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Simplified Inverse Design of a Straight Vaneless Diffuser of Radial Stage FREE

[+] Author Affiliations
S. V. Horn

Borg-Warner Corporation, Des Plaines, IL

Paper No. 83-GT-2, pp. V001T01A001; 7 pages
doi:10.1115/83-GT-2
From:
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7951-1
  • Copyright © 1983 by ASME

abstract

Two inverse design methods of a vaneless diffuser, with the inviscid core symmetry along radial mid-streamline, are presented. Inverse design models consist of an inviscid core and attached skewed turbulent boundary layers computed by Cebeci’s method. The displacement model was used for inverse design studies and compared with the entrainment model. Both inverse design models were corroborated with the published vaneless diffuser design featuring convergent contours. For the same inlet conditions the inverse design would provide attached flow while the tested diffuser had backflow region. Inverse design studies clarify the effect of the inlet swirl angle, Laval number, specific heat ratio, boundary layer blockage, skew angle, Reynolds number and skin friction coefficient on the diffuser contour generation for a radial pump or compressor stage. The inlet swirl angle was chosen to vary from 15–30°, the inlet Laval number from 0–1.1 and the inlet boundary layer blockage from 0.2% to 5% of inlet diffuser width.

Copyright © 1983 by ASME
This article is only available in the PDF format.

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