发动机轴流压缩系统逐级模拟技术  

Modeling technique for stage by stage axial flow compression system

作　　者：郁新华[1] 廉小纯[1] 吴虎[1] 张丽娟 

机构地区：[1]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《推进技术》2000年第1期39-41,共3页Journal of Propulsion Technology

摘　　要：基于轴流压气机逐级过失速特性,建立了一个能够显示压缩系统喘振和旋转失速等过失速行为的一维非定常逐级模拟技术,发展了分析轴流压缩系统过失速响应的动态滞后方法。并将该模型应用于国内某型号的高转速、双转子压缩系统的过失速行为的分析,讨论了时间滞止常数、燃烧室对压缩系统失速行为的影响,得到了合理的定性结果。Based on method of characteristics, a stage by stage axial flow compression system model was established which can predict the post stall behaviors such as surge and rotating stall A first order lagging method is used to simulate the compressor dynamic response during post stall conditions The modeling technique was applied with a dual spool,high speed,high pressure compressor typical of today's turbine engine to analyses the effects of time constant,combustion on post stall behavior It showed that the numerical results compare favorably with previous results

关 键 词：旋转失速 喘振 数值模拟 航空发动机 压缩系统 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]