Rotor for a thermal turbomachine

Patent metadata

Field	Value
Publication number	US-2016146010-A1
Application number	US-201414904542-A
Country	US
Kind code	A1
Filing date	Jun 26, 2014
Priority date	Jul 17, 2013
Publication date	May 26, 2016
Grant date	—

Abstract

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.

First claim

1 .- 8 . (canceled)

9 . A rotor disk for a rotor of a turbomachine, comprising:
a disk web which runs endlessly about a rotational axis of the rotor disk and a hub region with a central opening at its radially inner end in relation to the rotational axis and a ring region for receiving rotor blades at its radially outer end, the hub region having a projecting length on both sides in the axial direction, at least one of the two projecting lengths of the hub region comprising an outwardly pointing freely ending annular auxiliary web with the formation of an annular recess, wherein a transversely projecting collar is arranged on both disk sides in the ring region, the collar height of which collar is slightly greater than the height of the relevant projecting length.

10 . The rotor disk as claimed in claim 9 ,
configured as a compressor disk or as a turbine disk.

11 . A rotor for a turbomachine, comprising:
at least one pair of rotor disks which lie on one another, wherein the first of the two rotor discs of the pair having a disk web which runs endlessly about a rotational axis of the rotor disk and has a hub region with a central opening at its radially inner end in relation to the rotational axis and a ring region for receiving rotor blades at its radially outer end, from which ring region holes are arranged which are distributed along the circumference, penetrate the disk web toward the inside, and open into a ring face of the rotor disk which is arranged obliquely with respect to the radial direction, the hub region having a multiplicity of ribs for flow forwarding of air which can flow through the holes in a manner which is adjacent radially on the inside with respect to the ring face, and wherein the second of the two rotor disks of the pair being configured as claimed in claim 9 , wherein the arrangement of the first and the second rotor disk of the pair being selected such that ribs and auxiliary web lie opposite one another.

12 . The rotor as claimed in claim 11 ,
wherein the 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.

13 . The rotor as claimed in claim 11 ,
wherein each guide element extends along the radial direction from the inside to the outside.

14 . The rotor as claimed in claim 11 ,
wherein at least one of the ribs, has a freely ending extension at its radially outwardly pointing ends.

15 . The rotor as claimed in claim 11 ,
wherein the first rotor disk is configured as a compressor disk or as a turbine disk in a manner which corresponds to the second rotor disk.

16 . The rotor as claimed in claim 11 ,
wherein all of the ribs have a freely ending extension at their radially outwardly pointing ends.

Assignees

• Siemens Ag

Inventors

• Costamagna Karin
• Kolk Karsten
• Stock Sebastian
• Veitsman Vyacheslav

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F04D29/321 Primary

  for axial flow compressors · CPC title

• F01D25/12

  Cooling · CPC title

• F01D5/02 Primary

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2240/24

  for turbines · CPC title