CAJ | 학술논문

喷管是发动机产生推力的主要部件,其气动性能对发动机的性能具有决定性的影响。本文利用简化特征线法设计二元收敛-扩张（2DCD）推力矢量喷管模型;采用RNGk-ε湍流模型和非平衡壁面函数对单缝二次流喷射后的喷管流场进行数值模拟,分析了射流位置、主流落压比（NPR）、二次流与主流总压比（SPR）等参数对矢量喷管气动性能的影响。计算结果表明：二次射流位置对激波强度及推力矢量角有较大影响,开缝位置越接近喷管出口,推力矢量越大;喷射位置固定,激波强度和推力矢量角主要受SPR影响;SPR相同,随着NPR的增加,存在着一个最大推力矢量角。
분관시발동궤산생추력적주요부건,기기동성능대발동궤적성능구유결정성적영향。본문이용간화특정선법설계이원수렴-확장（2DCD）추력시량분관모형;채용RNGk-ε단류모형화비평형벽면함수대단봉이차류분사후적분관류장진행수치모의,분석료사류위치、주류락압비（NPR）、이차류여주류총압비（SPR）등삼수대시량분관기동성능적영향。계산결과표명：이차사류위치대격파강도급추력시량각유교대영향,개봉위치월접근분관출구,추력시량월대;분사위치고정,격파강도화추력시량각주요수SPR영향;SPR상동,수착NPR적증가,존재착일개최대추력시량각。
Nozzle is the main component of an engine,which produces thrust.Its aerodynamic performance is of a decisive influence to engine performance.A Two-Dimensional Convergent-Divergent（2DCD） thrust vectoring nozzle model with fixed length is designed by the simplified method of characteristics in this paper.The full flow-field of the 2DCD thrust vectoring nozzle with single secondary injection are numerically simulated by CFD method,with the RNG turbulence model and non-equilibrium wall functions employed.The influence of secondary injection locations,Nozzle Pressure Ratio（NPR） and Secondary Pressure Ratio（SPR） on aerodynamic performance of thrust vectoring nozzle are examined.The numerical results indicate that：the secondary injection location is of significant effect on shock intensity and thrust vectoring angle,the thrust vectoring angle gradually increase when secondary injection location is transferred toward the nozzle;at the same secondary injection location,the shock intensity and thrust vectoring angle are mainly affected by SPR;at the same of SPR,there exists a maximum thrust vectoring angle as NPR increasing.