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A Numerical Technique for the Calculation of Transonic Flows in Turbomachinery Cascades FREE

[+] Author Affiliations
S. Gopalakrishnan, R. Bozzola

Avco Lycoming Div., Stratford, CT

Paper No. 71-GT-42, pp. V001T01A042; 10 pages
doi:10.1115/71-GT-42
From:
  • ASME 1971 International Gas Turbine Conference and Products Show
  • ASME 1971 International Gas Turbine Conference and Products Show
  • Houston, Texas, USA, March 28–April 1, 1971
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7982-5
  • Copyright © 1971 by ASME

abstract

A numerical technique is presented for the calculation of steady inviscid transonic flows in turbomachinery cascades, wherein both subsonic and supersonic regions co-exist. The problem is posed in the time-dependent form and the aysmptotic solution at large times provides the solution of the steady physical problems. The solutions for a hyperbolic nozzle cascade and two turbine cascades are compared with other analytical solutions and with an experimental result. The agreement appears to be very good. Some preliminary results are presented for a flow containing an oblique shock and its reflection. The computed results compare satisfactorily with the exact solution.

Copyright © 1971 by ASME
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