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Interactive computing methods for aeroelastic analysis of turbomachinery

  1. Alexandru Dumitrache*

Article first published online: 22 DEC 2004

DOI: 10.1002/pamm.200410261

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PAMM

PAMM

Volume 4, Issue 1, pages 560–561, December 2004

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How to Cite

Dumitrache, A. (2004), Interactive computing methods for aeroelastic analysis of turbomachinery. Proc. Appl. Math. Mech., 4: 560–561. doi: 10.1002/pamm.200410261

Author Information

  1. Institute of Statistics and Applied Mathematics, P.O. Box 1-24, RO-010145, Bucharest, Romania

*Phone: +40 21 411 4900, Fax: +40 21 411 4305

Publication History

  1. Issue published online: 22 DEC 2004
  2. Article first published online: 22 DEC 2004

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Abstract

An interaction viscous-inviscid method for efficiently computing steady and unsteady viscous flows is presented. The inviscid domain is modeled using a finite element discretization of the full potential equation. The viscous region is modeled using a finite difference boundary layer technique. The two regions are simultaneously coupled using the transpiration approach. A time linearization technique is applied to this interactive method. For unsteady flows, the fluid is assumed to be composed of a mean or steady flow plus a harmonically varying small unsteady disturbance. Numerically exact nonreflecting boundary conditions are used for the far field conditions. Results for some steady and unsteady, laminar and turbulent flow problems are compared to linearized Navier-Stokes or time-marching boundary layer methods. (© 2004 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)

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