小突片红外抑制效应的实验研究  

Experiment on infrared suppression with small tabs

作　　者：朱英[1] 黄勇[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《推进技术》2007年第4期413-417,共5页Journal of Propulsion Technology

摘　　要：利用地面模拟试验件实验研究了主喷管流速为亚声速,温度610℃左右,下洗气流速度11m/s,位于主喷管出口的小突片的安装方式和尺寸对某型号直升机发动机出口红外隐身效果的影响,实验用的混合管主喷管面积比为1.5。结果表明,和不装小突片时的基准状态相比,安装四片小突片时出口最高气流温度和平均气流温度分别降低2.3%和1%,主喷管总压升高0.44%。而增加小突片的尺寸,对红外抑制效果有所改进,不过总压损失会增大。An experiment is conducted to study the infrared suppression effects of the small tabs which are fixed on the exit of a model infrared suppressor for helicopter. The main flow velocity is subsonic and temperature of the main flow is about 610℃. The downwash flow velocity is about 11 m/s. The area ratio of the mixer inlet to main nozzle exit is about 1.5. The results show that by comparison with the baseline structure without tabs, the highest and the averaged exhaust temperatures at the exit decrease by 2.3% and 1% , respectively, and the total pressure of the main nozzle increase by 0.44% , when four tabs are fixed. By increasing the size of the tabs the infrared suppression effect is improved but the total pressure loss is increased.

关 键 词：直升机 红外抑制 小突片^+ 强化混合^+ 射流喷管 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]