Volume 30 Issue 1
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Article Navigation >  Journal of Aerospace Power  > 2015  >  30(1): 16-21
HE Xiao-min, QIN Wei-lin, ZHU Zhi-xin, NIU Zhi-gang, FEI Li-qun, PENG Li, YANG Cheng-yu. Experiment on combustion performance of ramjet engine withtrapped-vortex combustor[J]. Journal of Aerospace Power, 2015, 30(1): 16-21. doi: 10.13224/j.cnki.jasp.2015.01.003
Citation: HE Xiao-min, QIN Wei-lin, ZHU Zhi-xin, NIU Zhi-gang, FEI Li-qun, PENG Li, YANG Cheng-yu. Experiment on combustion performance of ramjet engine withtrapped-vortex combustor[J]. Journal of Aerospace Power, 2015, 30(1): 16-21. doi: 10.13224/j.cnki.jasp.2015.01.003
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Experiment on combustion performance of ramjet engine withtrapped-vortex combustor

doi: 10.13224/j.cnki.jasp.2015.01.003

  • 1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 2. Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China

  • Received Date: 2013-09-09
  • Publish Date: 2015-01-28
    Abstract
  • Experiments were conducted to study the combustion performance of ramjet engine model with trapped-vortex combustor under different inlet temperatures and velocity coefficients. The results show: with the increase of inlet velocity coefficient increases (0.20-0.35), the ignition and lean blowout fuel air ratios rise, and the combustion efficiency changes little. As the inlet temperature increases(573-773K), the ignition fuel air ratio and lean blowout fuel air ratio decreases, and the combustion efficiency increases varying with increase of the excess air coefficient(1.1-2.1). The minimum ignition fuel air ratio and the lean blowout fuel air ratio is 0.0035 and 0.0028 respectively, the maximum combustion efficiency obtained from experiment is 93%.The results prove the feasibility of applying the cavity to the ramjet combustor.

     

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