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Three Dimensional Flow in a Linear Compressor Cascade at Design Conditions PUBLIC ACCESS

[+] Author Affiliations
Shun Kang, Ch. Hirsch

Vrije Universiteit Brussel, Pleinlaan, Brussels, Belgium

Paper No. 91-GT-114, pp. V001T01A047; 8 pages
doi:10.1115/91-GT-114
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

Experimental data measured upstream, inside and downstream of a large scale linear compressor cascade with NACA 65-1810 blade profile are presented. The flow is surveyed at 15 traverse planes with 14 (in half span) × 24 (in pitch) points inside a passage, and 14 × 33 points downstream exit plane. The measurements are obtained with a small size five hole probe, and wall static pressure taps. It is observed that the three dimensional flow inside and behind the cascade is characterized, not only by the conventional aspects, such as leading edge horseshoe vortices, passage vortices, trailing edge vortex sheet and corner vortices, but also by two spiral node points, formed from the three dimensional separation lines, on suction surface, and the resulting concentrated vortices.

Copyright © 1991 by ASME
This article is only available in the PDF format.

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