超声速高温冲击射流注水流场实验研究  

Experimental study on flow field of high temperature supersonic impinging jet injected by water

作　　者：姜毅[1] 周帆[1] 张学文[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《实验流体力学》2011年第4期32-36,共5页Journal of Experiments in Fluid Mechanics

摘　　要：为了降低发动机羽流冲击流场的温度,减弱其对发射装置的冲击和烧蚀作用,对超声速高温冲击射流的注水流场开展了实验研究。通过高速摄影和红外热像仪两种非接触式测量设备对无注水和注水两种状态下的冲击流场进行了对比拍摄,并且使用热电偶对底板冲击区的温度进行了测量。对注水两相冲击流场的结构和温度场分布进行了深入分析和研究,并与无注水状态下流场进行对比,得出了通过注水方式可以减少核心区长度和面积,降低迎气面温度,减弱其热冲击烧蚀效应的结论。In order to decrease the temperature of flow field of engine plume impinging jet, and weaken the impact and ablation effect on the launcher, an experimental study was developed on flow field of high temperature supersonic impinging jet injected by water. The films of flow field were photographed and compared under two conditions of no-water-injected and water-injected by two non-contact measuring devices of high-speed photography and infrared thermograph, and the temperature of impinging region on bottom plate was measured by thermocouples. Two-phase impinging flow structure and temperature distribution under condition of water-injected were detailedly analyzed and researched,and then compared with condition of no-water-injected. It is concluded that the length and area of potential core have been reduced, the temperature of head face can be decreased,and the thermal impact and ablation effect can be weakened by water injection.

关 键 词：超声速冲击射流 注水 热烧蚀 温度分布 流场结构 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]