不同燃烧室结构下的碳/空气两相旋转爆轰发动机数值研究

Solid-gas two-phase rotating detonation engines have been widely studied, which may be expected to improve the propulsive performance of solid ramjets, but experimental limitations have prevented the full information of the particle distribution and flow field from being revealed. This paper conducts a three-dimensional numerical study on annular and hollow combustors at different equivalence ratios, using carbon/air as the propellant at room temperatures. The laminar finite rate reaction model and the multiple surface reaction model are used for the gaseous chemical reaction and the carbon combustion, respectively. The particle diameter is 1 µm. The results show that the number of incompletely burned particles is larger in the hollow combustor, the contact surface is uneven and there is a lack of the low temperature strip behind detonation waves. The annular combustor forms new detonation waves by colliding of detonation waves with the combustor wall, whereas the hollow combustor forms new detonation waves through the high-pressure area generated by shockwave collisions downstream of the combustor. Compared with the annular combustor, the hollow combustor has lower detonation pressure of detonation wave and combustion efficiency of the particles. In the same fuel and air mass flow rate conditions, the engine thrust is lower and more unstable in the hollow combustor.