Rotor for a turbomachine and compressor

Patent metadata

Field	Value
Publication number	US-2016362995-A1
Application number	US-201615148567-A
Country	US
Kind code	A1
Filing date	May 6, 2016
Priority date	May 7, 2015
Publication date	Dec 15, 2016
Grant date	—

Abstract

A rotor for a turbomachine having at least a first rotor main body and a second rotor main body, the second rotor main body having a rotor arm having an arrangement for form-fittingly flange-mounting the first rotor main body to the second rotor main body, the arrangement having a balancing ring disposed on the radially outer side of the rotor arm is provided. The balancing ring is integrally connected to the rotor arm for form-fittingly flange-mounting the second rotor main body to the first rotor main body, the arrangement being disposed at the upstream and/or downstream end of the rotor arm. A compressor of a turbomachine having a rotor is also provided.

First claim

What is claimed is:

1 . A rotor for a turbomachine, the rotor comprising:
at least a first rotor main body; and a second rotor main body, the second rotor main body having a rotor arm having an arrangement for form-fittingly flange-mounting the first rotor main body to the second rotor main body, the arrangement including a balancing ring disposed on a radially outer side of the rotor arm, the balancing ring being integrally connected to the rotor arm for form-fittingly flange-mounting the second rotor main body to the first rotor main body, the arrangement being disposed at an upstream or downstream end of the rotor arm.

2 . The rotor as recited in claim 1 wherein the first and second rotor main bodies receive rotor blades to form a first rotor stage and a second rotor stage.

3 . The rotor as recited in claim 1 wherein the first and second rotor main bodies are integrally connected to rotor blades.

4 . The rotor as recited in claim 1 wherein the rotor arm has at least one sealing tip for reducing leakage flows between the rotor and a stator vane assembly of the turbomachine.

5 . The rotor as recited in claim 4 wherein the at least one sealing tip is configured to form a sealing gap with respect to an abradable seal.

6 . The rotor as recited in claim 1 wherein a radial extent of the balancing ring is less than a radial extent of at least one sealing tip on the rotor arm.

7 . The rotor as recited in claim 1 wherein the rotor arm is made from or contains a first material, and the balancing ring is made from or contains a second material, the first material and the second material being different.

8 . The rotor as recited in claim 1 wherein the balancing ring has on a periphery at least one region for material removal for balancing of the rotor.

9 . The rotor as recited in claim 1 wherein the first rotor main body has a balancing flange having at least one balancing weight.

10 . The rotor as recited in claim 1 wherein the rotor arm has an opening allowing fluids to pass therethrough from an inner rotor space to an outer rotor space.

11 . A compressor of a turbomachine, the compressor comprising:
at least one rotor as recited in claim 1 ; and at least one stator stage having an inner ring.

12 . A high-pressure compressor of an aircraft engine comprising the compressor as recited in claim 11 .

Assignees

• MTU Aero Engines AG

Inventors

• Albers Lothar

Classifications

• F04D29/321

  for axial flow compressors · CPC title

• F04D29/083

  especially adapted for elastic fluid pumps · CPC title

• F01D5/02

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

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title