基于放热分布的RBCC热力喉道研究

发布时间：2018-04-08 11:50

本文选题：火箭基组合循环　切入点：热力喉道　出处：《推进技术》2016年04期

【摘要】：为了更清楚地认识RBCC亚燃模态热力喉道生成机理与规律,通过三维数值模拟,研究了不同燃料喷注位置、凹腔位置、当量比以及火箭流量等影响RBCC燃烧室流道内放热分布的因素,分析了不同放热分布对于热力喉道生成的影响。研究结果表明在放热量足够形成热力喉道的前提下,放热分布相比放热量对热力喉道生成位置的影响更大,并且热力喉道不会形成于主放热区内,提高掺混、增加燃料当量比等使放热量增大的方法会伴随30%~50%的主放热区间长度的增加,对于热力喉道生成位置的影响能力有限。对于RBCC燃烧室,调节火箭流量是一种更有效也更容易实现热力喉道位置宽范围调节的方法,调节范围可以达到燃烧室长度的24%。
[Abstract]:In order to understand more clearly the formation mechanism and law of thermal throttle in RBCC sub-combustion mode, different fuel injection positions and cavity positions were studied by three-dimensional numerical simulation.The influence of equivalent ratio and rocket flow rate on the heat release distribution in the flow channel of RBCC combustor is analyzed, and the influence of different heat release distribution on the formation of thermal throttle is analyzed.The results show that if the heat release is sufficient to form the thermal throat, the heat release distribution has more influence on the position of the thermal throat than the heat release, and the thermal throat will not be formed in the main exothermic zone, and the mixing will be improved.The increase of fuel equivalent ratio and other methods to increase the heat release will be accompanied by an increase in the length of the main exothermic zone of 30 ~ 50%, which has a limited influence on the position of the thermal throat formation.For the RBCC combustor, adjusting the rocket flow rate is a more effective and easy way to realize the wide range adjustment of the thermal throttle position, and the adjustment range can reach 24% of the combustion chamber length.
【作者单位】：西北工业大学航天学院;
【分类号】：V430

【相似文献】