超燃冲压发动机地面试验氢燃烧加热器流场数值模拟  

Numerical investigation of hydrogen combustion-heater for scramjet ground test

作　　者：王辽[1] 徐旭[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2008年第8期1397-1402,共6页Journal of Aerospace Power

摘　　要：采用Fluent软件模拟超燃冲压发动机直联式地面试验用燃烧型加热器的内部流场,对设计的氢气多孔喷射和氢气单孔喷射方案分别进行了研究.计算结果表明:加热器出口流场均能满足设计总温为1 900 K,马赫数为1.85的要求,而氢气单孔喷射方案优于氢气多孔喷射方案.计算中也发现了这两种设计方案中存在的不足.Fluent was used to investigate numerically the internal flow field of combustion-heater for direct-connect scramjet ground test facility. The hydrogen multi-hole injection and hydrogen single-hole injection was computed, respectively. The results show that the exit flow field can meet the design requirements of total temperature 1 900 K, Ma= 1.85, and the hydrogen single hole injection is superior to hydrogen multi-hole injection. Meanwhile the computational results also indicate the shortcomings of these two design schemes.

关 键 词：超燃冲压发动机 燃烧加热器 数值模拟 

分 类 号：V211.72[航空宇航科学与技术—航空宇航推进理论与工程]