Abstract: The invention relates to a turbocompressor (1) comprising a compressor housing (2) and a compressor wheel (4) with blades (5). The compressor wheel (4) is rotatably mounted relative to the compressor housing (2) and is arranged such that the exposed upper edges of the blades (5) are spaced from a compressor housing (2) wall (3) facing the blade upper edges across a head gap (7), wherein both the upper edges of the blades (5) as well as the housing wall (3) have at least one recess (11, 13) and at least one elevation (10, 14) over the respective Meridian contour, said recess and elevation interacting locally such that the head gap (7) defines a Z-shaped course in the region of the recesses (11, 13) and the elevations (10, 14) when viewed on a Meridian plane.

Abstract: A return geometry fluidically connects a first and a second compressor stage of the turbocompressor. The return geometry has multiple partial helices that are evenly or unevenly distributed in the circumferential direction. The multiple partial helices extend at least in part in the circumferential direction. They form flow channels that extend at least in some sections, separately from each other, to fluidically connect the first and second compressor stages.

Abstract: An axial fan for use with a wall ring plate includes a housing having an inlet region and a rotor. The rotor has an increased rotor diameter compared to a standardised rotor diameter. On the inlet side, the inlet region has a tapered section that narrows in an arched manner in a cross-sectional view from an inlet diameter to a wall ring diameter. The axial width and radial length of the tapered section are formed in a predetermined ratio.

Abstract: The invention relates to a turbocompressor (1) comprising a compressor housing (2) and a compressor wheel (4) with blades (5). The compressor wheel (4) is rotatably mounted relative to the compressor housing (2) and is arranged such that the exposed upper edges of the blades (5) are spaced from a compressor housing (2) wall (3) facing the blade upper edges across a head gap (7), wherein both the upper edges of the blades (5) as well as the housing wall (3) have at least one recess (11, 13) and at least one elevation (10, 14) over the respective Meridian contour, said recess and elevation interacting locally such that the head gap (7) defines a Z-shaped course in the region of the recesses (11, 13) and the elevations (10, 14) when viewed on a Meridian plane.

Abstract: A return geometry fluidically connects a first and a second compressor stage of the turbocompressor. The return geometry has multiple partial helices that are evenly or unevenly distributed in the circumferential direction. The multiple partial helices extend at least in part in the circumferential direction. They form flow channels that extend at least in some sections, separately from each other, to fluidically connect the first and second compressor stages.

Abstract: An axial fan for use with a wall ring plate includes a housing having an inlet region and a rotor. The rotor has an increased rotor diameter compared to a standardised rotor diameter. On the inlet side, the inlet region has a tapered section that narrows in an arched manner in a cross-sectional view from an inlet diameter to a wall ring diameter. The axial width and radial length of the tapered section are formed in a predetermined ratio.