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Three-dimensional numerical thrust performance analysis of hydrogen fuel mixture rotating detonation engine with aerospike nozzle
Proceedings of the Combustion Institute ( IF 5.3 ) Pub Date : 2018-10-02 , DOI: 10.1016/j.proci.2018.09.024
Nicolas Jourdaine , Nobuyuki Tsuboi , Kohei Ozawa , Takayuki Kojima , A. Koichi Hayashi

The propulsive performance for an H2/O2 and H2/Air rotating detonation engine (RDE) with conic aerospike nozzle has been estimated using three-dimensional numerical simulation with detailed chemical reaction model. The present paper provides the evaluation of the specific impulse (Isp), pressure gain and the thrust coefficient for different micro-nozzle stagnation pressures and for two configurations of conic aerospike nozzle, open and choked aerospike. The simulations show that regardless of the nozzle, increase the micro-nozzles stagnation pressure increases the mass flow rate, the pre-detonation gases pressure and consequently the post-detonation pressure. This gain of pressure in the combustion chamber leads to a higher pressure thrust through the nozzle, improving the Isp. It was also found that the choked nozzle increases the chamber time-averaged static pressure by 50–60% compared with the open nozzle, inducing higher performance for the same reason explained before.



中文翻译:

含气尖嘴混合气旋转爆震发动机的三维数值推力性能分析

使用具有详细化学反应模型的三维数值模拟,估算了带有圆锥形气动尖嘴喷嘴的H 2 / O 2和H 2 /空气旋转爆震发动机(RDE)的推进性能。本文提供了对特定冲量(I sp),不同的微喷嘴滞止压力以及圆锥形气钉喷嘴的两种配置(开放式和cho塞式气钉)的压力增益和推力系数。模拟表明,不管喷嘴如何,增加微喷嘴的停滞压力都会增加质量流量,爆炸前的气体压力,从而增加爆炸后的压力。燃烧室中的这种压力增加导致通过喷嘴的压力推力更高,从而改善了I sp。还发现与打开的喷嘴相比,节流的喷嘴将腔室的平均时空压力提高了50-60%,从而产生了更高的性能,原因与之前解释的相同。

更新日期:2018-10-02
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