Measured and Predicted Effects of Inlet Distortion on Axial Compressors PUBLIC ACCESS

[+] Author Affiliations
J. P. Longley

Cambridge University, Cambridge, England

Paper No. 90-GT-214, pp. V001T01A067; 7 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


Encouraging developments have recently been made both in the understanding and the modelling of compressor flowfields. This paper describes an experimental investigation undertaken to assess the validity of the assumptions made in the simple non-linear model for a bladerow operating in an unsteady or non-uniform flowfield. The results show that the basic fluid dynamics of the problem have been correctly modelled and that meaningful predictions may be made. The measurements also indicate that inlet guide vanes may be more sensitive to incidence variations than had been previously thought. The effects of inter-bladerow gaps are also discussed.

Copyright © 1990 by ASME
Topics: Compressors
This article is only available in the PDF format.



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