某中央翼燃油箱惰化流场的数值模拟及特性分析

王学德; 王志伟; 刘卫华; 张声奇; 王小平

某中央翼燃油箱惰化流场的数值模拟及特性分析

1.
南京理工大学能源与动力工程学院,南京 210094
2.
南京航空航天大学航空宇航学院,南京 210016
3.
南京机电液压工程研究中心航空机电系统综合航空科技重点实验室,南京 211100

基金项目: 南京理工大学紫金之星资助计划; 教育部博士点基金(20093219120031); 南京理工大学自主科研资助项目(2011YBXM111)

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出版历程
- 收稿日期: 2011-12-22
- 刊出日期: 2012-12-28

Numerical simulation and analysis of nitrogen-enriched air flow in a center wing tank

1.
School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China
2.
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
3.
Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration, Nanjing Engineering Institute of Aircraft System, Nanjing 211100, China

摘要

摘要: 在不同富氮气体入口参数下,对某大型运输机中央翼燃油箱的惰化过程进行了数值模拟,研究了在不同流量和体积分数富氮气体条件下燃油箱的惰化规律.计算结果显示:当富氮气体中氮气体积分数为95%、体积流量分别为0.021,0.028m³/s和0.042m³/s时,燃油箱内平均氧体积分数随体积置换次数的变化曲线几乎完全重合;当富氮气体体积流量为0.042m³/s、氮气体积百分比分别为92%,94%和98%时,燃油箱惰化率随时间的变化曲线重合.说明相同体积分数富氮气体条件下燃油箱惰化完成时所需富氮气体量与富氮气体流量无关,而富氮气体的流量直接决定了各舱室富氮气体的惰化率.通过对计算结果的分析,证明了利用缩比油箱去模拟真实油箱的惰化过程的合理性.为优化某运输机中央翼燃油箱惰化系统设计提供参考.
- 数值模拟 /
- 燃油箱惰化 /
- 油箱冲洗 /
- 机载制氮系统 /
- 入口参数
Abstract: Under the different nitrogen-enriched air(NEA) parameters, the inerting process was studied by numerical simulation of a civil airplane center wing tank(CWT). The study show the inerting rule of the CWT under different flow rates and different oxygen concentration. The results show that, when the NEA containing volume fraction of about 95% of the nitrogen and the volume flow rate of the NEA are 0.021, 0.028m³/s and 0.042m³/s, the average oxygen volume fraction distribution versus volumetric tank exchange (VTE) are almost the same; when the volume flow rate of the NEA is 0.042 m³/s and the volume fraction of the nitrogen are 92%, 94% and 98%, the inerting ratio versus time are the same. It is conclusion that the inerting time of the CWT has nothing to do with the flow rate under the same oxygen concentration, and the flow rate of the NEA determines the inerting ratio of each bay. Based on comparative analysis of the numerical result, it proves that the shrink analogy method can be used to simulate the inerting process of the CWT. The research provides reference for optimizing the design of a transport airplane inerting system.
- numerical simulation /
- fuel tank inerting /
- fuel washing /
- onboard inert gas generation system /
- input parameter

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参考文献(15)

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