Abstract: A compressor arrangement has a common shaft, an axial compressor having at least a single-stage, and a radial compressor having at least single-stage. Assemblies of the, or each, axial compressor stage on the rotor side and assemblies of the, or each, radial compressor stage on the rotor side are attached to a common shaft (4). A ratio between a maximum diameter of the shaft (4) in the region of the axial compressor (2) and a minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.5 and 3.0.

Abstract: A compressor arrangement has a common shaft, an axial compressor having at least a single-stage, and a radial compressor having at least single-stage. Assemblies of the, or each, axial compressor stage on the rotor side and assemblies of the, or each, radial compressor stage on the rotor side are attached to a common shaft (4). A ratio between a maximum diameter of the shaft (4) in the region of the axial compressor (2) and a minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.5 and 3.0.

Abstract: An inlet connection piece for an axial compressor, particularly for a turbocompressor, includes an inlet housing (1) in which is arranged a bearing housing (2) with a bearing (3), particularly a radial and/or axial bearing, for a rotor. The bearing housing (2) is connected to the inlet housing (1) by an inlet strut (4) which is connected to the inlet housing in a front cross section. The center of the bearing (3) is arranged axially in the flow direction of a fluid to be compressed behind the area center of the front cross section by at least 0.1-times, particularly at least 0.15-times, particularly at least 0.2-times, particularly at least 0.25-times, the chord length of the front cross section. In addition or alternatively, a fluid passage (5, 6) is formed in the inlet strut (4), and at least portions of this fluid passage (5, 6) form an acute angle with a normal plane relative to the longitudinal axis of the inlet connection piece.

Abstract: A cover disk (1) for a closed rotor of a radial flow machine or diagonal flow machine for defining a flow channel has a wall thickness which has a local maximum along the profile mean line of the meridional cross section of the cover disk between a first front side (2) and a second front side (3) of the cover disk. An outer surface (1.2) of the cover disk remote of the flow channel has in the area of this local maximum a convex curvature with a radius (R2.2) whose ratio (R2.2/D2) to an outer diameter (D2) of the rotor is within a range of 0.05 to 0.5 (0.05?R2.2/D2?0.5).

Abstract: A cover disk (1) for a closed rotor of a radial flow machine or diagonal flow machine for defining a flow channel has a wall thickness which has a local maximum along the profile mean line of the meridional cross section of the cover disk between a first front side (2) and a second front side (3) of the cover disk. An outer surface (1.2) of the cover disk remote of the flow channel has in the area of this local maximum a convex curvature with a radius (R2.2) whose ratio (R2.2/D2) to an outer diameter (D2) of the rotor is within a range of 0.05 to 0.5 (0.05<R2.2/D2<0.5).

Abstract: An inlet connection piece for an axial compressor, particularly for a turbocompressor, includes an inlet housing (1) in which is arranged a bearing housing (2) with a bearing (3), particularly a radial and/or axial bearing, for a rotor. The bearing housing (2) is connected to the inlet housing (1) by an inlet strut (4) which is connected to the inlet housing in a front cross section. The center of the bearing (3) is arranged axially in the flow direction of a fluid to be compressed behind the area center of the front cross section by at least 0.1-times, particularly at least 0.15-times, particularly at least 0.2-times, particularly at least 0.25-times, the chord length of the front cross section. In addition or alternatively, a fluid passage (5, 6) is formed in the inlet strut (4), and at least portions of this fluid passage (5, 6) form an acute angle with a normal plane relative to the longitudinal axis of the inlet connection piece.