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An Experimental Investigation of the Secondary Flow Occurring in a Compressor Cascade

Published online by Cambridge University Press:  07 June 2016

W. D. Armstrong
W. D. Armstrong*
Affiliation:
Cambridge University
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Summary

When a non-uniform stream flows through a cascade of compressor blades a three-dimensional secondary motion is generated in the outlet stream. This motion, which consists of a spanwise re-orientation of the Bernoulli planes, together with the effects of vorticity components in the stream direction, may be predicted theoretically. In this paper experimental results obtained on a 6 in. chord cascade are reported. The experimental and computed outlet angles are compared and the discrepancies are explained qualitatively. Additional particle track and visualisation experiments were designed to investigate the local blade flows and the effects of the nose vortices.

Type
Research Article
Information
Aeronautical Quarterly , Volume 8 , Issue 3 , August 1957 , pp. 240 - 256
Copyright
Copyright © Royal Aeronautical Society. 1957

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References

1. Hawthorne, W. R. Rotational Flow through Cascades. Pt. I, The Components of Vorticity. Quarterly Journal of Mechanics and Applied Mathematics. Vol. VIII, p. 266, 1955.CrossRefGoogle Scholar
2. Hawthorne, W. R. and Armstrong, W. D. Rotational Flow through Cascades. Pt. II, The Circulation About the Cascade. Quarterly Journal of Mechanics and Applied Mathematics, Vol. VIII, p. 280, 1955.CrossRefGoogle Scholar
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5. Armstrong, W. D. The Secondary Flow in a Cascade of Turbine Blades. R. & M. 2979, 1957.Google Scholar
6. Armstrong, W. D. The Non-Uniform Flow of Air through Cascades of Blades. Cambridge University Ph.D. Thesis, 1954.Google Scholar
7. Hawthorne, W. R. and Armstrong, W. D. Shear Flow through a Cascade. The Aeronautical Quarterly, Vol. VII, p. 247, November 1956.CrossRefGoogle Scholar