直升机附件舱流场和温度场的数值仿真研究  

Numerical Simulation Study on Flow Field and Temperature Field of Accessory Nacelle on a Helicopter

作　　者：秦彦[1] 余建祖[1] 王先炜[2] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083 [2]中国直升机设计研究所,景德镇333001

出　　处：《直升机技术》2005年第2期19-23,共5页Helicopter Technique

摘　　要：建立了某型直升机发动机附件舱内流动和传热的数学模型,利用 k-ε二方程紊流模型模拟舱内流动,应用非结构化网格与网格自适应技术进行区域离散化,采用有限容积法对附件舱内的空气流场和温度场进行了三维数值仿真和分析,为附件舱冷却系统的改进和优化设计提供了依据。结果表明,附件舱冷却系统可以满足舱内冷却要求。A mathematical model for the computation of airflow and heat transfer in an engine acces- sory nacelle of a helicopter was established and the k-ε two-equation turbulence model was used to simulate the airflow.Unstructured grids and grid adaption was applied for region discreteness.The numerical simulation and analysis were carried out for the 3D distribution of airflow and temperature field in accessory nacelle by finite volume method,and a basis for the study on the design and opti- mization of the cooling system was given.The results show that the cooling requirements of the ac- cessory nacelle can be met by the cooling system.

关 键 词：直升机 紊流模型 数值模拟 流场 温度场 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]