Application of Detonation Waves to Rocket Engine Chamber
Application of Detonation Waves to Rocket Engine Chamber
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爆震波在火箭发动机舱中的应用
DOI：
10.1007/978-3-319-68906-7_4
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发表时间：
2018
影响因子：
1.6
通讯作者：
N. Tanatsugu
中科院分区：
文献类型：
--
作者：
J. Kasahara;Y. Kato;K. Ishihara;Keisuke Goto;K. Matsuoka;A. Matsuo;I. Funaki;H. Moriai;D. Nakata;K. Higashino;N. Tanatsugu
我们展示了使用旋转爆震发动机进行的实验结果，该发动机使用环形燃烧室中的连续爆震来产生推力。爆震波在超音速且非常小的区域中传播，从而可以缩短燃烧室。 RDE的燃烧室在喷射推进剂时会产生高压损失，并且由于高热通量而需要冷却。然而，环形燃烧室中爆震燃烧的燃烧效率是最重要的，但尚未得到充分阐明。此外，喷射器形状和旋转爆震燃烧室直接冷却的影响需要澄清。本文报告了燃烧室停滞压力和推力的测量结果、喷射器形状对 c* 效率的影响以及热通量的估计。当我们使用收敛或收敛-扩散喷嘴且当量比小于1.0时，c*效率为88-100%。喷射器的形状影响波传播模式，但该模式不会改变 c* 效率。我们根据终端温度估算了时空平均热通量，无注水条件下的热通量为8.1 ± 1.8 MW/m2。火箭RDE滑橇测试成功进行。火箭RDE系统总质量为58.3 kg，总时均推力为201 N，时均质量流量为143 g/s，比冲为144 s。
We present the results of experiments performed with a rotating detonation engine using continuous detonation in an annular combustor to create thrust. Detonation waves propagate in a supersonic and very small region, allowing shortening of the combustor. The combustor of RDE causes high-pressure loss when the propellant is injected, and cooling is necessary due to high heat flux. However, the combustion efficiency of detonation combustion in an annular combustor is the most important, but have not been fully elucidated. In addition, the influence of the injector shape and direct cooling of a rotating detonation combustor require clarification. This paper reports the measurement results of combustor stagnation pressure and thrust, the influence of injector shape on c* efficiency, and the estimate of heat flux. The c* efficiency was 88–100% when we used the convergent or convergent-divergent nozzle and the equivalence ratio was less than 1.0. The shape of the injector influenced wave propagation mode, but the mode did not change the c* efficiency. We estimated time-spatial average heat flux from the terminal temperature, and the heat flux was 8.1 ± 1.8 MW/m2 in no water injection condition. The rocket RDE sled test was successfully performed. The total mass of the rocket RDE system was 58.3 kg, total time averaged thrust was 201 N, the time averaged mass flow rate was 143 g/s, and the specific impulse was 144 s.