重型直升机前飞和悬停状态下主减速器舱流场与通风散热分析  

Analysis of flow field and ventilation and heat dissipation of main reducer cabin under condition of forward flight and hovering of heavy helicopter

作　　者：鲍和云[1] 侯潇男 陆凤霞[1] 朱如鹏[1] BAO Heyun;HOU Xiaonan;LU Fengxia;ZHU Rupeng(National Key Laboratory of Science and Technology on Helicopter Transmission,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机传动技术重点实验室,江苏南京210016

出　　处：《中南大学学报（自然科学版）》2021年第5期1473-1481,共9页Journal of Central South University:Science and Technology

基　　金：国家自然科学基金资助项目(51975274)。

摘　　要：建立重型直升机主减速器舱模型,应用计算流体动力学(CFD)方法,模拟直升机的前飞状态,得到直升机前飞时的出口边界参考压力;对直升机前飞及悬停状态下的流场及温度场进行仿真分析,并考虑空气分配器、发电机通风管路和液压箱通风管路的影响,比较前飞和悬停状态下主减速器舱空气流动状态和散热性能;探讨不同飞行高度和飞行速度下主减速器舱的空气流量和主减速器的散热功率。研究结果表明:在前飞状态下,直升机主减速器舱及舱体外表面温度更低,经由侧气口排出的空气大大增加,而上气口则由压力出口变为进口,涌入大量空气吹向主减速器舱;在前飞状态下,主减速器舱内空气流动速度更快,每组侧气口排出的空气量大致相等,主减速器舱周围空气流速加快,有利于主减速器的散热;随飞行高度和飞行速度增加,主减速器舱出口边界参考压力逐渐减小,主减速器舱空气流量和主减速器的散热功率逐渐增大。The model of the main reducer cabin of the heavy helicopter was established.The forward flight state of the heavy helicopter was simulated with computational fluid dynamics(CFD)method,and the outlet boundary reference pressure was obtained during the forward flight.Considering the influence of the air distributor,generator ventilation pipe and hydraulic tank ventilation pipe,the flow field and temperature field of the helicopter were studied during forward flight and hovering.The air flow and heat dissipation performance of the main reducer cabin in forward flight and hovering state were compared.Then,the air flow of the main reducer cabin and the heat dissipation power of the main reducer at different flight altitudes and flight speeds were discussed.The results show that during the forward flight,the temperature of the main reducer and cabin is lower,the air discharged through the side air port greatly increases,and the upper air port changes from the pressure outlet to the inlet,and a large amount of air pours into the main reduction;the air flow rate in the main reducer cabin is faster,and the air discharged from each side air port is approximately equal;the air velocity around the main reducer accelerates,which is conducive to the heat dissipation of the main reducer.With the increase of flight altitude and flight speed,the reference pressure of the main reducer cabin outlet gradually decreases,and the air flow main reducer cabin and the heat dissipation power of main reducer gradually increase.

关 键 词：重型直升机 主减速器舱 CFD仿真 流场 温度场 前飞 悬停 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]