高低燃温组合推进剂下喷管壁面温度边界层影响规律

发布时间：2019-01-21 18:10

【摘要】：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。
[Abstract]:In order to obtain the influence law of the lower nozzle temperature boundary layer of low and low temperature combined propellant, four physical models were established, and different low burning temperature propellants were used. The effect of low temperature gas on the boundary layer of nozzle temperature is analyzed with different mass fraction. The results show that the temperature of the boundary layer on the surface of the nozzle can be reduced very well if only a small amount of low burning temperature propellant is needed when the gas is injected near the nozzle throat liner. The cooling effect of the nozzle boundary layer is not obvious even when the nozzle is far away from the nozzle throat liner even if the mass fraction of the nozzle is high. The decrease of nozzle temperature boundary layer is affected by low temperature gas temperature, mass fraction, inlet position and inlet diameter.
【作者单位】：中国航天科技集团第四研究院第41研究所;
【分类号】：V435

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