二次扩张型射流矢量喷管的设计及性能计算  

Design of secondary-divergent vectoring nozzle based on secondary fluidic injection

作　　者：张永升[1] 王延奎[1] 于晓伟[1] 邓学蓥[1] 

机构地区：[1]北京航空航天大学流体力学教育部重点实验室,北京100083

出　　处：《北京航空航天大学学报》2007年第3期261-264,318,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：应用数值模拟的方法对二次扩张型射流矢量喷管进行设计并研究了其推力矢量性能,探讨了二次扩张段注入射流产生推力矢量的机理,分析了二次扩张角度以及次主流压力比(SPR,Secondary to Primary total pressure Ratio)的变化对喷管主喷流偏转特性的影响.计算结果表明:在二次扩张段上注入二次射流可使喷管的出口段在不同区域产生不均匀的压强分布并且迫使主喷流发生偏转产生推力矢量;二次扩张型喷管比无二次扩张型喷管具有更好的推力矢量性能;二次扩张角度越大喷管产生的气动矢量角越大,在文中设计条件下二次扩张型喷管的气动矢量角最大可达39;°气动矢量角随次主流压比SPR的增大而增大.Secondary-divergent vectoring thrust nozzle based on secondary fluidic injection was designed and the performance of vectoring thrust nozzle was studied by using computer simulation method. Several parameters, such as the angle of secondary-divergent section, the ratio of secondary fluidic injection pressure to main flow pressure, were taken into consideration in analysis of the nozzle performance. As a result, several conclusions were drawn from the above investigations. Firstly, the vectoring thrust is mainly caused by the secondary fluidic injection on the secondary-divergent section. The performance of nozzle with secondary-divergent section is better than that of nozzle without secondary-divergent section. Secondly, vectoring angle increases with the increasing of angle of secondary-divergent section and the maximum of vectoring angle reaches 39°. Finally, the vectoring angle increases with the increasing of the ratio of secondary fluidic injection pressure to main flow pressure.

关 键 词：矢量喷管 射流 气动矢量角 数值模拟 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]