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Analysis of Transonic Turbomachinery Flows Using a 2-D Explicit Low-Reynolds k-ε Navier-Stokes Solver PUBLIC ACCESS

[+] Author Affiliations
F. Dejean, C. Vassilopoulos, G. Slmandirakis, K. C. Giannakoglou, K. D. Papailiou

National Technical University of Athens, Athens, Greece

Paper No. 94-GT-063, pp. V001T01A024; 12 pages
doi:10.1115/94-GT-063
From:
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7883-5
  • Copyright © 1994 by ASME

abstract

An explicit, time-marching fractional-step solver for the calculation of the two-dimensional compressible Navier-Stokes equations is presented. The advantage of using a fractional-step analysis is its simplicity and the fact that greater time-steps are allowed, since the stability criterion is less strict compared to other explicit solvers. Turbulence is modeled through a low-Reynolds k-ε model, for which a novel artificial viscosity scheme is implemented, ensuring a smooth ε-distribution close to solid walls. The method is used in order to numerically investigate the flow field in three different cascades, namely a highly loaded transonic linear turbine guide vane cascade in six different flow conditions, a transonic steam turbine cascade in two different flow conditions and a low supersonic compressor cascade. Calculations are performed using both H- and C-type grids.

Copyright © 1994 by ASME
This article is only available in the PDF format.

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