Engine Dynamic Analysis With General Nonlinear Finite Element Codes: Part II — Bearing Element Implementation, Overall Numerical Characteristics and Benchmarking PUBLIC ACCESS

[+] Author Affiliations
J. Padovan, M. Adams, P. Lam

The University of Akron, Akron, OH

D. Fertis, I. Zeid

Northeastern University, Boston, MA

Paper No. 82-GT-292, pp. V005T13A025; 9 pages
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; Process Industries; Technology Resources; General
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7960-3
  • Copyright © 1982 by ASME


In an attempt to increase jet engine efficiences, typically smaller rotor-stator-running clearances are being employed. Because of this and the ever present need to improve maintenance, reliability and structural integrity under various modes of operation, more sophisticated analyses tools are required to model the engine. Due to the wide-spread usage of general purpose finite element codes, this report seeks to adapt the procedure to use in modeling turbine rotor-bearing-stator structure. The work outlined in this report covers the second phase of work on a three-phase NASA Lewis sponsored research grant on engine dynamic simulation by developing strategies which enable the use of available finite element codes.

Copyright © 1982 by ASME
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