Rotor arrangement for a turbomachine and compressor

Patent metadata

Field	Value
Publication number	US-10519774-B2
Application number	US-201615133406-A
Country	US
Kind code	B2
Filing date	Apr 20, 2016
Priority date	May 7, 2015
Publication date	Dec 31, 2019
Grant date	Dec 31, 2019

Abstract

The present invention relates to a rotor arrangement for a turbomachine, having a rotor with a first rotor stage, a shaft, and a first hub for joining the first rotor stage to the shaft. The first hub has a balancing device for balancing the first rotor stage. In addition, the present invention relates to a compressor.

First claim

What is claimed is:

1. A rotor arrangement for a turbomachine, comprising:
a rotor comprising a first rotor stage, a second rotor stage, a shaft, and a first hub for joining the first rotor stage to the shaft,
wherein the first hub has a balancing device for balancing the first rotor stage,
wherein the first rotor stage includes a first basic rotor body and does not have a balancing device disposed thereon,
wherein the second rotor stage comprises a second basic rotor body with a rotor arm joining the first rotor stage to the second rotor stage, and
wherein a second balancing device is disposed on a radially outer side of the second rotor stage.

2. The rotor arrangement according to claim 1 , wherein the first basic rotor body is an integrally bladed basic rotor body or a basic rotor body with blades joined to the first basic rotor body in form-fitting manner.

3. The rotor arrangement according to claim 1 , wherein the first hub comprises a balancing ring and/or balancing weights for balancing the first rotor stage.

4. The rotor arrangement according to claim 1 , wherein the first rotor stage does not have a balancing fret and/or a balancing flange.

5. The rotor arrangement according to claim 1 , wherein the rotor arm has a radial passage opening for the through-flow of fluids from an inside space of the rotor into an outside space of the rotor.

6. The rotor arrangement according to claim 1 , wherein the rotor arrangement is configured and arranged for use in a compressor of a turbomachine.

7. The rotor arrangement according to claim 6 , wherein the compressor is a high-pressure compressor of an aircraft engine.

Assignees

• MTU Aero Engines AG

Inventors

• Boewing Stefan

Classifications

• F05D2220/3219

  for the last stage of a compressor or a high pressure compressor · CPC title

• F04D29/701

  especially adapted for elastic fluid pumps · CPC title

• F05D2240/60

  Shafts · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F04D29/321

  for axial flow compressors · CPC title