Volume 37 Issue 1
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HU Jiaying, WANG Zhenguo, PAN Yu, LI Peibo. Flow channel scheme of U-shaped cooling channel in scramjet[J]. Journal of Aerospace Power, 2022, 37(1): 11-25. doi: 10.13224/j.cnki.jasp.20210242
Citation: HU Jiaying, WANG Zhenguo, PAN Yu, LI Peibo. Flow channel scheme of U-shaped cooling channel in scramjet[J]. Journal of Aerospace Power, 2022, 37(1): 11-25. doi: 10.13224/j.cnki.jasp.20210242
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Flow channel scheme of U-shaped cooling channel in scramjet

doi: 10.13224/j.cnki.jasp.20210242

  • College of Aerospace Science and Engineering，National University of Defense Technology，Changsha 410073，China

  • Received Date: 2021-05-14
  • Publish Date: 2022-01-28
    Abstract
  • Three-dimensional simulation of different channel schemes of four channel U-shaped channel plate were conducted.The two configurations of U-shaped channel plate with the same direction inlet/the reverse direction inlet were mainly studied，and the cooling effects of different entrance and exit schemes in each configuration were also discussed and compared.The results showed that the channel scheme with alternate inlet arrangement of the two configurations was more suitable for the regular non-uniform heat flow，the channel scheme with the inlet channel located on both sides of the plate of the two configurations was more suitable for relatively uniform heat flow environment.In the U-shaped channel，the temperature difference between the adjacent channels was large，accompanied by strong heat transfer between the channels，and the lower temperature coolant channel can absorb more heat flow from the combustion chamber wall，which can significantly reduce the cooling burden of the adjacent high temperature channels.

     

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