Rotor arrangement for a low-pressure turbine of a turbomachine
The invention relates to a rotor arrangement for a low-pressure turbine of a turbomachine with end-side linkage to a shaft of the turbomachine, comprising a plurality of rotating stages, which are arranged in a flow direction and are connected to one another, wherein the last rotating stage in the flow direction can be linked to the shaft by a rotor disk.
1 . A rotor arrangement for a low-pressure turbine of a turbomachine with end-side linkage to a shaft of the turbomachine, comprising:
a plurality of rotating stages, which are arranged in a flow direction and are connected to one another,
wherein the rotor arrangement is linked to the shaft in the flow direction at a last rotating stage of the plurality of rotating stages by a rotor disk, wherein the rotor disk is configured and arranged as a conical disk that expands radially outward along an axial length from upstream to downstream; the rotor disk having a wall between a radially inner shaft linkage region and a radially outer hub region; the wall having a thinnest region; the wall having only one widening of the wall thickness from the thinnest region of the wall to the shaft linkage region and only one widening of the wall thickness extending from the thinnest region of the wall to the hub region.
2 . The rotor arrangement according to claim 1 , wherein the rotor disk, formed as a conical disk, is linked to the shaft in the axial direction between a first rotating stage and the last rotating stage.
3 . The rotor arrangement according to claim 1 , wherein the wall encloses an angle with the axis of rotation of the shaft in the range of 44° to 56°.
4 . The rotor arrangement according to claim 1 , wherein the rotor disk, formed as a conical disk, has at least one fillet radius at the shaft linkage region.
5 . The rotor arrangement according to claim 1 , wherein a bearing of the rotor is arranged radially within a second rotating stage of the rotor arrangement.
6 . The rotor arrangement according to claim 1 , wherein an axial distance between the first rotating stage and the last rotating stage is 21 cm to 25 cm.
7 . The rotor arrangement according to claim 1 , wherein a radial distance between a turbomachine axis and an outer diameter of a first rotor disk of the first rotating stage is 19 cm to 32 cm.
8 . The rotor arrangement according to claim 1 , wherein a ratio of the axial distance between the first rotating stage and the last rotating stage and the radial distance of the turbomachine axis to the outer diameter of the first rotor disk is 0.95 to 1.45.
9 . The rotor arrangement according to claim 1 , wherein a ratio of the axial distance between the first rotating stage and the last rotating stage and an axial distance between the bearing of the rotor and the last rotating stage is 1.2 to 1.7.
10 . The rotor arrangement according to claim 1 , wherein a ratio of the axial distance between the first rotating stage and the last rotating stage and a linkage distance between the bearing of the rotor and the shaft linkage region is 2.7 to 3.3.
11 . A low-pressure turbine for an aircraft engine turbomachine, with a four-stage low-pressure turbine, comprising a rotor arrangement formed according to claim 1 .
12 . An aircraft engine turbomachine, comprising a rotor arrangement formed according to claim 1 .
13 . An aircraft engine turbomachine, comprising a low-pressure turbine formed according to claim 11 .