Aerodynamic stability assessment for compression component running in turbofan engine with distorted flow

A new model was presented for predicting aerodynamic stability limit of fan component in turbofan engine. Firstly, a quasi one-dimensional, time dependent compression system model was used to model the dynamic flow in compressor and the actuator-lag-volume model was adopted to model the stage of compressor. Secondly, lyapunov stability theory was used to identify the aerodynamic stability of compression component. Finally, this aerodynamic stability numerical model was coupled with steady state thermodynamic cycle model of turbofan for predicting aerodynamic stability limit of compression component in turbofan engine environment. A turbofan engine with 3 stages fan and 5 stages compressor, as an example, was simulated. Numerical results show that in different aerodynamic stability assessment environment the effect of inlet flow distortion on fan and compressor stability limit is different.