Abstract: The invention relates to a magnetic bearing assembly of a rotor in a stator, with at least one magnetic bearing (1) comprising a stator part (2) and a rotor part (3) arranged coaxially thereto in the operating position without contacting the stator part. The bearing effective area of the rotor part is formed by a radial exciting system (6) having a permanent magnet (4), while the stator part (2) comprises a high-temperature superconductor concentrically surrounding the radial exciting system (6) while maintaining an annular air gap (10).

Abstract: A turbo-compressor having a housing and at least one rotor shaft pivotably supported in the housing, with a free shaft end and with a rotor connected with the other end of the rotor shaft. The free end of the rotor shaft facing away from the rotor projects into a pressure chamber connected with the housing, and is acted upon by a pressurized fluid whose force of pressure compensates for the force of the axial thrust acting on the rotor. Thus, the starting friction of the compressor is lower and drive motors of lower output target can be utilized.

Abstract: An expansion turbine for low-temperature applications containing a turbine stage into which a cold gas is admitted. A turbine rotor is mounted on a shaft. Also provided is a roller support for the shaft being lubricated with a minimum amount of oil or grease. The roller support contains a roller bearing located adjacent to the turbine stage. The roller bearing is comprised of an inner bearing ring, rollers, and an outer bearing ring supported on the side of the housing. An insulating bush made of ceramic engineering material is arranged between the inner bearing ring and the shaft. The bush thermally separates the inner bearing ring from the cold shaft.

Abstract: A method of operating a radial compressor wherein the output pressure and the throughput {dot over (m)} through a radial compressor are measured and the working point A in the operational characteristic diagram of the compressor is determined. For predetermined settings of the discharge flow control, the pump limits of the intake flow control characteristic fields are calculated in the operational characteristic diagram of the compressor. When the discharge flow control is so set that the working point falls in a working range associated with one of the pump limits and whose boundaries in the compressor operational characteristic diagram is spaced by a predetermined minimum spacing and a predetermined maximum spacing from the pump limit. When the working point A varies within this working range, only the intake flow control is adjusted. When the working point leaves the range, the discharge flow control is also adjusted.

Abstract: A method of operating a multistage turbocompressor or of monitoring the pump limit thereof, whereby the pump limit function is stored in the control unit in the form Y=m.F+b and the coefficients m and b are determined by the linear relationshipsm=m.sub.0 +m.sub.1.dT.sub.s +.SIGMA.m.sub.2i.dT.sub.rib=b.sub.0 +b.sub.1.dT.sub.s +.SIGMA.b.sub.2i.dT.sub.riwhere T.sub.s and T.sub.ri represent the intake temperature and the backcooling temperatures following coolers after each turbocompressor and dT.sub.s and T.sub.ri and reference temperatures T.sub.ref. The system automatically compensates for the shift of the pump limit with temperature and allows operation closer to the pump limit or boundary for stable aerodynamic operation.

Abstract: A turbine has a housing, an impeller centered on and rotatable about an axis in the housing, and an axle assembly in the housing having a large-diameter mounting part and a small-diameter bearing stem centered on the axis and extending into the impeller. A sun gear traversed by the bearing stem is fixed to the impeller and forms with the impeller a rotor having a center of mass spaced axially a predetermined distance from the large-diameter mounting part. A ring gear rotatable in the housing about the axis around the sun gear meshes with planet gears rotatable on the housing about respective planet axes radially equispaced from and angularly equispaced about the impeller axis. Each planet gear meshes inwardly with the sun gear. A bearing supports the rotor on the stem of the axle assembly at a bearing location spaced from the large-diameter mounting part by a distance equal to between 0.4 and 1.2 times the predetermined distance between the center of mass and the mounting part.

Abstract: A turbine has a housing, an impeller centered on and rotatable about an axis in the housing, and a small-diameter bearing stem centered on the axis, fixed on the housing, and extending from an attachment location on the housing toward the impeller. A pinion traversed by the bearing stem is fixed to the impeller and forms with the impeller a rotor having a center of mass spaced axially a predetermined distance from the attachment location. A gear rotatable on the housing adjacent the axis and meshing with the pinion is supported on the stem by an inner bearing engaged between the pinion and the stem. An outer bearing supports the rotor on the stem of the axle assembly at a bearing location spaced from the attachment location by a distance equal to between 0.4 and 1.2 times the predetermined distance between the center of mass and the attachment location.