塞锥气膜冷却对二元塞式喷管红外特征的影响  

Effect of wedge film cooling on the infrared signature of two-dimensional wedge nozzle

作　　者：周兵[1] 吉洪湖[1] ZHOU Bing JI Hong-hu(College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)

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》2016年第12期2895-2903,共9页Journal of Aerospace Power

摘　　要：为了研究二元塞式喷管塞锥壁面多斜孔气膜冷却对喷管红外特征的影响,设计了带冷却结构的喷管试验模型,测量了吹风比从0增加到1时的塞锥壁面温度、喷管出口截面处喷流温度以及喷管红外辐射强度.结果表明:随着吹风比的增加,气膜冷却效率逐渐提高,最大达到0.68;喷管出口截面在中心区域喷流的温度逐渐降低,最大降幅为14%;喷管红外辐射强度逐渐降低,在0°方位角上最大降低52.8%,在90°方位角上最大降低13%.The experimental model of two-dimensional wedge nozzle with cooling structure was designed, and a series of experimental investigations were conducted to measure the effect of wedge film cooling on infrared signature of the nozzle. The wedge wall temperature, the jet flow temperature on the nozzle exit and the infrared radiation intensity of the nozzle were measured at blowing ratios of 0 to 1. Results show that, with the increase of blowing ratio, the wedge wall temperature gradually decreases and the film cooling effectiveness increases up to 0. 683 the jet flow temperature on center area of the nozzle exit decreases to 14%, the infrared radiation intensity of the nozzle gradually decreases to 52.8% at azimuth angle of 0° and 13% at azimuth angle of 90°.

关 键 词：二元塞式喷管 塞锥 冷却 多斜孔 红外特征 

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]