多喷嘴超声速引射器压力匹配性能试验研究  

Experimental Investigation on Pressure Matching of Multi-nozzle Supersonic Ejector

作　　者：吴继平[1] 陈健[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2007年第5期5-9,共5页Journal of National University of Defense Technology

基　　金：国家863计划资助项目(2005AA992020)

摘　　要：建立了多喷嘴超声速引射器试验台,采用燃气作为一、二次流驱动工质对多喷嘴超声速引射器进行了试验研究,重点考察了引射器的压力匹配问题。试验结果表明:一次流总压越低,引射喷嘴出口压力越低,与二次流压力匹配越容易;二次流总压越低,保持压力匹配对引射器的要求越高;二次流总温对压力匹配基本无影响。An ejector test facility was established to investigate the multi-nozzle supersonic ejector performance, and hot rocket exhaust gases were used as primary and secondary driving fluids. Emphases were placed on pressure matching between primary and secondary flows. The investigation indicates that the higher the total pressure of primary flow is and the lower the static pressure of on primary nozzle exit is, the more convenient it is for the performance to match with the secondary flow, and that the lower the secondary flow total pressure is, the more the critical ejector performance is required to maintain pressure matching, and that the secondary flow total temperature has little influence on pressure matching.

关 键 词：超声速引射器 超声速扩压器 压力匹配 高空模拟试车台 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]