分离和耦合求解对轴对称喷管尾焰流场计算的影响  

Influence of Separation and Coupling Solution on Calculation of the Plume Flow Field of Axisymmetric Nozzle

作　　者：王杏涛[1] 祁鸣[1] 张二磊[1] Wang Xingtao;Qi Ming;Zhang Erlei(China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2018年第5期68-72,共5页Aero Weaponry

摘　　要：基于某型发动机轴对称喷管的简化模型,分别采用分离求解和耦合求解进行喷管尾焰数值仿真,分析了两种算法对喷管尾焰流场分布的影响。研究表明:在喷管尾焰核心区,耦合求解比分离求解所出现的环形马赫盘分布周期数量更多,与之对应喷管轴向中心线上压力、温度、速度和马赫数曲线震荡更加明显,震荡距离更长;两种求解方式的流场压力分布大小基本一致;分离求解比耦合求解的温度场分布更高,且在尾焰核心区尾部出现峰值;耦合求解比分离求解的尾焰核心区速度和马赫数分布更高;耦合求解更加适合超音速喷管流场的计算。Based on the simplified model of an axisymmetric nozzle for a certain type of engine, the numerical simulation of nozzle tail flame is done by separation and coupling solution and the influence of two solutions on the distribution of flow field of the nozzle tail flame are analyzed. Studies show that compared to separation solution, coupling solution gets more ring Mach disks in the tail flame core area and the curves of pressure, temperature, velocity and Mach number have more severe concussion and longer concussion distance on the axial center line of the nozzle. The pressure distribution of flow field of the two solutions is basically the same. Compared with coupling solution, separation solution have a higher temperature distribution and a peak at the tail of the flame core. However, coupling solution gains higher velocity and Mach number distribution. Coupling solution is more suitable for the calculation of supersonic nozzle flow field.

关 键 词：轴对称喷管 数值仿真 分离求解 耦合求解 尾焰流场 马赫盘 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V231[航空宇航科学与技术—航空宇航推进理论与工程]