前飞状态下直升机动力舱通风冷却性能仿真

Simulation on the ventilation cooling performance of the helicopter engine nacelle in forward flight

针对某型直升机动力舱通风冷却系统,提出了一种简化的基于旋翼下洗流的动力舱通风冷却性能计算方法,利用商业CFD软件,计算了前飞状态下采用单进口和双进口共9种方案时动力舱流场和温度场分布,分析了不同进口数、进口大小和位置对动力舱通风冷却性能的影响,并与试飞试验结果进行了对比。结果表明,该方法能够准确预测直升机动力舱通风冷却系统性能,仿真研究结果可以为动力舱通风冷却系统的设计与优化提供科学依据。

A simplified method of evaluating the ventilation cooling performance of the engine nacelle based on rotor downwash flow was presented,for the engine nacelle ventilation cooling system of the helicopter.Using the business CFD software,the flow field and the temperature field in the nacelle in forward flight were calculated for single-inlet scheme and double-inlets scheme,total up to 9 schemes.The influence on the cooling performance was analyzed for different inlet number,inlet size and inlet position.And the comparisons were completed between flight test and numerical simulation results.The results show that the method can exactly forecast the performance of the ventilation cooling system of the helicopter nacelle,and the simulated results can be regarded as reference for the design and optimization of the system.