Volume 40 Issue 1
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JIANG Yuguang, QI Yongjian, DUAN Yanjuan, et al. Effect of cooling flow deviation on flight velocity region of scramjet[J]. Journal of Aerospace Power, 2025, 40（1）：20230107 doi: 10.13224/j.cnki.jasp.20230107
Citation: JIANG Yuguang, QI Yongjian, DUAN Yanjuan, et al. Effect of cooling flow deviation on flight velocity region of scramjet[J]. Journal of Aerospace Power, 2025, 40（1）：20230107 doi: 10.13224/j.cnki.jasp.20230107
shu

Effect of cooling flow deviation on flight velocity region of scramjet

doi: 10.13224/j.cnki.jasp.20230107
  • 1.

    School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

  • 2.

    National Key Laboratory of Solid Rocket Propulsion，The Institute of Xi’an Aerospace Solid Propulsion Technology，Xi’an 710025，China

  • 3.

    School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China

  • Received Date: 2023-02-27
    Available Online: 2024-06-03
    Abstract

  • The influence of hydrocarbon fuel flow deviation on the allowable Mach number upper limit of scramjet was focused and researched. A quasi-one-dimensional coupling model of combustion and cooling was established and verified as an overall analysis tool. The simulation results showed that the working range of scramjet was seriously affected by the flow deviation. Taking the flow deviation $ \,\beta $=−0.5 as an example, the flow deviation lowered the upper limit of the engine flight Mach number from Ma=6 to Ma=5, indicating that the flow deviation seriously restrained the safe operating speed range of the engine and affected the flight mission. The influencing mechanism of different combustion and cooling designs on the upper Mach number limit was compared and analyzed, such as counter flow cooling, multi-stage fuel injection, flow deviation initial position, and maximum wall/fuel temperature. The flow deviation was suppressed and the flight Mach number range was broadened. Finally, based on the experimental data of the cascade-throttle flow deviation suppression method, the upper flight Mach number limit of the engine was extended by 1 Mach number.

     

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