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An Improved Blade Root Design for Axial Flow Compressors (and Turbines)

Published online by Cambridge University Press:  04 July 2016

H. Shaw
H. Shaw*
Affiliation:
formerly Turbomachinery Dept, NGTE Pyestock, now Engine R&D Branch, Mintech, London
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Extract

To save weight, designers of aircraft gas turbines aim to produce axial compressors with fewer rows of blades and greater mass flows per unit of frontal area. These improvements often consist of increases in blade tip speeds and reductions in the ratio of the hub to tip diameters. As the efficiency of transonic blading is partly dependent upon a low value of blade pitch/chord it is now frequently necessary to design a blade with a greater actual chord at the tip than at the hub.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 74 , Issue 715 , July 1970 , pp. 589 - 594
Copyright
Copyright © Royal Aeronautical Society 1970 

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References

1.Stress concentration factors for a flat bar in tension. Data Sheet—No. 65004. IMechE/RAeS.Google Scholar
2. Heywood, R. B. Designing by photo-elasticity. p 224. Chapman and Hall Ltd, 1952.Google Scholar
3. Shaw, H. Blading for fluid flow machines. British Patent No. 1, 151, 937. US Pat. No. 3,458,119.Google Scholar