风洞引射器试验研究  

EXPERIMENTAL RESEARCH OF WIND TUNNEL INJECTOR

作　　者：凌其扬[1] 廖达雄[1] 陶祖贤[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《气动实验与测量控制》1994年第2期10-18,共9页

摘　　要：本文简要地叙述了ＣＡＲＤＣ近期结合新型跨声速风洞对引射器进行试验研究的情况。研究表明：当采用中压气源（２５×１０５Ｐａ）为动力源时，设计合理的多喷嘴引射器在获得跨声速风洞（Ｍ＝０．４５～１．２）需要的增压比前提下，消耗的中压气源空气流量较目前国内常用的二元引射器成倍下降，引射后混合气体流量与消耗的气源气体流量之比可达３～６；气流噪声随喷嘴个数增加而下降；大型风洞的多喷嘴引射器喷嘴个数≥１６是有利的。The experimental research about wind tunnel injector withthe developing of new CARDC transonic wind tunnel is conclusively described in this paper. The conclusions we drew from investigations are asfollows: Comparing with a two dimensional injector usually adopted domestically, when the air storage is a medium pressure one, a reasonablydesigned multinozzle injector which will suffice the pressure ratio fortransonic blind tunnel (M=0. 45～1. 2) consumes times less mass flow froma medium pressure air storage. The ratio of mixed mass flow to the massflow the air storage consumed is as high as three to six. The flow noisewill decrease with the increasing of nozzles and the optimal nozzle number for multi-nozzle injector should be sixteen or more.

关 键 词：引射器 引射器试验 风洞 驱动装置 

分 类 号：V211.752[航空宇航科学与技术—航空宇航推进理论与工程]