基于激波控制的S弯二元矢量喷管数值模拟  

Numerical Simulation of Serpentine 2-D Vectoring Nozzle based on Shock Wave Control

作　　者：王伟 赵振 金文栋 邓洪伟 WANG Wei;ZHAO Zhen;JIN Wen-dong;DENG Hong-wei(AECC Shenyang Engine Research Institute,Shenyang 110015,China;Changchun Military Representative of Air Force Equipment Ministry,Changchun 130000,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]空军装备部驻长春地区军事代表室,长春130000

出　　处：《航空发动机》2021年第5期19-25,共7页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了掌握S弯二元矢量喷管的气动性能,采用CFD数值模拟方法研究了有无二次流喷射状态下S弯二元矢量喷管激波诱导的工作机理,以及二次流喷射位置、主流落压比和二次流与主流总压比对S弯二元矢量喷管推力系数、矢量角、壁面静压的影响。结果表明:在二次流流通面积不变、次流与主流流量比W_(s)/W_(p)≤6%的情况下,喷管上、下壁面分别喷射二次流产生的最大矢量角分别为22.9°和15.9°;喷射位置对矢量角有较大影响,对推力系数影响不大,随着二次流喷射位置逐渐靠近出口,矢量角先增大后减小;射流位置固定,随着主流落压比的增大,推力系数增大,当主流落压比从2增大到6时,推力系数最多提高17.9%,矢量角先增大后减小;随着二次流与主流总压比的增大,推力系数整体呈单调减小趋势,矢量角先增大后减小。In order to obtain the aerodynamic performances of the Serpentine 2-D vectoring nozzle,the working mechanism of shock wave induction of Serpentine 2-D vectoring nozzle with or without secondary flow injection was studied by CFD numerical simulation meth⁃od,and the effects of secondary flow injection position,Nozzle Pressure Ratio(NPR)and Second Flow Pressure Ratio(SPR)on the thrust co⁃efficient,vector angle and wall static pressure of Serpentine 2-D vectoring nozzle were studied.The results show that under the condition of fixed secondary flow area and the ratio of secondary flow by main flow less than or equal to 6 percent,maximum vector angle due to second⁃ary flow injection on the up and down nozzle surface reach 22.9 and 15.9 degree separately.Injection position have dramatically affects on vector angle and have little effect on thrust coefficient.Vector angle increased firstly and decreased later as the secondary flow injection po⁃sition approach outlet gradually.Thrust coefficient increase with the increase of NPR when the injection position fixed.Thrust coefficient increase 17.9 percent maximum and vector angle increased firstly and decreased later when NPR increase from 2 to 6.With the increase of SPR,thrust coefficient decrease and vector angle increased firstly and decreased later.

关 键 词：S弯二元矢量喷管 激波控制 推力矢量 数值模拟 航空发动机 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]