Supersonic combustion induced by reflective shuttling shock wave in fan-shaped two-dimensional combustor
Supersonic combustion induced by reflective shuttling shock wave in fan-shaped two-dimensional combustor
复制标题
扇形二维燃烧室反射穿梭激波诱发超音速燃烧
DOI：
10.1016/j.proci.2018.06.210
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发表时间：
2019
影响因子：
3.4
通讯作者：
A. Matsuo
中科院分区：
文献类型：
--
作者：
M. Yamaguchi;K. Matsuoka;A. Kawasaki;J. Kasahara;H. Watanabe;A. Matsuo
作为一种区别于脉冲爆震发动机和旋转爆震发动机的新型爆震燃烧器，提出了一种爆震波在爆震燃烧器中反复穿梭的反射式穿梭爆震燃烧器（RSDC）。在扇形二维燃烧室中，爆震波传播，反复衰减和侧壁处的激波反射重燃。在演示实验中，同时进行了化学发光可视化和乙烯-氧气混合气体压力测量。结果表明，在燃烧室中观察到了与压力上升耦合的单一梭动波。波的切向速度为1526 ± 12 m/s，约为估计的Chapman-Jouguet速度2513 m/s的60%。波前压力与主波或反射波后压力之比符合一维激波理论，表明反射激波后的快速反应维持了激波的连续传播。
As a novel detonation combustor that differs from a pulse and a rotating detonation engine, a reflective shuttling detonation combustor (RSDC), in which detonation waves shuttle repeatedly, was proposed. In a fan-shaped two-dimensional combustor, detonation waves propagate, repeating attenuation and re-ignition by a shock reflection at the side wall. In the demonstration experiment, chemiluminescence visualization and pressure measurement with ethylene–oxygen mixture were conducted at the same time. As the result, a single shuttling wave coupled with pressure rise was observed in the combustor. The tangential velocity of the wave was 1526 ± 12 m/s and approximately 60% of the estimated Chapman–Jouguet velocity of 2513 m/s. The ratio of pressure in front of the wave to one behind the primary wave or the reflected wave was in good agreement with one-dimensional shock theory, and it was suggested that the rapid reaction behind the reflected shock wave sustained the continuous propagation of the shock wave.