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<p>This paper introduces a configuration of a Turbine-Based Bypass Detonation Combined (TBDC) engine, where rotating detonation combustion chamber (RDC) is arranged in parallel on the outer side of a turbojet engine. In this configuration, the air supply for the RDC is derived from the air bled after the compressor, directly avoiding the coupling issue between the RDC and the turbine. Based on the proposed configuration, a simulation model for the overall performance of the TBDC is established. According to certain requirements, the overall performance cycle parameters of the TBDC were optimized using the NSGA-II, leading to an overall performance scheme (<i>π</i><sub>c</sub>=6.747, <i>T</i><Stack> <sub>4.1</sub> <sup>*</sup> </Stack> =1300 K, <i>T</i><Stack> <sub>4.2</sub> <sup>*</sup> </Stack> =2200 K, <i>π</i><sub>D</sub>=1.3, <i>S</i><sub>f</sub>=0.137). The specific TBDC engine based on this overall performance scheme was designed, and integration of the whole engine as well as verification of its overall performance was conducted. Comparison between the model and experimental data revealed a relative error of less than 5%. Finally, a thrust performance analysis was conducted, revealing that the instantaneous maximum thrust of the TBDC reached 6000.5 N, with a thrust gain of 611.3 N compared to a turbojet engine of the same parameters without air bleeding. Furthermore, as the equivalent ratio of reactants and the engine speed increase, the thrust of the TBDC continues to rise, with the effect of speed changes on thrust being more significant.</p>

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Overall Performance Optimization of Turbine-Based Bypass Detonation Combined Engine and Thrust Analysis of Whole Engine Testing

  • 期刊论文

  • 发表日期：

    2026年3月11日

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  • Wenwen Wang,
  • Kun Zhang,
  • Jianbo Gong,
  • Guangwei Yang,
  • Dan Li,
  • Xin’gen Lu

摘要

This paper introduces a configuration of a Turbine-Based Bypass Detonation Combined (TBDC) engine, where rotating detonation combustion chamber (RDC) is arranged in parallel on the outer side of a turbojet engine. In this configuration, the air supply for the RDC is derived from the air bled after the compressor, directly avoiding the coupling issue between the RDC and the turbine. Based on the proposed configuration, a simulation model for the overall performance of the TBDC is established. According to certain requirements, the overall performance cycle parameters of the TBDC were optimized using the NSGA-II, leading to an overall performance scheme (πc=6.747, T 4.1 * =1300 K, T 4.2 * =2200 K, πD=1.3, Sf=0.137). The specific TBDC engine based on this overall performance scheme was designed, and integration of the whole engine as well as verification of its overall performance was conducted. Comparison between the model and experimental data revealed a relative error of less than 5%. Finally, a thrust performance analysis was conducted, revealing that the instantaneous maximum thrust of the TBDC reached 6000.5 N, with a thrust gain of 611.3 N compared to a turbojet engine of the same parameters without air bleeding. Furthermore, as the equivalent ratio of reactants and the engine speed increase, the thrust of the TBDC continues to rise, with the effect of speed changes on thrust being more significant.