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Approximate Estimation of the Passage Vorticity in the Secondary Flow Behind A Cascade

Published online by Cambridge University Press:  04 July 2016

S. Soundranayagam
S. Soundranayagam*
Affiliation:
Formerly Mechanical Engineering Laboratory, English Electric Co. Ltd., now Department of Mechanical Engineering, University of Hong Kong
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Extract

Expressions for the secondary circulation behind a cascade are derived in Ref. 1. A simple derivation of the same results is given in Ref. 2. The secondary flows within the blade passages and their extensions downstream are determined by the “secondary passage circulation”, Г, given by

for a diffusing cascade, and

for an accelerating cascade,

where Ul inlet velocity to cascade

z distance in spanwise direction

s blade pitch

αl, inlet flow angle

α2 outlet flow angle

Ll, distance along lower side of aerofoil

L2 distance along upper side of aerofoil

q1 velocity along lower side of aerofoil

qu velocity along upper side of aerofoil.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 64 , Issue 598 , October 1960 , pp. 635 - 638
Copyright
Copyright © Royal Aeronautical Society 1960

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References

1.Hawthorne, W. R. (1955.) Rotational Flow Through Cascades. Quarterly Journal of Mechanics and Applied Mathematics, Vol. 8, Part 3, 1955.Google Scholar
2.Soundranayagam, S. (1957). The Secondary Flow Behind a Cascade. Journal of the Aeronautical Sciences, pp. 706–707, Sept. 1957.Google Scholar
3.Squire, H. B. and Winter, K. G. (1951). The Secondary Flow in a Cascade of Aerofoils in a Non-Uniform Stream. Journal of the Aeronautical Sciences, Vol. 18, 1951.Google Scholar