后置燃气发生器的新型固冲发动机工作过程数值模拟  

Numerical investigation on operation process of solid ducted rocket with postpositional gas generator

作　　者：王云霞[1] 陈林泉[1] 杨向明[1] 张胜勇[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2012年第6期736-741,共6页Journal of Solid Rocket Technology

摘　　要：进行了后置燃气发生器的新型固体火箭冲压发动机直连式试验,并对实验演示用发动机补燃室三维内流场进行了数值模拟,将试验结果与数值模拟结果进行对比,验证了数值模拟的准确性。采用单因素比较分析的方法,研究了一次燃气喷射方式与补燃室长度对固冲发动机性能的影响。结果表明,一次燃气喷射角度为150°时的燃烧效率比60°时高14%,补燃室燃烧效率在一次燃气喷射角度为180°时达到最大值;8喷口的燃烧效率高于4喷口;补燃室长度增加,燃烧效率增大,补燃室长度为149 mm时的燃烧效率比99 mm仅高5%。Direct-connected test of solid ducted rocket with postpositional gas generator was completed.Numerical investigation on the field of solid ducted rocket secondary chamber was presented.The simulation model was proved by comparing the test and CFD results.Furthermore,the effect of fuel injection style and length of secondary chamber on combustion efficiency was carried out by analysis method of single factor.The numerical results show that the combustion efficiency increases with either the number of fuel-inlet or the length of secondary chamber.In addition,the combustion efficiency was increased by 14 % when the fuel injection angle was equal to 150°,then increased to the maximum while the fuel injection angle was 180°,and the combustion efficiency was increased by only 5% when the length of secondary chamber increased to 149 mm.

关 键 词：固体火箭冲压发动机 后置燃气发生器 直连式试验 燃烧效率 

分 类 号：V448.15[航空宇航科学与技术—飞行器设计]