Propagation Mode of Detonation Wave in a Plane-Radial Rotating Detonation Combustion Chamber

被引:0
作者
Shen W.-B.-Y. [1 ]
Huang Y. [1 ]
You Y.-C. [1 ]
Huang H.-T. [1 ]
机构
[1] School of Aerospace Engineering, Xiamen University, Xiamen
来源
Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 04期
关键词
Combustion chamber; Inlet and outer diameter ratio; Numerical simulation; Propagation mode; Radial length; Rotating detonation;
D O I
10.13675/j.cnki.tjjs.200503
中图分类号
学科分类号
摘要
In order to study the propagation characteristics of the rotating detonation wave in a plane-radial rotating detonation combustor, Euler equation with 14 species-19 reactions methane/oxygen reaction mechanism were solved. Numerical simulations were conducted to study the effects of injection temperature, pressure, inlet and outer diameter ratio and radial length on the rotating detonation wave propagation mode. The results show that a continuous rotating detonation wave is formed in the fixed combustion chamber with the pre-mixed injection temperature of 500~900K and the injection pressure of 0.5~3.5MPa. With the effect of the combustor structure, propagation modes of rotating detonation waves are divided into stable mode and unstable mode. The entire unstable propagation mode can be divided into two stages based on the interference of the detonation wave to the previous period: the interference stage and the non-interference stage. In the non-interference stage, the propagation speed of the detonation wave is higher than the C-J (Chapman-Jouguet) speed. In the interference stage, the propagation speed of the detonation wave is lower than the C-J speed, and the detonation wave is divided into two parts by the discontinuous surface. The propagation speed of the detonation wave in the stable mode is higher than that in the unstable mode, while the angle of detonation wave and combustor outlet area ratio are reversed. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码:865 / 873
页数:8
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