某减压阀高压冲击超调问题仿真分析与试验研究  

Simulation and experiment research on high-pressure shock overshoot phenomenon of pressure reducing valve

作　　者：朱建国[1] 魏学峰[1] 孙亮[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2015年第5期72-76,共5页Journal of Rocket Propulsion

摘　　要：针对某正向卸荷式气体减压阀高压冲击时出口压力超调和振荡现象,通过AMEsim仿真软件建立减压阀以及增压系统的仿真模型,对比分析了阀芯开度、限流圈、管系对出口压力的影响,确定了以减小阀芯开度和增加阀前限流圈的综合技术措施减小出口压力超调和振荡。通过单机高压冲击试验和整机试车考核,改进后的减压阀出口压力建压平稳、无超调现象、无明显振荡,解决了工程研制问题。本文研究结果表明,减小减压阀阀芯开度、在阀前增加限流圈的技术措施,对于提升减压阀抗高压冲击能力具有一定的通用性,对其它超高压气体减压阀设计具有指导意义。In allusion to the overshoot and oscillation phenomena of a certain forward unloading pressure reducing valve, caused by high-pressure shock, the dynamic simulation model of pressure reducing valve and pressurizing system was established with AMEsim software. The influence of valve spool opening, current-limiting orifice and pipe on exit pressure is analyzed. The technical measures of adding the current-limiting orifice in front of valve and reducing the valve spool opening are confirmed to reduce the exit pressure effectively. The engineering development problems were solved with these technical measures, which passed the evaluation by high pressure shock test and overall system test. The exit pressure of the improved valve is smooth, and has no overshoot and obvious oscillation phenomena. The results show that the technical measures are general-purpose for improving capability of resist high-pressure shock, and have guiding significance for design of the extra high-pressure reducing valve.

关 键 词：高压冲击 振荡 超调 仿真分析 试验研究 

分 类 号：V432[航空宇航科学与技术—航空宇航推进理论与工程]