冲压基旋转爆震波与来流相互作用机理研究

Continuous rotating detonation ramjet engine (CRDR) could operate continuously with just one initiation, producing a roughly stable thrust. It would be an ideal thrustor for the hypersonic vehicle, having huge potential benefits. The CRDR has a very simple structure, usually consisting of an inlet, an isolator, a detonation combustor and a nozzle. Due to the high combustion speed of detonation wave, the released heat concentrates to a very small area. Then the combustor pressure of CRDR is very high, and the air inflow process will be influenced, which will have an effect on the fuel injection and mixing process. And finally the rotating detonation combustion process will be influenced. Using a combination of experimental observation, numerical simulation and theoretical analysis, the present study will focus on three aspects, which are ramjet based rotating detonation combustion process, isolator flow process with rotating back pressure and fuel injection and mixing process with rotating back pressure. The research results will help to reveal the interaction mechanism between the rotating detonation wave and air inflow, and could also provide a technical support for the CRDR development.

连续旋转爆震冲压发动机（CRDR）只需一次点火即可连续工作，能够提供稳定的推力，可作为高超声速飞行器的理想动力装置，具有广阔的应用前景。CRDR结构简单，一般由进气道、隔离段、爆震室和尾喷管组成。由于爆震燃烧速度快、释热位置集中，产生的高压易对来流造成影响；而来流状态的变化会影响到燃料喷注混合效果，最终又会对旋转爆震燃烧过程产生影响。本项目拟采用试验观测、数值模拟、理论分析等手段，开展冲压基旋转爆震燃烧、旋转反压作用下隔离段流动过程、旋转反压作用下燃料喷注混合过程三方面研究，以揭示旋转爆震与来流间的耦合机制，研究成果可为CRDR研制提供技术支撑。

连续旋转爆震冲压发动机（CRDR）只需一次点火即可连续工作，能够提供稳定的推力，可作为高超声速飞行器的理想动力装置，具有广阔的应用前景。CRDR结构简单，一般由进气道、隔离段、爆震室和尾喷管组成。由于爆震燃烧速度快、释热位置集中，产生的高压易对来流造成影响；而来流状态的变化会影响到燃料喷注混合效果，最终又会对旋转爆震燃烧过程产生影响。本项目采用试验观测和数值模拟相结合的手段，开展了冲压基旋转爆震燃烧、旋转反压作用下隔离段流动过程、旋转反压作用下燃料喷注混合过程的研究，分析了燃烧室和隔离段内的流场结构，总结了隔离段反压对燃料喷注混合的促进作用，揭示了旋转爆震与来流间的耦合机制，研究成果可为CRDR研制提供技术支撑。