Volume 31 Issue 10
Oct.  2016
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Article Navigation >  Journal of Aerospace Power  > 2016  >  31(10): 2454-2463
ZHAO Lin, XU Jing-lei, QIU Yun, ZHAO Lei, GUO Xiao-shun. Numerical simulation of film-cooling for the adjustable nozzle of the tandem TBCC[J]. Journal of Aerospace Power, 2016, 31(10): 2454-2463. doi: 10.13224/j.cnki.jasp.2016.10.019
Citation: ZHAO Lin, XU Jing-lei, QIU Yun, ZHAO Lei, GUO Xiao-shun. Numerical simulation of film-cooling for the adjustable nozzle of the tandem TBCC[J]. Journal of Aerospace Power, 2016, 31(10): 2454-2463. doi: 10.13224/j.cnki.jasp.2016.10.019
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Numerical simulation of film-cooling for the adjustable nozzle of the tandem TBCC

doi: 10.13224/j.cnki.jasp.2016.10.019

  • 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 2. The 31st Institute of the 3rd Research Academy, China Aerospace Science and Industry Corporation, Beijing 100074, China

  • Received Date: 2015-01-15
  • Publish Date: 2016-10-28
    Abstract
  • In view of the problem that the higher inlet total temperature of tandem TBCC nozzle can reduce the ablation of the wall material, a film-cooling scheme adapted to different flight Mach numbers in the flight envelope was presented, showing a significant effect on the thermal protection of the nozzle. The cooling effect for different flight Mach numbers based on the CFD method was calculated. The research indicates that there will be a more noticeable change of the flow field conditions nearby the rhomboid slots than annular slots. After film-cooling, the temperature of nozzle has a 1000K's decline than before. The film-cooling adiabatic efficiency of the downstream wall centerline can reach to 0.9 at most flight Mach numbers. The downstream wall temperature of the slot is mainly distributed symmetrically along the span of the nozzle, and the temperature uniformity gradually declines with x's increment.

     

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