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The effect of stream surface convergence on turbomachine blade boundary layers
Published online by Cambridge University Press: 04 July 2016
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.
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- Copyright © Royal Aeronautical Society 1974
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