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Numerical Integration of the 3D Unsteady Euler Equations for Flutter Analysis of Axial Flow Compressors FREE

[+] Author Affiliations
G. A. Gerolymos

SNECMA, Villaroche Research Center, Moissy Cramayel, France

Paper No. 88-GT-255, pp. V001T01A091; 10 pages
doi:10.1115/88-GT-255
From:
  • ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 6–9, 1988
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7918-4
  • Copyright © 1988 by ASME

abstract

In order to analyze axial-flow compressor flutter, methods are required that compute the unsteady flow through vibrating cascades. A 3D fully nonlinear method has been developed by numerically integrating the 3D unsteady Euler equations, in the time-domain. The equations are discretized in a moving grid, which conforms with the vibrating blades and are integrated using the explicit MacCormack scheme, in finite-difference formulation. The method assumes a traveling-wave assembly mode of vibration. In this manner, the flow is computed in a single channel by applying the corresponding chorochronical periodicity condition at the permeable pitchwise limits. The blade vibratory mode is an input to the method obtained by a standard finite element method structural analysis code. A number of results are presented, for a transonic fan rotor, illustrating the possibilities of the method, both in started and unstarted supersonic flow conditions.

Copyright © 1988 by ASME
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