部件冷却对二元俯仰矢量排气系统红外特征抑制实验  

Experiment on infrared characteristics suppression by component cooling of two-dimensional convergent-divergent vectoring nozzle exhaust system

作　　者：卢浩浩[1] 吉洪湖[1] 王丁[1] 刘健[1] 王浩[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2017年第9期2070-2079,共10页Journal of Aerospace Power

摘　　要：实验测试了采用中心锥气膜冷却和喷管冲击-气膜冷却的二元俯仰(2D-CD)矢量排气系统,在几何偏转0°,10°,20°三种角度下,壁面温度和红外辐射特征分布,并与未冷却状态进行了对比分析。结果表明:前密后疏的气膜孔排布形式可有效减小热侧面高温区域大小。中心锥冷却时,密流比为0.8条件下壁面冷却效率达45%~63%,排气系统尾向±10°范围内红外辐射强度下降20%;但是由于冷气流注入,导致下游壁面(隔热屏、喷管)温度升高,在30°探测方向上红外辐射强度上升15%。喷管冷却时,收敛段(密流比为0.25)冷却效率达19%~33%,扩张段(密流比为0.65)冷却效率达75.5%~83.5%,侧壁段(密流比为0.65)冷却效率达78%~90%,导致在排气系统尾向15°~75°范围内,红外辐射强度下降30%以上,最大降幅达80%(几何偏转20°,宽边探测面30°探测方向)。Experiment was conducted to study the distribution of wall temperature and infrared radiation characteristics on two-dimensional convergent-divergent （2D-CD） vecto- ring nozzle exhaust system with cone film cooling and nozzle impingement-film cooling, in three geometric deflection states, namely deflection of 0°, 10°, 20°, and the results were compared with no-cooling state. The experimental results showed that film holes with pre dense and after thinning arrangement form can effectively reduce the hot side temperature re- gion size. For cone cooling state, under the conditions of density flow ratio of 0.8, cooling efficiency reached 45%- 63%, the infrared radiation intensity of exhaust system decreased by 20%, in the tail direction ±10°, but due to the cooling air flow injection, the tempera- ture of heat shield wall and nozzle wall increased, and infrared radiation intensity increased by 15%, in 30° detection direction. In nozzle cooling state, convergent section （density flow ratio of 0.25） cooling efficiency reached 19%-33%, the expansion section （density flow ra-tio of 0. 65） cooling efficiency reached 75.5%-83.5%, the side wall sections （density flow ratio of 0. 65） eooling efficiency reached 78%-90%, infrared radiation intensity decreased by more than 30%, in the tail direction 15°-75°, the maximum decrease reached 80% （geo- metric deflection angle of 20°, detection direction of 30°）.

关 键 词：二元俯仰(2D-CD)矢量喷管 矢量偏转 气膜冷却 冲击-气膜冷却 红外抑制 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]