导流片对大形状比出口弯曲混合管引射性能影响的数值研究  

Numerical Study on Effects of Guide Baffles on Pumping Performance of Curved Mixing Duct with a Large-Aspect-Ratio Outlet

作　　者：郑禛 张靖周[1] ZHENG Zhen;ZHANG Jingzhou(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&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实验室,南京210016

出　　处：《南京航空航天大学学报》2020年第4期540-547,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：采用数值模拟方法对波瓣喷管-大形状比出口弯曲混合管引射系统进行了流动分析,重点研究导流片数目(n)和出口角(β)对引射性能的影响。与常规无导流片情形相比,出口导流片改善了混合气流在排气出口附近的均匀性,降低了喷管出口截面二次流流通的静压;引射系数随导流片数的增加呈现单调增大的趋势,在导流片数达到8以后继续增加导流片数量,引射系数变化微弱,相对于无导流片情形引射系数的增幅最大可达20%左右;引射系数随导流片出口角的增加而呈现出先增大后减小的趋势,存在一个相对较优的导流片出口角范围,在出口角度为78°左右时可以获得高的引射系数和总压恢复系数。A numerical investigation is performed to study the flow fields inside the specific mixer-ejector,composed of a lobed nozzle and a curved mixing duct with a large-aspect-ratio outlet.The effects of guide baffle number(n)and outflow angle(β)on the pumping performance are illustrated.When compared to the conventional no-baffle situation,the presence of guide baffles is demonstrated to improve the flow uniformity of mixing flow in the vicinity of exhaust outlet and reduce the static pressure of secondary flow passage at the primary nozzle exit.With the increase of guide baffle number the pumping coefficient is raised monotonically.However,beyond n=8,the guide baffle number has nearly no influence on the pumping coefficient.With respect to the conventional no-baffle situation,the pumping coefficient could be increased about 20%by the presence of outflow guide baffles at the best.With the increase of guide baffle outflow angle,the pumping coefficient takes on a first-increase and then-decrease tendency.An optimum outflow angle appears atβ=78°approximately,achieving the maximum pumping coefficient and better total pressure recovery coefficient.

关 键 词：引射混合器 弯曲混合管 大形状比出口 导流片 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.3