小推力双组元火箭发动机中壁面液膜数值模拟

Numerical Simulation of Wall Liquid Film in Small Bipropellant Rocket Engine

在航天推进器中,推进剂在燃烧室内的气液两相流动与燃烧过程直接关系到燃烧性能和冷却性能的好坏,对推进器的整体性能具有重要影响.对小推力甲基肼/四氧化二氮双组元液体火箭推力室内液体推进剂在壁面液膜的形成和发展进行了数值计算.结果表明,液膜对燃烧室壁面起到了很好的冷却作用,液膜向前后两个方向发展,在2.0,ms内液膜质量和厚度达到最大值,随着燃烧室内温度的升高,液膜厚度和质量呈现震荡下降.

In aerospace propeller,the gas-liquid two-phase flow and combustion processes in the combustionchamber are directly related to the combustion and cooling performance,both of which have an important influenceon the performance of the thruster.In this paper,the formation and development of wall film in monomethylhydrazineand nitrogen tetroxide(MMH/NTO)bipropellant liquid rocket thrust chamber were calculatednumerically,and the results show that the liquid film has a good cooling effect on the wall of combustion chamberand develops in both forward and backward directions along the wall.The mass and thickness of the liquid filmreach the maximum values in2,ms.With the increase of the temperature in the combustion chamber,the filmthickness and quality fall turbulently.