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Secondary Flow and its Contribution to Heat Transfer Enhancement in a Blade Cooling Passage With Discrete Ribs FREE

[+] Author Affiliations
Zhengjun Hu, Jiarui Shen

Chinese Academy of Sciences, Beijing, China

Paper No. 96-GT-313, pp. V004T09A039; 6 pages
doi:10.1115/96-GT-313
From:
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Birmingham, UK, June 10–13, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7875-0
  • Copyright © 1996 by ASME

abstract

A detailed map of heat transfer coefficients has been measured in a converging blade cooling passage with 45 deg. discrete ribs on two opposite walls for a range of engine representative Re of 10,000 ∼ 50,000. Flow visualization showed that there were four different types of secondary flow created by the discrete ribs: skewed boundary layer, secondary flow in front of the rib, secondary flow behind the rib, swirling longitudinal vortex flow and for large rib heights there were vortex streets. The origin of these secondary flows and their structure are discussed together with their contribution to the local enhancement of heat transfer. The results were used to understand the mechanism of heat transfer enhancement using secondary flow created by rib turbulators and from this to develop new design methods for improved enhanced heat transfer.

Copyright © 1996 by ASME
This article is only available in the PDF format.

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