Boundary Layer Optimization for the Design of High Turning Axial Flow Compressor Blades

[+] Author and Article Information
K. D. Papailiou

Low Speed Section, Turbomachinery Laboratory, von Karman Institute, Rhode Saint Genese, Belgium

J. Eng. Power 93(1), 147-154 (Jan 01, 1971) (8 pages) doi:10.1115/1.3445387 History: Received January 30, 1970; Online July 14, 2010


An optimization method, based on Le Foll’s boundary layer theory and on Goldstein’s conformal mapping method is described. The parameters of optimization are circulation per blade and absolute losses. The problem is treated as an inverse problem (i.e., the best blading is found starting from the flow conditions imposed). The performance of a highly loaded compressor cascade, designed according to the method presented and tested in a low speed wind tunnel, is compared with the theoretical predictions. Some discrepancies exist which are due to the influence of flow convergence and blade curvature. A modification of the method to take into account these effects is discussed.

Copyright © 1971 by ASME
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In