Hostname: page-component-cb9f654ff-p5m67 Total loading time: 0 Render date: 2025-08-26T06:56:25.946Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access Rights & Permissions [Opens in a new window]

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 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

1. Goldstein, S. (Ed). Modern developments in fluid dynamics. Clarendon Press, Oxford. 1938.Google Scholar
2. Thwaites, B. (Ed). Incompressible aerodynamics. Clarendon Press, Oxford. 1960.10.1115/1.3644123Google Scholar
3. Head, M. R. Entrainment in the turbulent boundary layer. ARC R & M 3152. 1960.Google Scholar
4. Dunham, J. Predictions of boundary transition on turbo-machinery blades. AGARDograph 164, p 55, 1972.Google Scholar
5. Shaalan, M. R. A. The stalling performance of compressor cascades of different aspect ratios. Liverpool University PhD thesis, 1967.Google Scholar
6. Ilyas, M. and Norbury, J. F. Effect of axial velocity variation on the subsonic flow through a compressor cascade. IMechE. CP.3, p 276, 1973.Google Scholar