固体燃气涡轮火箭发动机燃烧组织优化研究  

Study on optimization of combustion technology in solid propellant air turbo rocket

作　　者：李江[1] 王伟[1] 刘洋[1] 刘诗昌[1] 杨昀[1] 杨飒[1] 

机构地区：[1]西北工业大学燃烧、热结构和内流场重点实验室,西安710072

出　　处：《固体火箭技术》2013年第4期462-467,共6页Journal of Solid Rocket Technology

摘　　要：为探索固体燃气涡轮火箭发动机(SP-ATR)较优燃烧组织方式,在分析地面直连实验补燃室二次燃烧问题,利用地面直连实验结果进行数值方法精度校核后,开展了典型工况下适宜燃烧组织方式初选。在此基础上,选择了一种基于替代模型的渐进优化方法,获得了改进V型掺混器的较优构型。结果表明,建立数值方法可反映流道内真实流动状态;V型掺混器结构较为适宜;文中确定的渐进优化方法稳定可靠,获得的掺混器优化构型性能较理想,比冲较直接掺混方式增加约13.50%;现有圆孔、六叶花2种形式掺混器的结构不合理。The computing method, which combines the results of the ground direct-connect experiments of solid propellant air turbo rocket （SP-ATR）, was established to analyze the uniguited problems in the secondary chamber, moreover, the numerical studies of different combustion technologies under typical operation modes were performed. A successive optimization method based on surrogate models was developed for V-shape optimization in order to achieve optimal configuration. The results show that it is clearly appropriate to adopt such a numerical method to obtain parameters of SP-ATR, and V-shape is an optimum configuration to achieve better performance. The optimization arithmetic base on the surrogate models is reliable and stable. In addition, the optimi- zation configuration has perfect performance and the specific impulse increases by 13.5% compared to the benchmark ease. The ir- rationality of two existing configurations were demonstrated.

关 键 词：优化 燃烧组织 固体燃气涡轮火箭发动机 数值方法 替代模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]