Volume 39 Issue 5
Jan.  2024
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HUA Yuanfan, LI Shipeng, WANG Ningfei, et al. Influence of injection position on combustion of multi-component fuel scramjet[J]. Journal of Aerospace Power, 2024, 39(5):20210569 doi: 10.13224/j.cnki.jasp.20210569
Citation: HUA Yuanfan, LI Shipeng, WANG Ningfei, et al. Influence of injection position on combustion of multi-component fuel scramjet[J]. Journal of Aerospace Power, 2024, 39(5):20210569 doi: 10.13224/j.cnki.jasp.20210569

Influence of injection position on combustion of multi-component fuel scramjet

doi: 10.13224/j.cnki.jasp.20210569
  • Received Date: 2021-10-09
    Available Online: 2023-12-22
  • In order to investigate the details of the combustion organization of aluminum-containing high-energy-density hydrocarbon fuels in scramjet engine, a discrete phase model (DPM) and simplified reaction mechanism were used to numerically simulate the combustion flow process at different fuel injection positions. The results showed that when the seven injectors were used to inject fuel from the upper wall, the exit section formed a temperature distribution near the center of the upper wall from inside to outside, namely, relatively low temperature-warming-up to the highest temperature-cooling down. The lower oxygen concentration of the upper wall near the center area affected the progress of the reaction. Under the research conditions, as the distance between the injector and the inlet of the combustion chamber increased, the fuel specific impulse first increased and then decreased. In the research condition, the maximum specific impulse of fuel was 11092 m/s. The performance of the combustion chamber can be improved by changing the injection position of the fuel injected into the combustion chamber from the upper wall and optimizing the injector layout. After optimization, the maximum specific impulse increased by 12.68%.

     

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