A Novel Centrifugal Diffuser Test Device PUBLIC ACCESS

[+] Author Affiliations
R. P. Shreeve, H. D. Schulz, J. R. Erwin

Naval Postgraduate School, Monterey, CA

L. Schumann

NASA Lewis Research Center, Cleveland, OH

Paper No. 85-IGT-135, pp. V001T02A049; 14 pages
  • ASME 1985 Beijing International Gas Turbine Symposium and Exposition
  • Volume 1: Aircraft Engine; Turbomachinery
  • Beijing, People’s Republic of China, September 1–7, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7942-9
  • Copyright © 1985 by ASME


A large scale (2 inch wide test vanes at 50-inch inlet diameter), low speed (100–200 ft/sec) steady flow radial cascade wind tunnel for diffuser studies was designed, built and tested. The apparatus was shown to provide flow angles from radial in the range 58–72 degrees with suitable spanwise profiles. The novel flow angle control mechanism was shown to work but measured flow angles were somewhat smaller than expected. The mechanism for controlling case-wall boundary layer profile did not behave as predicted. Attempts to predict the generated flow both analytically and with computational codes are compared with initial measurements. The low speed apparatus will be used to obtain detailed data for diffuser design and analysis code verification, and to provide experience toward the design of a high speed device.

Copyright © 1985 by ASME
Topics: Diffusers
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