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Apparatus and method for retaining bladed rotor disks of a jet engine

  • US 20090016886A1
  • Filed: 07/03/2008
  • Published: 01/15/2009
  • Est. Priority Date: 07/06/2007
  • Status: Active Grant
First Claim
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1. An apparatus for retaining bladed rotor disks in a jet engine which includes an axial-flow compressor having a plurality of bladed rotor disks, with at least two bladed rotor disks at a compressor inlet side being designed as blisks where each blisk integrally combines a rotor disk and circumferentially distributed rotor blades;

  • at least one turbine section; and

    at least one shaft interconnecting the compressor and turbine section;

    comprising;

    at least one tie-rod, releasably retaining the blisks while the other rotor disks are firmly attached to each other separately and independently of the tie-rod.

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