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The effect of stream surface convergence on turbomachine blade boundary layers

Published online by Cambridge University Press:  04 July 2016

J. Dunham
J. Dunham*
Affiliation:
National Gas Turbine Establishment
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Extract

The design and analysis of axial turbomachine blade profiles has usually been done assuming the flow to be two-dimensional, that is assuming the blade-to-blade stream surfaces are parallel planes. Similarly, most of the detailed experimental studies of blade profiles have been done in nominally two-dimensional cascades or using wall boundary layer suction to achieve (on average) two-dimensional conditions. In an actual compressor or turbine, however, this condition rarely obtains.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 78 , Issue 758-759 , March 1974 , pp. 90 - 92
Copyright
Copyright © Royal Aeronautical Society 1974 

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References

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