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Circumferential Asymmetry in Axial Flow Compressors

Published online by Cambridge University Press:  04 July 2016

M. D. C. Doyle  and
J. H. Horlock
M. D. C. Doyle
Affiliation:
Mechanical Engineering Department, University of Liverpool
J. H. Horlock
Affiliation:
Mechanical Engineering Department, University of Liverpool
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Extract

In this paper we are restricting our attention to those cases of circumferential inlet distortion where the distortion of the velocity profile is too large to be described as a small perturbation. Thus any theory describing the flow must use a mathematical model which is non-linear.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 70 , Issue 670 , October 1966 , pp. 953 - 957
Copyright
Copyright © Royal Aeronautical Society 1966

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References

1.Jaumotte, A. L.The Influence of Flow Distortions on Axial Flow Fan and on Rotating Stall. Zeitschrift für augewandte Mathemalik und Physik 15, Vol 2, pp 116–125. 1964.CrossRefGoogle Scholar
2.Pearson, H. and Mckenzie, A.Wakes in Axial Compressors. J Roy Aero Soc, Vol 63, 583, pp 415–416. 1959.CrossRefGoogle Scholar