摘要
建立了某型直升机动力舱内三维空气流动与传热的物理和数学模型,并根据动力舱结构和舱内气体流动的特点,应用非结构化网格和网格自适应技术进行区域离散化,采用标准k-ε紊流模型和有限容积法对5种不同冷却系统设计方案的舱内三维空气流场和温度场进行了数值仿真,分析了冷却气流进出口大小、分布位置等对舱内流场和温度场的影响。计算结果表明,通风冷却系统进气口开在动力舱前部,出气口开在舱后部,有利于舱内冷却气流流动和换热,舱内气流存在涡旋运动,动力舱温度分布呈“前低后高”趋势。
The physical and mathematical model of the 3D airflow and heat transfer was set up for the helicopter nacelle. Unstructured grids and grid adaptation was applied to the region discretization, taking the characteristic of nacelle configuration and air flow into consideration. For five cooling system design configurations,numerical simulation of the 3D airflow and temperature field was carried out using the standard k-ε turbulent model and finite volume method. The influence of inlet and outlet size and their distribution on velocity field and temperature field was analyzed. The results show that the inlet located in front and the outlet located aft of the nacelle is of benefit to the airflow flow and heat transfer. Air eddy was found in nacelle ,and the temperature in the front part of the nacelle was higher than the rear part.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第2期297-302,共6页
Journal of Aerospace Power
基金
国家重点项目协作课题
关键词
航空
航天推进系统
数值仿真
直升机
流场
温度场
传热
有限容积法
aerospace propulsion system
numerical simulation
helicopter
airflow field
temperature field
heat transfer
finite volume method
