固定几何气动矢量喷管气动性能数值仿真  

Numerical Simulation on Performances of Fluidic Control Fixed Geometry Aerodynamic Nozzle

作　　者：张少丽 周吉利 贾东兵 徐速 ZHANG Shao-li;ZHOU Ji-li;JIA Dong-bing;XU Su(AECC Shenyang Engine Research Institute, Shenyang 110015, China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2018年第2期20-26,共7页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：为掌握固定几何气动矢量喷管气动性能,通过CFD数值模拟的方法,研究了主流落压比、扩张段二次流落压比、扩张段二次流角度和引射对固定几何气动矢量喷管轴向推力系数的影响;主流落压比、扩张段二次流落压比和扩张段二次流角度对矢量角的影响;主流落压比、喉道二次流落压比和喉道二次流角度对喉道控制率的影响。结果表明:随主流落压比增大轴向推力系数增大,矢量角减小,喉道控制率减小;随扩张段二次流落压比增大推力系数减小,矢量角增大;随喉道二次流落压比增大,喉道控制率增大;随扩张段二次流角增大轴向推力系数减小,矢量角略有减小;随喉道二次流角增大喉道控制率增大;随引射方式增加喷管推力系数增大。In order to obtain the aerodynamic performances of the fluidic control fixed geometry nozzle,the effects of Nozzle Pressure Ratio（NPR）,Second Flow Pressure Ratio（SPR）,angle of second flow on divergent section and injection on the axial thrust coefficient for the fluidic control fixed geometry nozzle,the effects of nozzle pressure ratio,SPR and angle of second flow on divergent section on the vectoring angle,the effects of NPR,SPR and angle of second flow on throat section on the control ratio of throat area were investigated by CFD numerical calculations.The results show that the axial thrust coefficient increased,the vectoring angle and the control ratio of throat area decreased with the increase of NPR.The axial thrust coefficient decreased,the vectoring angle increased with the increase of SPR on divergent section.The control ratio of throat area increased with the increase of SPR on throat section.The axial thrust coefficient decreased and the vectoring angle decreased a little with the increase of angle of second flow on divergent.The control ratio of throat area increased with the increase of angle of second flow on throat.The thrust coefficient increased with the increase of injection mode.

关 键 词：气动性能 固定几何 流体控制 矢量喷管 数值仿真 航空发动机 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]