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Experimental study of mode transition characteristics of a cavity-based scramjet combustor during acceleration

机译：腔内超燃燃烧器加速过程中模式转变特性的实验研究

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Experiments were performed in a direct-connect supersonic combustion test facility to simulate scramjet combustor acceleration in high altitude. The combustor inlet flow Mach number increased from 2.40 to 2.94, and the flowrate and total temperature simultaneously changed with Ma. The combustor has two cavities and fuel jets. The fuel used is room-temperature liquid kerosene RP3. Mode transition is seen to occur in the first cavity during acceleration, and pressure fluctuations occur in the transitions from both the ram mode to the transition mode and from the transition mode to the scram mode, indicating that the mode transition process is unstable. When the mode transition occurs upstream, the downstream ram mode has the effect of eliminating instability: therefore, the engine's overall thrust performance is stable. When the downstream is also in the transition mode, the thrust fluctuates, indicating that the mode transition is an unstable process. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：在直接连接的超音速燃烧测试设备中进行了实验，以模拟高空超燃冲压发动机燃烧室的加速。燃烧器入口流量马赫数从2.40增加到2.94，并且流量和总温度随Ma同时变化。燃烧室有两个空腔和燃料喷嘴。所使用的燃料是室温液态煤油RP3。可以看出，在加速过程中在第一腔中发生了模式转换，并且在从冲压模式到转换模式以及从转换模式到超燃模式的转换中都出现了压力波动，这表明模式转换过程是不稳定的。当模式转换发生在上游时，下游冲压模式具有消除不稳定性的作用：因此，发动机的整体推力性能稳定。当下游也处于过渡模式时，推力会波动，表明模式过渡是一个不稳定的过程。 （C）2019 Elsevier Masson SAS。版权所有。

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