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Modeling Unsteady Flow Effects in a 3D Transonic Compressor

[+] Author Affiliations
Magnus Stridh, Lars-Erik Eriksson

Chalmers University of Technology, Göteborg, Sweden

Paper No. GT2005-68149, pp. 951-960; 10 pages
doi:10.1115/GT2005-68149
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

When using the mixing-plane method in a multistage axial compressor all unsteady effects due to blade row interactions is lacking compared to a U-RANS method. By writing the ensemble-passage-averaged flow equations it is seen that, in the mixing-plane case, the so-called deterministic stress terms (DST) are missing. Previous work has shown that the DST terms are accurately predicted in 2D using a linearized harmonic approach. The present study is one of the first applications of this technique for calculating unsteady effects in adjunctive blade rows based on full 3D linearized N-S equations (LN-S). In this work the effects of DST terms on the average flow are evaluated at several operating points along a speedline, and are compared with conventional RANS solutions. Our main interest in this paper is to see how the DST affects typical design parameters for the compressor running at various conditions along a speedline. The overall methodology, first solve the steady state with conventional mixing-plane, secondly use this as input for LN-S solver and obtain the DST terms and finally use these to correct the average flow field, appears to work well also in fully 3D transonic cases. No problem have been encountered obtaining solutions to the linearized N-S equations. This is attributed to the use of a solution technique which is highly compatible with the steady-state RANS solver. The effects of the DST terms on the steady-state RANS solutions are significant in terms of performance parameters, such as losses and blockage. The method also makes it possible to evaluate unsteady effects, such as time dependent blade loads due to wake interactions.

Copyright © 2005 by ASME

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