低温推进剂火箭发动机循环预冷系统喷泉非稳现象的数值研究  

Numerical study on geysering instability in circulating precooling system for cryogenic propellant rocket turbopump

作　　者：郭宁[1] 匡波[1] 张中伟[1] 黄辉 田玉蓉 

机构地区：[1]上海交通大学机械与动力工程学院,上海200240 [2]北京宇航系统工程研究所,北京100076

出　　处：《低温工程》2013年第2期24-35,共12页Cryogenics

基　　金：国家自然科学基金(No.51076091)资助

摘　　要：通过数值模拟,分析了低温推进剂(液氧)火箭发动机循环预冷系统中喷泉非稳现象的过程与机理;计算分析了不同影响因素下的喷泉现象及行为规律;同时,参照针对竖直立管的喷泉失稳边界Murphy曲线,对比探讨了输送管几何与保温参数影响下的自然循环预冷回路的喷泉稳定性边界;进一步地,针对特定循环预冷回路,数值分析并验证了消除喷泉效应的有效措施。Unstable phenomenon and basic mechanism of geysering in a circulating precooling system for liquid oxygen propellant rocket turbopump were analyzed through numerical simulation. The geysering behaviors and related variation rules under various influencing factors were studied. Meanwhile, referring to the Murphy curve which was in connection with geysering stability margin in an vertical riser, a geysering stability margin curve of a natural circulating precooling loop under different geometric and heat insulating conditions were deduced and discussed comparatively. Furtherly, several practical geysering-inhibiting measures for specific circulating precooling loop were numerically investigated and validated.

关 键 词：喷泉 自然循环 低温推进剂火箭发动机 循环预冷系统 稳定边界 消除措施 

分 类 号：TB657.3[一般工业技术—制冷工程]