微型涡流发生器改善S弯喷管流场的实验研究  

Experimental investigation of S-shaped nozzle flow field performance enhancement using micro-vortex generator

作　　者：刘诗敏 梁华[1] 李金平 张富垚 马张煜 LIU Shimin;LIANG Hua;LI Jinping;ZHANG Fuyao;MA Zhangyu(National Key Lab of Aerospace Power System and Plasma Technology,College of Aeronautical Engineering,Air Force Engineering University,Xi’an 710038,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]空军工程大学航空工程学院航空动力系统与等离子体技术全国重点实验室,陕西西安710038 [2]南京航空航天大学航空学院,江苏南京210016

出　　处：《推进技术》2025年第2期41-56,共16页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅱ-0014-0035);基础加强基金(2019-053)。

摘　　要：S弯喷管虽然能够提升飞行器隐身性能,但弯曲的几何结构会造成额外的总压损失和低能流体脉动增强的问题,导致飞行器性能降低,因此需要采用流动控制手段改善内部流场。本文将阵列式微型涡流发生器安装在S弯喷管上壁面中心线局部速度最大点前侧,研究其在冷态流场中对喷管出口总压损失的控制效果和对上壁面下游流场低频脉动的抑制效果。结果表明:(1)在试验参数下,对于相同高度的微型涡流发生器,安装位置距离局部速度最大点较远时,喷管出口截面总压损失系数更低。(2)落压比为1.2时,安装高度为2.2%喷管入口直径的微型涡流发生器,能够使喷管出口平均总压损失系数相对基准降低8.57%。(3)微型涡流发生器能降低喷管上壁面下游流场的低频脉动,使脉动幅值降低22.8%,提升低能流稳定性。Although the S-shaped nozzle can improve the stealth performance of the aircraft,the curved ge⁃ometry will cause additional total pressure loss and increase the pulsation of low-energy fluid,resulting in re⁃duced performance of the aircraft.Therefore,flow control methods are needed to improve the flow field.A single array of micro-vortex generators(MVGs)is employed in front of the local maximum velocity point of the center line on the upper wall of the S-shaped nozzle,and its control effect on the total pressure loss of the nozzle outlet and the suppression effect on the low frequency pulsation of the downstream flow field of the upper wall are inves⁃tigated.The results show that:(1)Under the test parameters,the total pressure loss coefficient of nozzle outlet section is lower when the installation position is far away from the local maximum velocity point for the micro-vor⁃tex generator with the same height.(2)When the drop pressure ratio is 1.2,the micro-vortex generator with a height of 2.2%of the nozzle inlet diameter can reduce the average total pressure loss coefficient of the nozzle out⁃let by 8.57%compared with the baseline.(3)The micro-vortex generator can reduce the low-frequency pulsa⁃tion of the downstream flow field on the upper wall of the nozzle,reduce the pulsation amplitude by 22.8%,and improve the stability of low-energy flow.

关 键 词：S弯喷管 微型涡流发生器 总压损失 流动控制 变分模态分解 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]