摘要
航空活塞发动机涡轮增压技术的应用大幅增加了动力系统的复杂性,与增压器相关的安全问题日趋严峻。以某型航空活塞发动机及其两级增压器为对象,聚焦失效诱因的判断方法研究,在建立的整机系统模型基础上,提出一种改进的对应分析法实现对增压器失效模式关键影响因素的分级。结果显示:通过列轮廓坐标随关键影响因素的数值偏离程度表明影响大小的分级方法,可以有效辨识出失效的关键影响因素,废气阀直径是影响各工作边界安全裕度的首要因素,需首先加以控制。
Using turbocharging technology dramatically increases the complexity of piston engine systems and the safety issues associated with turbocharger are becoming urgent.A typical two-stage turbo supercharged piston engine is considered and the judgment method for failure of incentives is focused in this study.Based on the built whole engine system model,a modified correspondence analysis method is proposed,which implements the classification of factors on the failure modes.The results show that the key influence factors and potential causes of coupling failure for turbo supercharged piston engine in actual motion can be judged through changed column contour coordinates in proposed classification method.The test presents that the diameter of exhaust valve is the dominant factors for safety margin boundary and needs to be controlled primarily.
作者
鲍梦瑶
丁水汀
李果
BAO Mengyao;DING Shuiting;LI Guo(Civil Aviation Management Institute of China,Beijing100102,China;Beijing Key Laboratory of System Safety on Aircraft/Engine,Beihang University,Beijing100083,China)
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2019年第6期1071-1080,共10页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金委员会-中国民航局民航联合研究基金(U1833109)~~
关键词
涡轮增压器
关键影响因素
系统模型
对应分析法
影响因素分级
turbo supercharger
key influence factors
system model
correspondence analysis method
classification of influence factors
