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A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and th

A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum.

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1. A rotor for a turbomachine which is exposable to an axial throughflow, comprising: a plurality of rotor disks arranged in a stacked manner and which are clamped to each other using a tie rod, each rotor disk including an outside diameter,wherein at least two of the plurality of rotor disks includ

1. A rotor for a turbomachine which is exposable to an axial throughflow, comprising: a plurality of rotor disks arranged in a stacked manner and which are clamped to each other using a tie rod, each rotor disk including an outside diameter,wherein at least two of the plurality of rotor disks includes a smaller outside diameter than one of the adjacent rotor disks and an existing diameter difference is compensated using a drum which annularly encompasses the two rotor disks with the smaller outside diameter,wherein an entire axial extent of the at least two rotor disks with the smaller outside diameter is encompassed by the drum, andwherein on an inner face of the drum there is an endlessly encompassing web which is axially clamped between the two encompassed rotor disks,wherein the web of the drum extends radially further inwards than the rotor disk with the smaller outside diameter, andwherein the web includes an axial width such that the web at least partially extends into a hub opening whereby the hub opening is a gap between the two rotor disks with the smaller outside diameter. 2. The rotor as claimed in claim 1, wherein a rotor disk with a larger outside diameter is arranged directly next to a rotor disk with a smaller outside diameter. 3. The rotor as claimed in claim 1, wherein the at least two rotor disks, as seen in an axial direction of the rotor, which are encompassed by the drum are hooked into the drum in order to absorb a plurality of centrifugal force loads. 4. The rotor as claimed in claim 3, wherein the at least two rotor disks, on a circumferential side of each rotor disk, have an annular hook which extends in the axial direction and engages in each case in a slot which is provided on the drum. 5. The rotor as claimed in claim 1, wherein the drum is formed from a more heat-resistant material than the rotor disk with the smaller diameter. 6. The rotor as claimed in claim 1, wherein the web includes a first set of two oppositely disposed, flange-like end faces which abut against a second and third set of flange-like end faces of the at least two adjacent rotor disks. 7. The rotor as claimed in claim 6, wherein the second and third set of end faces of the rotor disks and the first set of end faces of the web abut against each other in a form-fitting manner. 8. The rotor as claimed in claim 7, wherein the form fit is formed using a Hirth toothing. 9. The rotor as claimed in claim 1, wherein the drum includes a slot for accommodating a rotor blade. 10. The rotor as claimed in claim 9, wherein the slot is formed as a circumferential slot. 11. The rotor as claimed in claim 10, wherein a first number of circumferential slots is greater than a second number of rotor disks which are encompassed by the drum. 12. The rotor as claimed in claim 11, wherein an outer side of the drum accommodates a plurality of rotor blades which are arranged in a plurality of rings, andwherein a third number of rings which may be installed is greater than a fourth number of rotor disks which are encompassed by the drum. 13. A compressor, comprising: a rotor, comprising: a plurality of rotor disks arranged in a stacked manner and which are clamped to each other using a tie rod, each rotor disk including an outside diameter,wherein at least two of the plurality of rotor disks includes a smaller outside diameter than one of the adjacent rotor disks and an existing diameter difference is compensated using a drum which annularly encompasses the two rotor disks with the smaller outside diameter,wherein an entire axial extent of the at least two rotor disks with the smaller outside diameter is encompassed by the drum,wherein on an inner face of the drum there is an endlessly encompassing web which is axially clamped between the two encompassed rotor disks,wherein the web of the drum extends radially further inwards than the rotor disk with the smaller outside diameter, andwherein the web includes an axial width such that the web at least partially extends into a hub opening whereby the hub opening is a gap between the two rotor disks with the smaller outside diameter. 14. The compressor as claimed in claim 13, wherein a rotor disk with a larger outside diameter is arranged directly next to a rotor disk with a smaller outside diameter. 15. The compressor as claimed in claim 13, wherein the compressor includes a pressure ratio of more than 1:16. 16. The compressor as claimed in claim 13, where the compressor is the compressor of a stationary gas turbine used for power generation. 17. A gas turbine, comprising: a compressor, comprising: a rotor, comprising: a plurality of rotor disks arranged in a stacked manner and which are clamped to each other using a tie rod, each rotor disk including an outside diameter,wherein at least two of the plurality of rotor disks includes a smaller outside diameter than one of the adjacent rotor disks and an existing diameter difference is compensated using a drum which annularly encompasses the two rotor disks with the smaller outside diameter,wherein an entire axial extent of the at least two rotor disks with the smaller outside diameter is encompassed by the drum,wherein on an inner face of the drum there is an endlessly encompassing web which is axially clamped between the two encompassed rotor disks,wherein the web of the drum extends radially further inwards than the rotor disk with the smaller outside diameter, andwherein the web includes an axial width such that the web at least partially extends into a hub opening whereby the hub opening is a gap between the two rotor disks with the smaller outside diameter. 18. The gas turbine as claimed in claim 17, wherein a rotor disk with a larger outside diameter is arranged directly next to a rotor disk with a smaller outside diameter. 19. The gas turbine as claimed in claim 17, wherein a nominal output of the gas turbine is more than 50 mega watts.