航空发动机过失速及退喘模型研究  

Model Research on Post Stall and Recovering from Stall for Aeroengine

作　　者：杨帆[1,2] 胡骏[1] 严伟[1] 

机构地区：[1]南京航空航天大学江苏省航空动力系统重点实验室,南京210016 [2]中国航发四川燃气涡轮研究院,成都610500

出　　处：《航空发动机》2017年第1期41-47,共7页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：针对涡喷和涡扇发动机,通过求解带源项的2维欧拉方程组,发展了模拟发动机整机过失速及退喘动态过程的理论模型,实现了2种发动机稳定状态-喘振/旋转失速-退喘动态过程的模拟。分析了某单轴涡喷发动机算例,模拟结果展现出喘振和旋转失速相应的基本特征;对某小涵道比双轴混排涡扇发动机进、退喘模拟结果进行分析,发现风扇与压气机均发生了喘振,且喘振频率相等,并最终都恢复至稳定状态。Aiming at turbojet and turbofan engine, a theoretical model of the dynamic process of post stall and recovering from stall for the overall unit was developed by solving two dimensional Euler equations with source tenn. The dynamic process from stable state to surge/ rotating stall and recovering from stall of turbojet and turbofan engine was simulated. The example of a turbojet engine was analyzed, and the simulated results can reflect the basic characteristics of surge and rotating stall. The simulated results of enter and recover from the surge on a small bypass ratio-biaxial-mixed exhaust turbofan engine were analyzed. The results show that the fan and the compressor are all entered the surge, and the two frequency of surge are equal. Eventually, the fan and the compressor are all returned to a stable state.

关 键 词：过失速 退喘 喘振频率 航空发动机 压气机 风扇 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]