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A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order

A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order to feed the medium from the outside into the rotor interior, and rib-shaped ribs, in order to guide the medium further in the direction of the rotational axis, and the second rotor disk of the pair being configured with the aid of an auxiliary web in such a way that the flow passages which are formed between the ribs as viewed in the circumferential direction are delimited axially at least over the large part of the radial extent of the ribs.

대표청구항 ▼

1. A rotor for a turbomachine, comprising: at least one pair of rotor disks which lie on one another,wherein a first rotor disk of the at least one pair of rotor disks comprises a first disk web which runs endlessly about a rotational axis of the rotor and which comprises a first hub region at a rad

1. A rotor for a turbomachine, comprising: at least one pair of rotor disks which lie on one another,wherein a first rotor disk of the at least one pair of rotor disks comprises a first disk web which runs endlessly about a rotational axis of the rotor and which comprises a first hub region at a radially inner end of the first disk web and comprising a first central opening therethrough and a first ring region configured to receive rotor blades at a radially outer end of the first disk web, from which first ring region holes are arranged which are distributed along a circumference of the first rotor disk, which penetrate the first disk web toward the inside, and which open into a ring face of the first rotor disk which is arranged obliquely with respect to a radial direction of the first rotor disk, the first hub region comprising a multiplicity of radially oriented ribs configured to partly define flow paths therebetween, the flow paths providing fluid communication between the holes and the first central opening,wherein a second rotor disk of the at least one pair of rotor disks comprises a second disk web which runs endlessly about the rotational axis and which comprises a second hub region at a radially inner end of the second disk web comprising a second central opening therethrough and a second ring region configured to receive the rotor blades at a radially outer end of the second disk web, the second hub region comprising a projecting length on both sides of the second disk web in an axial direction of the rotor, one of the projecting lengths comprising an outwardly pointing freely ending annular auxiliary web,wherein an arrangement of the first rotor disk and the second rotor disk being selected such that the ribs and the auxiliary web are radially aligned so that the auxiliary web also partly defines the flow paths between the ribs, andwherein at least one of the ribs comprises a freely ending extension at its radially outwardly pointing ends. 2. The rotor as claimed in claim 1, wherein an extent, which can be detected in the radial direction, of the ribs and that of the auxiliary web and the projecting length are adapted to one another such that the ribs and the auxiliary web or the projecting length end on the same radius on the outside and on the inside. 3. The rotor as claimed in claim 1, wherein each rib extends along the radial direction from the inside to the outside. 4. The rotor as claimed in claim 1, wherein all of the ribs comprise the freely ending extension at respective radially outwardly pointing ends. 5. A rotor for a turbomachine, comprising: a first rotor disk comprising: a first disk web comprising a first hub and a first ring region configured to receive rotor blades; and holes each comprising a first opening arranged in the first ring region and a second opening at a ring face of the first rotor disk which is arranged radially inward of the first opening and obliquely with respect to a radial direction of the first rotor disk;wherein the first hub comprises a first central opening therethrough and a multiplicity of radially oriented ribs configured to partly define radially oriented flow paths therebetween, the flow paths providing fluid communication between the holes and the first central opening; anda second rotor disk disposed upstream of the first rotor disk and comprising a second disk web comprising a second hub region and a second ring region configured to receive the rotor blades;wherein the second hub region comprises a projecting length on both sides of the second disk web in an axial direction of the rotor, one of the projecting lengths comprising an outwardly pointing freely ending annular auxiliary web;wherein the rotor is configured such that the ribs and the auxiliary web are radially aligned so that the auxiliary web also partly defines the flow paths between the ribs, andwherein at least one of the ribs comprises a freely ending extension at its radially outwardly pointing ends. 6. The rotor of claim 5, wherein radially outward ends of the ribs define an annular shape, the second openings aim toward the annular shape. 7. The rotor of claim 5, wherein the ribs and the auxiliary web are set apart axially, thereby forming a gap therebetween.