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An Influence of Shroud Design on the Dynamic and Aeroelastic Behavior of Bladed Disc Assemblies PUBLIC ACCESS

[+] Author Affiliations
G. Jacquet-Richardet

Institut National des Sciences Appliquées, Villeurbanne, France

F. Moyroud

Institut National des Sciences Appliquées, Villeurbanne, FranceRoyal Institute of Technology, Stockholm, Sweden

T. H. Fransson

Royal Institute of Technology, Stockholm, Sweden

Paper No. 97-GT-191, pp. V004T14A037; 7 pages
doi:10.1115/97-GT-191
From:
  • ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award
  • Orlando, Florida, USA, June 2–5, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7871-2
  • Copyright © 1997 by ASME

abstract

Precise non-linear aeroelastic modeling of shrouded bladed-disc assemblies is generally beyond present capacities and analyses often assume that the behavior of the coupled system remains linear and retains a cyclic symmetrical property. In this paper, several models of shrouded assemblies, in the particular case of fully slipping interfaces, are examined and compared. Considering the cyclic symmetrical property of the structure, only the model where shroud segments can slip and propagation relations are applied in the direction normal to the interface plane, should be used. A reduced model based on a direct discretisation of the whole assembly is presented and validated. The application is based on a first stage shrouded fan. The influence of varying the interface shroud angle is examined in terms of frequency, mode shape and aeroelastic damping.

Copyright © 1997 by ASME
Topics: Design , Disks
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