基于旋翼下洗流场的直升机动力舱通风冷却系统仿真

本文对直升机悬停状态下下洗流场影响区域、动力舱以及发动机排气引射器进行了联合建模,采用结构化网格对计算域进行离散,采用有限体积法求解雷诺平均Navier-Stokes方程,通过数值仿真考察不同湍流模型、发动机散热、以及动力舱进口尺寸对排气引射器引射系数以及动力舱通风冷却系统内部流场的影响。结果表明,引射系数对湍流模型依赖性较小;发动机散热将导致引射气流量、引射系数减小,而且随着冷却气流进口面积的增大,这种影响将增大;增大冷却气流进口尺寸,冷却气流量增大,引射系数增大,但进口尺寸增大到一定值后,其效果已不明显。

Simulation Study of Helicopter Nacelle Ventilation Cooling System Considering of Downwash Flow

The physical and mathematical model of airflow and heat transfer was set up for the helicopter nacelle,exhaust ejector and outflow region.Structured grids were applied to the computing region discretization.The Reynolds-averaged Naviers-Stokes equations were solved based on the method of finite control volume.The impact of turbulence model,heat dissipation of the engine and nacelle inlet size on pumping coefficient of exhaust ejector and flowfield of nacelle ventilation cooling system is studied.The results...