双工况流量调节阀的设计与试验  

Design and experiment of two-stage flow control valve

作　　者：李君海[1] 俞南嘉[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2013年第1期219-225,共7页Journal of Aerospace Power

摘　　要：介绍了一种双工况流量调节阀的原理与设计方法,利用上游贮箱压力作为控制气调节阀芯位移,控制阀门开启与工况调节,实现飞行用挤压式供给系统的启动以及流量快速调节.分析了阀门关键设计参数:敏感元件外径、弹簧刚度和初始压缩量对阀芯位移的影响;通过试验验证了阀门的压降损失在2种工况下能分别保持固定值;对采用该阀门的供给系统进行了试验,试验中阀门开启迅速,成功实现了氧化剂供给系统的流量调节,其中第1工况阶段流量约4.5kg/s,第2工况阶段流量为2.0kg/s,工况转换较迅速,达到了预期值,这说明阀门的原理和设计方法是可行的.Principle and design methods of a new two-stage flow control valve were presented.Tank pressure was used to regulate the motion of the valve to open the valve and change the work status.The pressurization feeding system started and changed the mass flow rate of the oxide as the valve worked.The key parameters of the valve,including key part＇s outer diameter,the stiffness and initial compression of the spring,were analyzed.The tests show that the coefficients of local pressure loss of the valve were same at different working statuses.Experimental results for the feeding system using the valve were obtained.In the tests,the valve opened quickly and the feeding system changed the mass flow successfully.In the first stage,the mass flow rate of the hydrogen peroxide was 4.5 kg/s.In the second stage,it was 2 kg/s.It is proved that the design and test methods of the valve are feasible.

关 键 词：阀门 流量调节 压降损失系数 供给系统 变推力发动机 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]