Abstract: A multistage turbocharging assembly is described. The multistage turbocharging assembly includes a first stage including a first turbine coupled with a first compressor via a first shaft. Further, the multistage turbocharging assembly includes a second stage including a second turbine coupled with a second compressor via a second shaft. The first compressor and the second turbine are arranged on a first side of the multistage turbocharging assembly and opposite to each other. The second compressor and the first turbine are arranged on a second side of the multistage turbocharging assembly and opposite to each other. Additionally, a method of operating a multistage turbocharging assembly is described.

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: Described herein is a shaft seal system of a shaft supported in a bearing housing of a turbomachine. The shaft seal system includes a rotor-side seal arranged between the bearing housing and the shaft. Additionally, the shaft seal system includes an axial bearing supporting the shaft. Further, a gap is provided between a rotor-side thrust bearing surface of the axial bearing and an opposite surface of the shaft. A gap width of the gap is adjustable as a function of rotation speed of the shaft.