential direction.

Abstract: A centrifugal compressor having a stator which is designed as an inlet stator, in particular for a compressor, with at least one vane having a vane airfoil around which a fluid can flow, with a plurality of vanes arranged in the form of a ring, with an adjustment device for adjusting the vane, wherein a curvature of a profile center line of the vane airfoil has at least one inflection point.

Abstract: A rotor of a multi-staged axial compressor which extends along an axis of rotation. The rotor has a shaft which has rotor blade slots. Rotor blades of the rotor are arranged next to one another in the circumferential direction and are each secured to the rotor blade slots by a blade root to form a respective rotor blade stage. At least two rotor blade stages are provided in axial succession and an interspace slot, extending in the circumferential direction, is provided in the shaft axially between the two rotor blade stages. The rotor blade slots open into the interspace slots and blade roots of the rotor blades are insertable radially into the interspace slots and can be pushed into the rotor blade slots. The rotor has an interspace cover which covers the interspace slots, wherein the interspace cover is designed segmented into interspace cover segments in the circumferential direction.