抽吸排气式高焓风洞应用实验研究  

Applied Experimental Study of Exhaust High Enthalpy Tunnel with Pumping

作　　者：蒲旭阳[1,2] 刘伟雄[1] 李向东[1] 毛雄兵[1] 卢传喜[2] 丛京伟[2] 

机构地区：[1]中国空气动力研究与发展中心,超高速空气动力研究所,高超声速冲压发动机技术重点实验室,四川绵阳621000 [2]中国空气动力研究与发展中心,吸气式高超声速技术研究中心,四川绵阳621000

出　　处：《推进技术》2018年第2期450-455,共6页Journal of Propulsion Technology

摘　　要：连续式高焓风洞是开展吸气式高超声速技术研究的重要试验设备,这类风洞一般采用了引射式排气或真空排气工作方式。为了避免引射式排气风洞组成复杂、参数匹配要求高、引射效率低以及真空排气风洞不能实现连续式排气等不足,提出了一种新的高焓风洞形式—抽吸排气式高焓风洞,采用了"真空罐+抽气泵"进行组合抽吸排气,真空罐完成风洞快速启动,抽气泵实现风洞长时间连续运行。实验结果表明:这种形式的高焓风洞实现了连续式排气,而且能在55%模型堵塞度条件下实现风洞启动运行,具有良好的应用前景。Continuous high enthalpy tunnel including injector tunnel and vacuum tunnel are playing very important roles on the air-breathing hypersonic technology research. For the sake of keeping away from the complexity of makeup and rigorous parameter matching and the lower injector efficiency of the injector high enthalpy tunnel and limitation of continuous exhaust of the vacuum tunnel,a new type of high enthalpy tunnel,i.e. exhaust high enthalpy tunnel with pumping,is presented in this paper. It adopts a combined exhaust system which is made up of a pump actualizing continuous exhaust and a vacuum pot used for fast start-up. The experimental results show that this type tunnel can realize continuous exhaust and can start up under the 55% model blockage condition,so the application prospects can be anticipated.

关 键 词：高焓风洞 抽吸 连续式排气 模型堵塞度 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]