旋转管状装药固体火箭发动机燃烧室流动特征

Exhaust Gas Flow in Combustion Chamber of Spinning Inner-burning Tube SRM

采用RSM湍流模型计算了某管状装药旋转固体火箭发动机在不同转速情况下燃烧室-喷管统一流场,分析了不同转速情况下燃烧室燃气流动特点,得到了燃烧室内旋流速度分布趋势以及涡核半径在不同转速情况下的变化规律,分析了燃烧室前封头处局部区域的流场结构,结果表明燃烧室内燃气切向速度分布类似于Rankine组合涡分布;旋涡涡核半径最小处在前封头临近区域;发动机转速增大,发动机内形成"准固体"区,其旋转角速度远大于发动机旋转角速度.

The RSM turbulent model was adopted to calculate the united flow field in a rocket motor with inner-burning tube solid propellant in the condition of different rotate speed. The characteristic of exhaust gas flow varied with rotational speed in the chamber was analyzed. The tangential velocity distribution of the swirling flow and the changing characteristics of swirl core size were obtained, and the flow field configuration close-by front blockage in the chamber was also analyzed. The results show that the tangential velocity distribution is similar to Rankine combination swirl, the minimum rotational swirl core radius is near to the front blockage, and with the increase of motor rotational speed, the ＂quasi-solid＂ area is formed, and its rotational angle velocity is much larger than that of motor.