旋转爆震发动机爆震波建立过程实验研究

发布时间：2018-02-03 03:56

本文关键词： 旋转爆震波氢-空气混合 DDT过程小能量点火　出处：《推进技术》2016年10期 　论文类型：期刊论文

【摘要】：为了深入研究旋转爆震发动机爆震波建立过程及形成机理,采用小能量火花单次点火的方式进行了一系列旋转爆震发动机起爆实验。发动机采用环缝-喷孔对撞式掺混方式,燃料为H2,氧化剂为空气,实验成功起爆旋转爆震波,并连续旋转稳定传播,爆震波传播频率为5.09~6.45k Hz,传播速度为1286~1644.8m/s。在发动机稳定工作过程中,集气腔与燃烧室相互影响,二者处于平稳的动态平衡。其次,通过对旋转爆震波起爆过程详细分析发现,点火形成的初始火焰在环形燃烧室经历一个类似DDT的火焰发展过程,成功转变为爆震波,且从点火到爆震波建立之间的火焰发展传播过程和时间间隔均表现出很强的随机性。此外,为验证小能量火花点火的可靠性,还进行了小能量点火重复性实验,发现在稳定工况条件下采用小能量点火成功率最高可达100%,各组旋转爆震波传播速度在1440m/s附近波动。
[Abstract]:In order to study the establishment process and formation mechanism of detonation wave in rotary detonation engine. A series of igniting experiments of rotating detonation engine were carried out by means of single ignition with small energy spark. The engine was mixed with ring slit and injection hole, the fuel was H _ 2 and the oxidant was air. The rotating detonation wave was successfully detonated and propagated steadily and continuously. The propagation frequency of the detonation wave was 5.09 ~ 6.45 kHz. The propagating speed is 1286 ~ 1644.8 m / s. During the steady operation of the engine, the gas collecting chamber and the combustion chamber interact with each other, and they are in a stable dynamic balance. Through the detailed analysis of the initiation process of rotating detonation wave, it is found that the initial flame formed by igniting goes through a flame development process similar to DDT in the annular combustion chamber, which is successfully transformed into a detonation wave. In addition, the flame propagation process and time interval between ignition and detonation wave are very random. In addition, in order to verify the reliability of small energy spark ignition, small energy ignition repeatability experiments are also carried out. It is found that the maximum success rate of ignition with small energy can be up to 100 under steady working conditions, and the propagation velocity of each group of rotating detonation waves fluctuates in the vicinity of 1440m / s.
【作者单位】：南京理工大学机械工程学院;上海航天动力技术研究所;
【分类号】：O354.4
【正文快照】： 1引言基于等压燃烧方式的航空航天发动机技术已经日臻成熟,大幅提高其推进效率已经十分困难。开发适应高速、高效要求的新型发动机成为当今航空航天事业向前推进的迫切需求。与以等压方式的爆燃相比,爆震是接近定容条件下的燃烧,其产生的熵增较小,在相同条件下,具有能量释放率

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