某RBCC样机进气道的设计与数值模拟  

Design and numerical investigation of RBCC prototype inlet

作　　者：石磊[1] 何国强[1] 秦飞[1] 刘佩进[1] 刘晓伟[1] 

机构地区：[1]西北工业大学航天学院,燃烧、热结构与内流场重点实验室,西安710072

出　　处：《航空动力学报》2011年第8期1801-1807,共7页Journal of Aerospace Power

摘　　要：针对某包含引射、亚燃两模态（马赫数为0～4．0）的支板式火箭基组合循环（rocket based combinedcycle）发动机地面集成试验，设计了样机用带支板的二元进气道．数值模拟对比分析了在亚燃模态下进气道加入支板前后的性能以及流道内的流动情况，验证了设计的合理性，并且给出了支板位置以及构型的改变引起RBCC发动机进气道性能变化的规律和优化设计结果．The inlet of RBCC （rocket based combined cycle） engine ground-test proto- type operated in rocket ejector mode and ramjet mode （Mach number from 0 to 4.0） was investigated. The 2 D （two-dimentional） inlet with strut was designed. Through numerical simulation, a comparative analysis of the performance and the inner flow with/without strut in the inlet in ramjet mode was made, whereas rationality of the design was verified and a rule was derived for the variation of the performance of RBCC prototype＇s inlet, which was induced by the change of the location or the configuration of strut. Finally, an optimized configuration was obtained.

关 键 词：支板式火箭基组合循环 二元进气道 支板 设计 数值模拟 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]