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Transonic and Supersonic Inviscid Computations in Cascades Using Adaptive Unstructured Meshes PUBLIC ACCESS

[+] Author Affiliations
F. Bassi

Università di Catania, Catania, Italy

S. Rebay

Politecnico di Milano, Milano, Italy

M. Savini

CNPM, Peschiera Borromeo, Italy

Paper No. 91-GT-312, pp. V001T01A095; 10 pages
doi:10.1115/91-GT-312
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

The paper describes a solution procedure for two dimensional compressible inviscid flows. The solution algorithm uses a finite volume spatial discretization on unstructured grids of triangles and an explicit Runge-Kutta time marching scheme; for steady problems efficiency is enhanced by using local time stepping and enthalpy damping. The use of unstructured meshes automatically adapted to the solution allows arbitrary geometries and complicated flow features to be treated easily and with high degree of accuracy, even if more work is needed to reach a computational efficiency comparable to those of existing structured codes. Adaptation criteria based on error estimates of significant flow variables have been implemented and tested. The method has been applied to the computation of transonic and supersonic flows in gas turbine nozzles and in impulse rotor cascades for spatial applications and the results have been compared with the experimental data.

Copyright © 1991 by ASME
Topics: Computation
This article is only available in the PDF format.

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