TURBOMACHINE

The invention relates to a turbomachine, in particular a turbo-compressor (TCO), comprising a rotor (R) which is at least partly arranged in a housing (CAS) and extends along a rotational axis (X). The turbomachine has at least one radial bearing (RB) in which the rotor (R) is radially mounted on a radial bearing point (RBP), said radial bearing (RB) being designed as an oil-lubricated sliding bearing. In the axial region of the radial bearing point (RBP), the rotor (R) has a hollow chamber (CAV) which is annularly located in the circumferential direction (CDR) in the region of the outer 20% of the diameter of the radial bearing point (RBP) of the rotor (R) and which is thermally insulating between a radially inner core region (COR) of the rotor (R) in the region of the radial bearing point (RBP) and the radial outer region of the rotor (R) in the region of the radial bearing point (RBP). In order to ensure that the turbomachine runs as smoothly as possible, a first shaft end (RN1) ofthe rotor (R) protrudes f