Abstract: The invention relates to a radial turbine. The radial turbine comprises: —a turbine housing having a radial gas inflow channel; —a nozzle ring, which is disposed in the radial gas inflow channel; and —an annular cleaning device for cleaning the nozzle ring. The annular cleaning device is connected to a cleaning-agent feed by means of an axially insertion-connectable supply line such that, after or during the demounting of the nozzle ring, the annular cleaning device can be removed from the turbine housing in the axial direction. The invention also relates to a method for mounting a cleaning device for cleaning a nozzle ring of a radial turbine and to a method for demounting the cleaning device.

Abstract: The invention relates to an exhaust-gas turbocharger, which is operated by the exhaust gas of a combustion engine and is equipped with a rotor unit that rotates at high-speed. Said rotor unit comprises a turbocharger shaft, a turbine wheel that is rotationally fixed to the shaft, in addition to a compressor wheel that is rotationally fixed to the shaft. To increase the operational reliability of said turbocharger, a torsional-vibration damper is located on the turbocharger shaft. The torsional-vibration damper reduces torsional-vibration stresses that arise in the shaft, which are caused by motor pulsations of a higher order of the combustion engine.

Abstract: The object of the invention is to provide an improved method for sealing off the separating gap, formed between a rotor and a stator, in a non-contacting manner, with which method the service life of the components involved can be increased. In addition, an arrangement for carrying out the method is to be shown. According to the invention, this is achieved in that the flow layers (35, 36), having different circumferential velocities, of the working fluid (18) are divided after the choking action into a first partial flow (35') having a high circumferential velocity and a second partial flow (36') having a low circumferential velocity, the first partial flow (35') is merely deflected, only the second partial flow (36') is swirled and is finally directed parallel to the deflected first partial flow (35') into the latter. To this end, the opposing surface (24) of the choke point (22) is designed as a flow divider for the working fluid (18).

Abstract: The object of the invention is to provide a simple and cost-effective solution for reducing the wear and consequently for increasing the life of axial sliding bearings. For this purpose, the profiled annular surface (24, 24') of the lubricating gap (25, 25') arranged between the fixed bearing body (20) and the rotating bearing collar (19) is designed to rotate about or with the shaft (14). Said annular surface has a plurality of radially arranged lubricating oil grooves (26, 26') and, in each case, a wedge surface (27, 27') connected to these in the circumferential direction. A catch surface (28, 28') is designed between each wedge surface (27, 27') and the lubricating oil groove (26, 26') adjacent to the latter. The lubricating oil grooves (26, 26') and the wedge surfaces (27, 27') are delimited radially outward by a sealing web (29, 29').

Abstract: A method and device for the autolubrication of the rolling bearings of turbomachines. The method and device utilize pressure differences present in the turbomachine for sucking in the lubricating oil. Moreover, a pressure is built up in centrifuges arranged on a shaft, and is used for the direct injection of the lubricating oil into the rolling bearings. For this purpose, an annular element imparting a negative pressure is arranged stationarily on the shaft, and is designed as a negative pressure chamber. The negative pressure chamber is connected via an oil suction conduit to an oil sump holding the lubricating oil and via a first air conduit to a negative pressure region of the turbomachine. The oil sump is connected via a second air conduit to an overpressure region of the turbomachine. A separating point is arranged between the oil suction conduit and the negative pressure region, preferably in the first air conduit.