Patent ID: 8882457
Filing Date: 2014-11-11
Classification: F04D

Abstract:
1. A multistage radial turbocompressor comprising: first, second, and third fans spaced along an axis, having respective axially directed vanes, and rotatable about the axis; an intermediate shaft part centered on and rotatable about the axis and forming with the first, second, and third fans a rotor rotatable about the axis, the intermediate shaft part being fixed rotationally between the second and third fans, the second fan being back-to-back with the third fan with the vanes of the second fan facing axially oppositely away from the vanes of the third fan and outputs of the second fan and the third fan being axially juxtaposed with no intake part between them; first, second, and third separate intake parts juxtaposed with the respective fans and forming respective first, second, and third intakes spaced along the axis; respective first, second, and third separate output parts axially juxtaposed and connected with the respective intake parts and forming respective first, second, and third spiral outputs spaced along the axis, the intake and output parts each being undivided and independent, the first output part being connected to the second intake part; a connector part connected between the second and third output parts, the intake and output parts and connector part together forming an axially extending housing surrounding the rotor; a first cooler connected between the first output part and the second intake part; a second cooler connected between the second output part and the third intake part; a plurality of radial bearings supporting the shaft in the housing; an axial bearing and one of the radial bearings on the intermediate shaft between the back-to-back second and third fans, between the intermediate shaft part and the connector part, and supporting the intermediate shaft part in the housing; and a drive connected to an end of the rotor to rotate the rotor about the axis.