航空涡扇发动机全包线平衡流形建模

Whole flight envelop corrected equilibrium manifold modeling for a turbofan engine

根据航空发动机相似工作状态原理和非线性系统平衡流形建模原理,提出一种适用于全飞行包线发动机性能仿真的换算平衡流形模型.首先,根据发动机各状态量的换算参数,对航空发动机平衡流形的概念进一步推广,提出换算平衡流形概念.然后,选取高压转子换算转速和飞行马赫数定义二维调度变量,对全包线发动机参量换算平衡流形进行拟合;并在换算参数意义下,建立某型涡扇发动机全包线换算平衡流形模型.最后利用该模型对不同条件下发动机转速调节过程进行仿真,并与发动机部件级非线性模型对比,检验了模型良好的计算精度和实时计算性能.

Based on the aero-engine resemble theory and the nonlinear system equilibrium manifold theory,a corrected equilibrium manifold modeling method for aero-engine＇s simulation in whole flight envelop was put forward.First,according to the corrected variables,by extending the concept of equilibrium manifold,corrected equilibrium manifold was presented.Then,a two-dimension schedule variable was defined though compressor rotor＇s corrected speed and Mach number,and was used to fit the corrected equilibrium manifold.Next,following the modeling frame of nonlinear system equilibrium manifold theory,a whole flight envelop corrected equilibrium manifold model for a turbofan engine was presented.Last,some simulation about this turbofan engine＇s dynamic response at different situations were shown,and were accordant with the corresponding result of this turbofan engine＇s component nonlinear model.In all,this model in this paper exhibites well about applicability,precision and real-time simulation for a turbofan engine.