采用CFD数值仿真研究固体火箭冲压发动机补燃室长度对其燃烧和流动的影响。仿真结果表明,补燃室中的损失主要是掺混损失和流动损失,当补燃室长径比较小(l/d<11.0)的时候掺混燃烧损失较大,补燃室出口温度均匀度较低,整个发动机性能不高。随着补燃室长度增大掺混燃烧逐渐均匀整个发动机性能达到最大,随着补燃室长度进一步增加,流动损失增大,发动机性能有所下降。同时增加补燃室长度可以得到均匀的补燃室出口流场,进而使发动机喷管的损失有所降低。

The combustion and flow performance in solid rocket ramjet's afterburning chambers were analyzed by CFD numerical simulation. The loss of afterburning chamber composes of adulteration loss and flow loss. The adulteration loss is on dominant when the afterburning chamber's aspect ratio is small (l/d <11), and the temperature uniformity of the outlet of afterburning chamber is low, so the performance of solid rocket ramjet is lower. With the length of the afterburning chamber increasing, the outlet flow condition of the afterburning chamber becomes more uniform, and the performance of the solid rocket ramjet gets tiptop. While, if the length extended even longer, the performance would be lower because of the flow loss augment. By the way, with the length of the afterburning chamber increasing, the flow performance of the nozzle of solid rocket ramjet would be in better condition as the flow condition is more uniform.