Turbomachine
A turbomachine having a rotor that extends along a rotational axis and a radial bearing in which the rotor is radially mounted on a radial bearing point. In the axial region of the radial bearing point, the rotor has a hollow chamber annularly located in the circumferential direction in the region of the outer 20% of the diameter of the radial bearing point and which is thermally insulating between a radially inner core region of the rotor in the region of the radial bearing point and the radial outer region of the rotor in the region of the radial bearing point. A first shaft end of the rotor protrudes from the axial center of the radial bearing point by a projection over the radial bearing point, wherein a first quotient QLO of the projection OVH divided by the total length TLE of the rotor QLO=OVH/TLE>0.15.
1. A turbomachine, comprising:
a rotor which is at least partly arranged in a casing and extends along a rotational axis,
at least one radial bearing in which the rotor is radially mounted at a radial bearing point,
wherein the at least one radial bearing is designed as an oil-lubricated slide bearing,
wherein in an axial region of the radial bearing point, the rotor has a cavity which is annularly located in a circumferential direction in a region of an outer 20% of a diameter of the radial bearing point of the rotor and which provides thermal insulation between a radially inner core region of the rotor in the region of the radial bearing point and a radially outer region of the rotor in the region of the radial bearing point,
wherein a first shaft end of the rotor protrudes from an axial center of the radial bearing point by an overhang OVH over the radial bearing point, wherein a first quotient QLO of the overhang OVH to a total length TLE of the rotor is QLO=OVH/TLE>0.15, and
wherein a radial height of the cavity is less than 10% of the rotor diameter at the radial bearing position.
2. The turbomachine as claimed in claim 1 ,
wherein an axial extent of the overhang OVH of the rotor has an overhang mass OVM, and the complete rotor has a total mass TMS,
wherein a second quotient QOT of the overhang mass OVM to the total mass TMS is QOT=OVM/TMS>0.06.
3. The turbomachine as claimed in claim 1 ,
wherein the radial bearing is configured such that a static bearing pressure >6 bar.
4. The turbomachine as claimed in claim 1 ,
wherein the rotor has an eccentricity <0.1.
5. The turbomachine as claimed in claim 1 ,
wherein the turbomachine is configured for a nominal operating state with a circumferential speed >60 m/s at the outermost circumference of the rotor.
6. The turbomachine as claimed in claim 1 ,
wherein the radial bearing is configured for an isentropic mounting.
7. The turbomachine as claimed in claim 1 ,
wherein the protruding first shaft end has a coupling, wherein a mass of the coupling is at least 2% of a total mass TMS of the rotor.
8. The turbomachine as claimed in claim 1 ,
wherein a weight force of an overhang mass OVM is at least 12% of the bearing load of the radial bearing.
9. The turbomachine as claimed in claim 1 ,
wherein the overhang OVH has a center of gravity, wherein the center of gravity of the overhang OVH is situated closer to the axial end of the rotor than to the axial center point of the radial bearing.
10. The turbomachine as claimed in claim 1 ,
wherein the rotor is configured for nominal operation such that, at nominal rotation speed, an imbalance centrifugal force of the overhang OVH at 1° bend on the radial bearing amounts to at least 60% of a static bearing force in the radial bearing.
11. The turbomachine as claimed in claim 1 ,
wherein a radial height of the cavity is less than 5% of the rotor diameter at the radial bearing position.
12. The turbomachine as claimed in claim 1 ,
wherein the turbomachine comprises a turbocompressor.