摘要
该文利用有限体积法,应用非结构网格,建立了×型直升机发动机舱的有限元模型;并根据舱内实际冷却气体流通情况,采用SIMPLE算法,求解了流动和传热的控制方程,模拟了发动机舱内温度场的分布。在此基础上针对现有设计存在的问题,提出了该型直升机发动机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。该模拟结果为发动机舱冷却系统的改进设计提供了参考,保证了发动机的正常工作及可靠运行,具有重要的现实意义。
The finite elements model of the nacelle is created using the non - structure grids by the finite volume method. Considering the real flow situation in the nacelle, the flow and heat transfer control equations are computed by the SIMPLE arithmetic, and the temperature field in the nacelle is analyzed. Further more, based on the problems in the existing design, the improved projects for the nacelle cooling situation are provided, and also the analysis of the projects. The simulation results have provided reference to the ameliorating design for the nacelle cooling system, which can ensure the engine working well, and have important practical meaning.~
出处
《计算机仿真》
CSCD
2005年第9期47-51,共5页
Computer Simulation
关键词
发动机舱
温度场
仿真
Engine nacelle
Temperature field
Simulation
