S弯进气道旋流缩涡实验研究  

EXPERIMENTAL INVESTIGATION ON SWIRL CONTROL IN AN S-SHAPED DIFFUSER BY VORTEX REDUCED DEVICE

作　　者：翁培奋[1] 郭荣伟[2] 

机构地区：[1]上海交通大学 [2]南京航空航天大学 [3]上海交通大学工程力学系

出　　处：《航空动力学报》1994年第3期310-312,共3页Journal of Aerospace Power

摘　　要：本文提出的旋流缩涡法采用了一种结构简单的缩涡器，是一个金属薄片弯成的框架。这个缩涡器框架被安置在进气道喉道前，通过４个薄片固定在模型上。实验研究表明：该法可缩小由Ｓ弯进气道进口分离所造成的单涡旋流作用范围，并提高出口截面平均总压系数。An experimental investigation on swirl control in an S duct has been completed by the aid of a so called vortex reduced device (VRD) which is made of a metallic frame and placed upwards near the throat of the diffuser.Effects of geometric sizes of the VRD and its angle of attack on the flow in the duct were investigated in a wind tunnel.The flow parameters,including wall static pressure,total pressures and 3 D velocity field at the duct exit were measured.The optimum geometry shape and size (W id =0 0595) are found.The VRD with optimized geometry can effectively reduce the swirling range and improve the average total pressure coefficient at the exit.

关 键 词：进气道 气场 畸变 飞机 

分 类 号：V228.71[航空宇航科学与技术—飞行器设计]