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为深入认识再生式液体发射药火炮(RLPG)喷雾燃烧过程和研究压力振荡现象,应用多维多相流模型描述RLPG膛内流动过程,用欧拉法描述气相流场,用拉格朗日方法描述液滴运动,液滴燃烧遵循压力指数燃烧规律。采用基于表面波破碎理论和线性稳定性分析的高速液体薄膜破碎模型描述RLPG环形射流的雾化过程。采用MacCormack差分格式求解气相控制方程,仿真结果与试验值吻合较好。结果表明:燃烧室存在高频燃烧不稳定现象,压力振荡主振型为径向二阶振型,弹丸运动主导了流场的形态。
In order to understand the spray combustion process of RLPG and investigate the phenomenon of pressure oscillation, a multi-dimensional multi-phase flow model was used to describe the flow in the RLPG bore, the gas flow field was described by Euler method and the Lagrangian method Droplet movement, droplet burning follow the pressure index burning law. The atomization process of RLPG toroidal jet was described by using a high-speed liquid film fragmentation model based on surface wave breaking theory and linear stability analysis. The MacCormack difference scheme is used to solve the gas phase control equation. The simulation results are in good agreement with the experimental values. The results show that the combustor is unstable in high frequency combustion. The main mode of pressure oscillation is radial second mode, and the projectile movement dominates the shape of the flow field.