高超音速动力系统用单斜面膨胀喷管内流场的数值模拟  

Numerical Simulation of Internal Flow-field in the Single Expansion Ramp Nozzle for High Supersonic Aeroengines

作　　者：陈玉春[1] 商旭升[2] 王晓锋[1] 李江红[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]海军装备研究院,北京100073

出　　处：《兵工学报》2007年第12期1489-1493,共5页Acta Armamentarii

摘　　要：针对设计的高超音速动力系统用单斜面膨胀喷管流动特点,采用三维质量平均Navier-Stokes方程,空间三阶精度高分辨率NND差分格式及可实现k-ε湍流模型,对喷管内流场进行了数值模拟,获得了喷管的流场参数分布。计算结果表明:喷管扩散段长度及出口斜切角变化对喷管出口流场会产生影响;Ⅱ型喷管的设计较为合理。Based on the flow field characteristic of the single expansion ramp nozzle for high supersonic aeroengines, the nozzle inner flow field was numerically simulated by 3D Navier-Stokes equations, three-order high resolution NND difference scheme and realizable κ-ε turbulence model, and the nozzle flow field parameter distribution was obtained. The calculated results show that the design of the type Ⅱ single expansion ramp nozzle for the high supersonic aeroengines is reasonable; varieties of the diffuse segment length and inclination angle of nozzle can affect the nozzle outlet flow-field.

关 键 词：流体力学 喷管 数值模拟 k-ε湍流模型 NAVIER-STOKES方程 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程] O175.1[理学—数学]