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Boundary Layers on Rough Compressor Blades FREE

[+] Author Affiliations
K. Bammert, R. Milsch

University of Hannover, Hannover, Germany

Paper No. 72-GT-48, pp. V001T01A047; 14 pages
doi:10.1115/72-GT-48
From:
  • ASME 1972 International Gas Turbine and Fluids Engineering Conference and Products Show
  • ASME 1972 International Gas Turbine and Fluids Engineering Conference and Products Show
  • San Francisco, California, USA, March 26–30, 1972
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7981-8
  • Copyright © 1972 by ASME

abstract

Blades of axial flow compressors are often roughened by corrosion or erosion. There is only scant information about the influence of this roughening on the boundary layers of the blades and thereby on the compressor efficiency. To obtain detailed information for calculating the efficiency drop due to the roughness, experimental investigations with an enlarged cascade have been executed. The results enabled to develop new formulas for a modified friction coefficient in the laminar region and for the laminar-turbulent transition and the separation points of the boundary layer. Thus, together with the Truckenbrodt theory, it was possible, to get a good reproduction of the experimental results.

Copyright © 1972 by ASME
This article is only available in the PDF format.

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