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The Influence of Attached Boundary Layers in Determining the Optimum Loading for Blades in Cascade

Published online by Cambridge University Press:  04 July 2016

B. S. Stratford
B. S. Stratford*
Affiliation:
Rolls-Royce Ltd
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Extract

In the design of cascade blading for compressors and turbines it is often assumed that the maximum efficiency will be attained at the maximum loading that just avoids separation and critical Mach number effects. In a turbine, the overall pressure gradient is favourable so that it should be possible to achieve very high loadings and yet avoid separation. The question then arises as to whether or not such high loadings would produce a high efficiency. The present note suggests that in fact there is an optimum loading, beyond which there would be no improvement in efficiency even though separation and critical Mach number effects were avoided.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 69 , Issue 650 , February 1965 , pp. 133 - 135
Copyright
Copyright © Royal Aeronautical Society 1965

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References

1.Allan, W. K. Theoretical Analysis of the Performance of Cascade Blades. ARC Tech. Note 23 061.Google Scholar
2.Stratford, B. S. and Beavers, G. S. The Calculation of the Compressible Turbulent Boundary Layer—A Correlation of Certain Previous Methods. R & M 3207, 1959/61.Google Scholar
3.Thwaites, B.Approximate Calculation of the Laminar Boundary Layer. Aeronautical Quarterly, Vol. 1, p. 245, 1949-50.Google Scholar
4.Heurteux, B. Calculation of the Pressure Distributions around some Turbine Blades. Private Communication, Rolls-Royce Ltd., February 1964.Google Scholar