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Effect of Wake Negative Jet Flow on the Boundary Layer Transition of Compressor Cascade

[+] Author Affiliations
Yangang Wang, Qijie Shao, Wenbing Hu

Northwestern Polytechnical University, Xi’an, China

Paper No. GT2018-76367, pp. V02AT45A020; 8 pages
doi:10.1115/GT2018-76367
From:
  • ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
  • Volume 2A: Turbomachinery
  • Oslo, Norway, June 11–15, 2018
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5099-2
  • Copyright © 2018 by ASME

abstract

The present paper performed a numerical study on a high-loaded and high turning compressor cascade, where the unsteady boundary layer transition behavior on the cascade blade undergoing negative jet flow is revealed. The two-equation SST turbulence model coupled with Langtry-Menter transition model is verified and applied on all the computations in present study. Reynolds number and turbulent intensity are selected as two dominate candidates which can significantly influence the transition behavior and their effect were examined. Results show that under all the tested case (i.e., varying Reynolds number and turbulence intensity), the flow structures on the suction surface of the blade are rolled up when the unsteady negative jet flow directly impacting on the blade. However, the unsteady wake from upstream has not influenced the boundary layer. For high Reynolds number (i.e., Re = 400,000) the rolling up and shed of the boundary layer only occurs at blade trailing edge. The wake is evidenced be able to bring more energy into the boundary layer and thus separation and loss can be significantly decayed and reduced. Moreover, decreasing the turbulent intensity would in practical decay the transition in the boundary layer and therefore make the boundary layer easy to separate.

Copyright © 2018 by ASME

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