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A Two-Dimensional Transonic Flow Model for Turbomachines Using an Implicit Lambda Scheme FREE

[+] Author Affiliations
J. O. Cruickshank, J. Brasz

United Technologies, Syracuse, NY

Paper No. 85-GT-163, pp. V001T03A038; 8 pages
doi:10.1115/85-GT-163
From:
  • ASME 1985 International Gas Turbine Conference and Exhibit
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Houston, Texas, USA, March 18–21, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7938-2
  • Copyright © 1985 by ASME

abstract

A two-dimensional Euler solver allowing the calculation of transonic flow conditions and weak shocks for turbomachinery blade rows is presented. The algorithm is based on a second-order-accurate finite-difference version of the implicit lambda scheme applied to the Euler equations assuming isentropic flow conditions. Using a fairly simple grid point network with equal spacing in meridional and tangential directions, this algorithm has been used successfully to calculate stationary and rotating stages of axial, radial and mixed flow turbomachinery cascades. Predictions are shown for a Laval nozzle and a high-turning turbine nozzle and compared against theoretically and experimentally available data.

Copyright © 1985 by ASME
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