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The Cascade Subjected to Inlet Distortions

Published online by Cambridge University Press:  07 June 2016

S. Fujii
S. Fujii*
Affiliation:
National Aerospace Laboratory, Tokyo
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Summary

This paper presents a method for evaluating the effects of shear flow on the performance of a two-dimensional cascade in an incompressible fluid. The method of distributing the singularities along the chord is modified to meet the requirement that the sum of the distorted and perturbed velocities should produce a flow around the aerofoil; therefore an actuator-disc or flat-plate type approximation is not used. Attention is confined to a single row of arbitrary aerofoils subjected to pure harmonic distortions, no attempt being made to include time-dependent terms. Hence it is probable that this paper offers the first stage of a time-independent solution for assessing the effects of upstream struts or blade rows. The agreement between this method and the exact solution for an isolated flat-plate aerofoil is fairly good.

Numerical examples are presented and discussed with reference to the changes of lift, deviation angle and surface velocity which distortion over the cascade would produce. It is found, for the limited number of examples calculated, that a positively-staggered cascade readily responds to the variation of geometrical parameters chosen.

Type
Research Article
Information
Aeronautical Quarterly , Volume 19 , Issue 3 , August 1968 , pp. 284 - 300
Copyright
Copyright © Royal Aeronautical Society. 1968

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References

1. Ehrich, F. Circumferential inlet distortions in axial flow turbomachinery. Journal of the Aeronautical Sciences, Vol. 22, p. 413, June 1957.CrossRefGoogle Scholar
2. Seidel, B. S. Asymmetric inlet flow in axial turbomachihes. ASME Transactions, Series A, Vol. 86, p. 18, January 1964.Google Scholar
3. Kemp, N. H. and Sears, W. R. Aerodynamic interference between moving blade rows. Journal of the Aeronautical Sciences, Vol. 20, No. 9, p. 585, September 1953.CrossRefGoogle Scholar
4. Kemp, N. H. and Sears, W. R. The unsteady forces due to viscous wakes in turbo-machines. Journal of the Aeronautical Sciences, Vol. 22, p. 478, July 1955.Google Scholar
5. Meyer, R. X. The effect of wakes on the transient pressure and velocity distributions in turbomachines. ASME Transactions, Vol. 80, p. 1544, October 1958.Google Scholar
6. Yeh, H. and Eisenhuth, J. J. The unsteady wake interaction in turbomachinery and its effect on cavitation. ASME Transactions, Series D, Vol. 81, p. 181, June 1959.Google Scholar
7. Schlichting, H. Berechnung der reibungslosen inkompressiblen Strömung für ein vorgegebene ebenes Schaufelgitter. VDI-Forschungsheft 447, 1955.Google Scholar
8. Mellor, G. I. An analysis of axial compressor cascade aerodynamics. ASME Transactions, Series D, Vol. 81, p. 362, September 1959.CrossRefGoogle Scholar
9. Pollard, D. and Wordsworth, J. A comparison of two methods for predicting the potential flow around an arbitrary aerofoil in cascade. ARC Current Paper 618, June 1962.Google Scholar
10. Lewis, R. I. and Pennington, G. A. Theoretical investigation of some basic assumptions of Schlichting’s singularity method of cascade analysis. ARC Current Paper 813, September 1964.Google Scholar
11. Tsien, H. S. Symmetrical Joukowsky airfoils in shear flow. Quarterly Journal of Applied Mathematics, Vol. 1, p. 130, 1943.Google Scholar
12. Nagamatsu, H. T. Circular cylinder and flat plate airfoil in a flow field with parabolic velocity distribution. Journal of Mathematics and Physics, Vol. 30, p. 131, 1951.Google Scholar