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Flow Investigations on Swirling Compressible Flow Through a Vaneless Radial Diffuser FREE

[+] Author Affiliations
D. P. Agrawal, S. M. Yahya, D. N. Reddy

Indian Institute of Technology, Delhi, India

Paper No. 87-GT-193, pp. V001T01A068; 8 pages
doi:10.1115/87-GT-193
From:
  • ASME 1987 International Gas Turbine Conference and Exhibition
  • Volume 1: Turbomachinery
  • Anaheim, California, USA, May 31–June 4, 1987
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7923-8
  • Copyright © 1987 by ASME

abstract

The present study deals with the experimental investigation of Swirling compressible flow through a parallel walled vaneless radial diffuser. Swirl generator of vortex nozzle type is used for supplying swirling compressible flow at the diffuser inlet up to a Mach number of 0.8. The desired flow angles are achieved by adjusting inlet swirl vane setting angles from 2.5° to 12.5°. The results are presented in terms of performance parameters such as pressure recovery and loss coefficient for various diffuser inlet Mach numbers from 0.3 to 0.8 and flow angle range from 20° to 35°. The effect of Mach number and swirl angle on the performance of the vaneless radial diffuser are discussed.

Copyright © 1987 by ASME
This article is only available in the PDF format.

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