直升机燃油系统增压转自吸供油动特性  

Transient Process of Helicopter Fuel System Transferred from Boost Fueling to Self-Suck

作　　者：杨小龙[1,2] 罗铁苟[2] 金华[3] 童明波[1] 

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点实验室,南京210016 [2]中国直升机设计研究所,景德镇333001 [3]总参谋部路航部驻景德镇地区军事代表室,景德镇333001

出　　处：《南京航空航天大学学报》2014年第6期895-900,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：通过某型燃油系统增压供油转自吸供油试验,研究了发动机入口处的流量历程。在试验研究和直升机燃油系统增压转自吸供油机理基础上,利用Flowmaster软件建立了某典型直升机燃油系统仿真模型,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,研究了直升机燃油系统增压转自吸供油动特性。结合仿真结果,分析了增压泵出口单向阀的弹簧预紧力、弹簧刚度对发动机入口燃油流量、压力的影响,为燃油系统零部件选型及参数确定提供参考。With the experiment of fuel system undergoing the boost fueling to self-suck,the study on history rate of fuel flow is conducted.Based on the experimental study and the analysis of operational principle of transient process of helicopter fuel system transferred from boost fueling to self-suck,a simulation model of helicopter fuel system is built with commercial code of Flowmaster.The simulation results and the experimental results are in a good agreement,which reveals the validity of numerical model.By combining with simulation results,the impact of check valve spring preload and spring rate on engine inlet pressure and flow rate is analyzed.Consequently,the reference of components of fuel system is provided.

关 键 词：燃油系统 增压供油 自吸供油 仿真 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]