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A Quasi-Three Dimensional Calculation System for the Flow Within Transonic Compressor Blade Rows FREE

[+] Author Affiliations
W. J. Calvert, R. B. Ginder

Royal Aircraft Establishment, Pyestock, Farnborough, Hants, UK

Paper No. 85-GT-22, pp. V001T03A012; 8 pages
doi:10.1115/85-GT-22
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 calculation system has been set up to predict both the internal flow field and the overall performance of a transonic compressor blade row. The system iterates between an inviscid-viscous time-marching blade-to-blade (S1) treatment and a streamline curvature throughflow calculation for the pitchwise-averaged flow in the meridional plane (S2). A blade geometry package and a data transfer/display program are used to link the S1 and S2 methods to give a semi-automatic convergence procedure. The only empirically-based correlation or correction required is an extra loss imposed near the blade hub and tip to allow for end effects. The system has been applied to a high bypass ratio transonic fan rotor near design point. The converged solution was in good agreement with the measured performance.

Copyright © 1985 by ASME
This article is only available in the PDF format.

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