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Experimental Study and Vortex Analysis in a Linear Compressor Cascade With Active Flow Control

[+] Author Affiliations
Simeng Tian, Yangyang Wu, Zhibo Zhang, Bangqin Cheng, Yinghong Li

Air Force Engineering University, Xi’an, China

Yun Wu

Xi’an Jiaotong University, Xi’an, China

Paper No. GT2016-57276, pp. V02AT37A034; 9 pages
doi:10.1115/GT2016-57276
From:
  • ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
  • Volume 2A: Turbomachinery
  • Seoul, South Korea, June 13–17, 2016
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4969-9
  • Copyright © 2016 by ASME

abstract

In this paper, experimental investigations of a linear compressor cascade have been performed with Reynolds number of 2.4×105 to analyze the flow mechanism of hub-corner separation with end-wall jet and suction control. The vortices are measured with a quasi-three dimensional test system in different axial planes consisting of vorticity distribution and secondary flow structure. The experimental results give detailed insight into the performance of the principle vortices with different flow control methods. Corner separation losses could remarkably decrease with the jets and suction position near the asymptotic line of separation lines on suction surface. The flow control position plays a great role in affecting the corner separation losses while it is a more sensitive factor in the case of jets rather than the suction. It is evidenced that the combined flow control would get a higher decrease in the total pressure loss coefficient while an additional benefit in the reduction of losses has been gained in the case of a combined actuator layout.

Copyright © 2016 by ASME

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