A Study on the Blade Shape Influence on Flow Distribution and Performance in Centrifugal Compressor Rotors PUBLIC ACCESS

[+] Author Affiliations
Raffaele Tuccillo, Adolfo Senatore

University of Naples, Napoli, Italy

Paper No. 90-GT-099, pp. V001T01A029; 10 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


The authors present an analysis of the flow through a centrifugal compressor rotor. A quasi-3D flow model evaluates the interaction of the meridional and blade-to-blade solution, so as to determine the flow pattern inside an inviscid region.

A further interaction is then considered between the non-viscous flow and the boundary layers which grow along the end-walls and the blade surfaces. This makes it possible both to determine a more realistic flow condition, because of the blockage effects exerted by the boundary layers, and to estimate the total pressure losses related to the momentum thickness.

Examples are presented for a compressor of an aircraft engine. The influence of blade shape on the above described phenomena is analyzed, starting from the actual rotor geometry and making a parametric study of the alterations in flow pattern produced by changes in meridional blade shape, inlet and outlet flow areas, and splitter blades.

The analysis will provide a basis for future activities involving the use of optimizing techniques for the final choice of the blade characteristics.

Copyright © 1990 by ASME
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