Interdependence of Centrifugal Compressor Blade Geometry and Relative Flow Field PUBLIC ACCESS

[+] Author Affiliations
H. Krain

DFVLR, Institut für Antriebstechnik, Cologne, West Germany

Paper No. 85-GT-85, pp. V001T03A027; 7 pages
  • ASME 1985 International Gas Turbine Conference and Exhibit
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Houston, Texas, USA, March 18–21, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7938-2
  • Copyright © 1985 by ASME


The influence of the impeller blade geometry on the calculated relative flow field has been studied by means of an impeller design program available at DFVLR [9]. Several geometrical parameters were varied, however, the meridional channel geometry was always kept constant. By this approach the blade wrap angle has been found to react significantly on the relative flow which is illustrated by comparing two designs with different wrap angles. Primarily in the hub/leading edge area a better boundary layer flow connected with a reduction of blade loading was obtained by increasing the wrap angle. But also in the shroud/pressure side area the increased blade looping attributed to an additional flow stabilization.

Copyright © 1985 by ASME
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