高低燃温组合推进剂下喷管壁面温度边界层影响规律

Temperature Boundary Layer in Nozzle Wall with High and Low Burning Temperature Combined Propellant

为了获得高低燃温组合推进剂下喷管温度边界层的影响规律,建立了四个物理模型,通过使用不同的低燃温推进剂、不同的质量分数来分析低燃温燃气对喷管温度边界层的影响。结果显示,在靠近喷管喉衬位置喷入低燃温燃气时,仅需少量低燃温推进剂就能很好的降低喷管表面边界层的温度;而在远离喷管喉衬部位时,即使使用较大的质量分数,喷管边界层的降温效果也不明显。喷管温度边界层的降低受低燃温燃气温度、质量分数、低燃温燃气进口位置以及进口直径影响。

In order to obtain the law of temperature boundary layer in nozzle wall with high and low burning temperature combined propel -lant, four physical models were put forward in this paper .Different low burning temperature propellant and mass fraction were used to ana-lyze the influence of low temperature gas on temperature boundary layer of nozzle wall .The calculation result shows that just a little mass of low burning temperature propellant can effectively reduce the temperature of nozzle wall when the low temperature gas is injected close to the nozzle throat .The effect is not obvious when the injecting position is far away form the nozzle throat .There is close relationship between reduction of temperature in nozzle wall and these factors which include temperature of low burning temperature propellant gas , mass frac-tion, the location of injecting inlet and injecting inlet diameter .