直升机附件舱温度场的数值模拟

谢永奇; 余建祖; 王先炜; 李德强

直升机附件舱温度场的数值模拟

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
3.
海军驻鞍钢军事代表室, 鞍山 114000

基金项目: 国家重点项目协作课题

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出版历程
- 收稿日期: 2007-03-30
- 修回日期: 2007-06-11
- 刊出日期: 2008-04-28

Numerical simulation on the temperature field of a helicopter accessory cabin

1.
School of Aeronautic Science and Technology, Beijing Unirersty of Aeronautics and Astronautics, Beijing 100083, China
2.
China Helicopter Research and Development Institute, Jingdezhen, 333001, China
3.
Military Representative of PLA Navy at Angang, Anshan, 114000, China

摘要

摘要: 为考查某型直升机附件舱的热控制能力,采用有限元软件分析了其在强制冷却和自然冷却情况下的温度场分布.应用非结构化网格和有限体积法进行计算区域和控制方程的离散,采用标准k-ε模型封闭湍流控制方程.针对3种冷却系统设计方案,分析了不同冷却气流进口尺寸、相对位置以及不同附件散热量对附件舱温度分布的影响,计算了自然冷却情况下附件舱密闭时的温度场.计算和试验结果均表明,所采用的冷却方案可以满足附件舱冷却的需要.
- 航空、航天推进系统 /
- 直升机 /
- 数值模拟 /
- 温度场 /
- 有限体积法
Abstract: In order to test the thermal control ability of a helicopter accessory cabin with forced ventilation cooling and free cooling,the temperature field was analyzed based on the finite element software.Unstructured grid and finite volume method were applied for region and governing equation discreteness,and standard k-ε model was used as turbulent model.The influence on temperature distribution by changing size and position of cooling air inlet as well as heat dissipating capacity from accessories was discussed for 3 cooling schemes.And the temperature field was calculated for the close cabin under free cooling.The calculation and test results show that the forced cooling scheme can meet the cooling requirements.
- aerospace propulsion system /
- helicopter /
- numerical simulation /
- temperature field /
- FVM(finite volume method)

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参考文献(6)

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