| 直升机动力舱流场及温度场的模拟 |
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| 引用本文： | 王芳,余建祖,谢永奇.直升机动力舱流场及温度场的模拟[J].航空动力学报,2005,20(2):208-213. |
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| 作者姓名： | 王芳 余建祖 谢永奇 |
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| 作者单位： | 北京航空航天大学航空科学与工程学院,北京100083 |
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| 摘 要： | 应用非结构网格,建立了直升机发动机动力舱的有限元模型,并根据舱内实际冷却气体的流通情况,采用SIMPLE算法,求解了流动和传热的控制方程,模拟了动力舱内流场与温度场的分布,研究了流场、压力场及温度场之间的依变关系。在此基础上针对现有设计存在的问题,提出了动力舱冷却系统的改进方案,并对不同方案的改进效果进行了分析比较。
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| 关 键 词： | 航空、航天推进系统 直升机 动力舱 流场 温度场 有限元 |
| 文章编号： | 1000-8055(2005)02-0208-06 |
| 收稿时间： | 2004/5/27 0:00:00 |
| 修稿时间： | 2004年5月27日 |
Numerical Simulation of Nacelle Flow and Temperature Field |
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| WANG Fang,YU Jian-zu and XIE Yong-qi.Numerical Simulation of Nacelle Flow and Temperature Field[J].Journal of Aerospace Power,2005,20(2):208-213. |
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| Authors: | WANG Fang YU Jian-zu and XIE Yong-qi |
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| Institution: | Institute of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing100083,China |
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| Abstract: | The finite element model of the nacelle flow was established using the non-structure grids.The flow and heat transfer control equations were solved by the SIMPLE algorithm taking the real cooling flow situation in the nacelle into consideration.The flow and temperature fields were simulated and the relationships between the flow,pressure and temperature field were analyzed. Further more,according to the problems in the existing design,plans were proposed to improve the nacelle cooling situation.The effectiveness of different plans were compared and analyzed. |
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| Keywords: | aerospace propulsion system helicopter nacelle fluid field temperature field finite element |
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