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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。
Nozzle is the main thrust of the engine, its aerodynamic performance has a decisive impact on the performance of the engine. In this paper, a simplified two-dimensional convergent-divergence (2DCD) thrust vector nozzle model was designed by using the simplified characteristic line method. The RNGk-ε turbulence model and the unbalanced wall function function were used to simulate the nozzle flow field after the single- The effects of jet position, mainstream pressure ratio (NPR), secondary flow and mainstream total pressure ratio (SPR) on the aerodynamic performance of vector nozzle were investigated. The results show that the location of the second jet has a significant influence on the shock strength and the thrust vector angle, and the closer the position of the slit to the exit of the nozzle, the larger the thrust vector. The fixed jet position, the shock intensity and the thrust vector angle are mainly affected by the SPR ; Same SPR, with the increase of NPR, there is a maximum thrust vector angle.