基于实时模型的涡扇发动机加速供油规律设计方法  

Design Method of Fuel Supply Law for Turbofan Engine Acceleration Based on a Real-Time Model

作　　者：韩文俊[1] 李家瑞[1] 王军[1] 王传宝[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2015年第2期1-5,共5页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：针对某型涡扇发动机建立了实时模型,并将实时模型计算与试验结果进行了对比,得出该实时模型对模拟航空发动机加速过程具有一定的精度。通过改变航空发动机加速过程控制逻辑,并引入压气机裕度这一限制条件,获得了1种航空发动机加速供油规律设计方法。在实时模型中采用该方法,能够快速准确地获得航空发动机的加速供油规律;同时能够直观地得到航空发动机加速过程的动态特性。结果表明:通过验算得到设计的加速供油规律符合航空发动机加速要求。The real-time model of a turbofan engine was built, which calculation results were compared with the experimentation results. It is accuracy to simulate the acceleration process of aeroengine. A design method of fuel supply law for aeroengine was obtained by changing the control law of aeroengine acceleration process and introducing the limitation condition of compressor margin. The acceleration fuel law of aeroengine was obtained quickly and accurately, and the dynamic characteristics of aeroengine acceleration process were presented directly by the method in the real-time model. The results show that the acceleration supply law designed by validation and calculation meets the requirements of aeroengine acceleration.

关 键 词：加速供油规律 实时模型 控制规律 动态特性 涡扇发动机 

分 类 号：V231.12[航空宇航科学与技术—航空宇航推进理论与工程]