直升机压力加油通气系统溢油动特性研究  

Study on Transient Process of Fuel Overflow by Vent System during Ground Pressure Refuel System for a Helicopter

作　　者：杨小龙[1] 谢增[1] 张驰 YANG Xiaolong;XIE Zeng;ZHANG Chi(China Helicopter Research and Development Institute,Jingdezhen333001,China)

机构地区：[1]中国直升机设计研究所

出　　处：《直升机技术》2019年第3期19-23,共5页Helicopter Technique

摘　　要：通过某型直升机压力加油通气系统溢油试验,研究了燃油箱内膨胀空间的压力历程。在试验研究和直升机压力加油通气系统溢油机理基础上,利用Flowmaster软件建立了某典型直升机压力加油通气系统溢油仿真模型,仿真结果与试验结果吻合较好,验证了模型的正确性。在此基础上,研究了直升机压力加油通气系统溢油动特性。结合仿真结果,分析了通气阀流阻特性、压力加油流量、通气口入口位置的影响,为通气系统部件选型及参数确定提供参考,具有良好的工程应用价值。With the experiment of fuel overflowby vent system during ground pressure refuel system for a helicopter,the study on history rate of pressure of fuel tank was conducted.Based on the experimental study and the analysis of operational principle of transient process of fuel overflow by vent system during ground pressure refuel system for a helicopter, a simulation model of helicopter vent system was built with commercial code of Flowmaster.The simulation results and the experimental results were in a good agreement which reveals the validity of numerical model.By combining with simulation results, the impact of vent valve' s loss and refuel flow rate and distancefrom exit of vent to top of tank and horizontal cross - sectional area of tank were analyzed. Consequently, the reference of components of vent system was provided which ismeaningful for engineering application.

关 键 词：压力加油 通气系统 溢油 仿真 

分 类 号：V233.2[航空宇航科学与技术—航空宇航推进理论与工程]