一种超音速环形引射器冷流缩比试验方法  

Cold-flow testing of a sub-scale model for the annular supersonic ejector

作　　者：何德胜[1] 鲍福廷[1] 赵继伟[2] 李广武[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国航天科技集团公司四院401所,西安710025

出　　处：《固体火箭技术》2011年第5期655-658,共4页Journal of Solid Rocket Technology

摘　　要：在超音速引射器的设计中,为开展引射机理及启动特性等研究,需进行模拟试验;同时,通过试验可验证数值计算结果的正确性与合理性,从而优化设计。文中提出以冷空气作为引射和被引射介质,采用缩比试验模型,通过模拟喷嘴生成被引射气流,简化了试验设备。数值计算结果与试验结果符合较好,正确预测了引射管道出口处出现的正激波,真空舱压强满足设计要求。该试验方法可作为超音速引射器原理性研制的试验手段。Simulation testing is an important method to study the mechanism and starting performance in design of supersonic ejector.At the same time,simulation testing can prove the correctness and the rationality of the computed result,and optimize the design of the supersonic ejector.A sub-scale model was proposed which uses cold-flow and simulation nozzle to produce ejected air.Test equipments can be simplified by using this method.The numerical results agree well with the available test data.The normal shock wave at the exit of the ejector is predicted correctly and the vacuum chamber meets the design requirement.The test method can be applied to theoretical research of supersonic ejector.

关 键 词：超音速引射器 引射机理 启动特性 冷流缩比试验 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]