液体火箭发动机碳/碳复合材料喷管烧蚀分析

Recession Analysis of CarbonCarbon CompositeNozzle of Liquid Propellant Rocket Engine

对液体火箭发动机碳／碳复合材料喷管的烧蚀过程进行研究。理论模型包括固相和气相守恒方程。气相湍流反应边界层流动应用质量加权平均控制方程分析，喷管壁温分布由非稳态传热方程进行数值计算获得。分析了推进剂混合比、液膜冷却量、燃烧室压力、壁面材料的密度对烧蚀速率的影响。

The recession process of C/C nozzle of liquid propellant rocket engine is studied. The analytical model consists of both solidphase and gasphase conservation equations. The gasphase turbulent reactive flow of boundary layer is analyzed with the Favreaveraged equations to account for variable density effects. The unsteady heat conduction equation is used to obtain the temperature distribution of the nozzle wall with the numerical computation. The effects of mixture ratio, film cooling, chamber pressure and the density of the nozzle material on the recession rate are discussed.