直升机动力舱流场及温度场的模拟
Numerical Simulation of Nacelle Flow and Temperature Field
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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。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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Key words:
- aerospace propulsion system /
- helicopter /
- nacelle /
- fluid field /
- temperature field /
- finite element
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