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Cyclo-Symmetric Modal Synthesis of Rotating Bladed Disc System PUBLIC ACCESS

[+] Author Affiliations
Jin Zhang

Beijing University of Aeronautics & Astronautics, Beijing, China

W. L. Wang

Fudan University, Shanghai, China

X. J. Chen

Wuxi Aero-engine Design Research Institute, Wuxi, China

Paper No. 91-GT-051, pp. V005T14A005; 6 pages
doi:10.1115/91-GT-051
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award; General
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7902-3
  • Copyright © 1991 by ASME

abstract

The natural mode analysis of bladed disc system at an arbitrary constant rotational speed is investigated in this paper and the large deformation effect caused by the pretorsion of the blades is also considered. The computational method of group theory is employed in substructure technique and equilibrium position and stress distribution of the bladed disc system in centrifugal field are obtained through simultaneous iteration, further more, the initial stress stiffness matrix, the large deformation stiffness matrix and the corresponding rotating natural frequencies and modal shapes are determined. Because the large deformation effect of the blades is considered and all the interface degrees of freedom between the substructures can be eliminated in the present method, the computation work can be cut down remarkably under the precondition that the computational accuracy is ensured. It shows practically that the substructure simultaneous iteration method presented in this paper has a good convergency and greatly reduces the computation work.

Copyright © 1991 by ASME
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