扰流环对粉末发动机燃烧流动影响的数值模拟

为了提高粉末火箭发动机的燃烧效率,通过数值模拟方法研究了扰流环的有无、通径及位置对燃烧室燃烧流动特性的影响。结果表明:扰流环会增强Al颗粒和气相的掺混和换热程度,促进Al颗粒蒸发和燃烧,从而提高粉末火箭发动机的燃烧效率。当扰流环通径比在0.538~0.846范围内时,扰流环的通径越小,燃烧效率越高;当扰流环头部距离比在0.3~0.8范围内时,扰流环位置离头部越近,燃烧效率越高。设计扰流环时,应在距离燃烧室头部30%~40%的位置布置小通径的扰流环。 

Numerical simulation of spoiler ring’s effect on combustion and flow of powdered rocket motor

In order to improve the combustion efficiency of powdered rocket motor, the effects of spoiler ring’s existence, flowing diameter and position on the combustion and flow characteristics in the chamber were studied by numerical simulation. Result showed that the spoiler ring can increase mixing and heat transfer intensity between particle and gas species, and improve the evaporation and combustion of Al particle, which resulting in the increase of combustion efficiency of the powdered rocket motor. When the ratio of spoiler ring flowing diameter to the combustion chamber diameter was between 0.538 and 0.846, the combustion efficiency increased with the reducing flowing diameter of spoiler ring. When the ratio of spoiler ring’s distance from the chamber’s head position to the chamber’s total length was between 0.3 and 0.8, the combustion efficiency increased as the spoiler ring moved toward the chamber’s head. The spoiler ring with small flowing diameter and distance from the head between 30% and 40% of the chamber length could be better for the spoiler ring design of powdered rocket motor.