二元塞式喷管塞锥气膜冷却特性研究  

Study of film cooling characteristics on plug of two-dimensional(2-D) plug nozzle

作　　者：陈静[1] 单勇[1] 张序墉 征建生 CHEN Jing;SHAN Yong;ZHANG Xuyong;ZHENG Jiansheng(Key Laboratory of Thermal Management and Energy Utilization of Aircraft,Ministry of Industry and Information Technology,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航空飞行器热管理与能量利用工业和信息化部重点试验室,南京210016

出　　处：《航空动力学报》2024年第8期107-116,共10页Journal of Aerospace Power

摘　　要：加力状态使得二元塞式喷管热负荷急剧升高,势必需要引入冷气对塞锥进行冷却。在缩比模型试验验证的基础上,采用全尺寸模型数值仿真,对比分析了入口总压比、开孔率和气膜孔径对二元塞式喷管流动和冷却特性的影响。结果表明:在研究参数范围内,气膜冷却能够显著降低塞锥表面温度,对喷管推力系数影响甚微;以无冷却为基准,入口总压比从1.02增至1.20,塞锥表面温度降低了20%~45%,总压恢复系数降低了0.22%~1.26%;增大开孔率会导致冷却通道压力降低、气膜出流阻力增大,在塞锥尾部甚至出现热气倒灌,综合考虑整个塞锥表面的冷气出流状况,小开孔率结构更具优势;减小气膜孔径意味着气膜孔数目增加、气膜覆盖范围增大,使得塞锥冷却效果有微弱的改善。The heat load of 2-D plug nozzle sharply increases under the afterburning condition,therefore,it is necessary to introduce cold air to cool the plug.Based on subscale model experiment verification,a numerical simulation of full-scale model was performed to investigate the effect of plug film cooling on the aerodynamic and cooling performance of 2-D plug nozzle.The effects of total pressure ratio of inlets,diameter of film holes and perforated percentage of film holes were analyzed by contrast.The calculation results indicated that:within the range of the study parameters,film cooling made the plug surface temperature significantly drop and had a little effect on the thrust coefficient of the nozzle.Compared with the case without cooling,the total pressure ratio of inlets increased from 1.02 to 1.20,the surface temperature of the plug decreased by 20% to 45% and the total pressure recovery coefficient decreased by 0.22% to 1.26%.A lower channel pressure and a bigger film outflow resistance were caused by a higher perforated percentage of film holes,which even caused the hot gas backflow in the tail of plug.Considering the cooling air discharge condition of the whole plug surface,a small perforated percentage of film holes showed more advantages.Reducing the diameter of film holes meant increasing the amount of film holes and the film coverage,thus making the cooling effect slightly enhanced.

关 键 词：二元塞式喷管 气膜冷却 气动特性 冷却特性 模型试验 数值仿真 

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]