Turbofan Engine Aerodynamic Stability Simulation,

The influence of the pressure and temperature distortion to the engine stability is one of important target to evaluate aircraft engine. The fan and compressor is the most sensitive part to the air current. The pressure and the temperature distortion can cause the compressor to lose the stability and enter the buzz. When the engine loses steadily, it can endanger the flight safety directly. The total pressure and temperature distortion is the most factors that influence aero-engine in stablity. This article has developed research about the total pressure and temperature distortion to the engine stability influence.According to the total pressure and temperature distortion question in the aircraft engine using process, this article closely track overseas development tendency and develop one mathematics physical model to evaluate the compressor system stability. A numerical model was presented for the prediction of the effects distortion on the stability limit of compressor in turbine engine. A quas. one-dimensional, time dependent compression system model based on the parallel compressor theory was used to model the dynamic flow in compressor and actuator lag-volume model was adopted to model the stage of compressor. A united method was used to identify the stability of compression system instead of the identification of each segment compressor. The identification of stability of compression system was conducted under the condition when compressors run in engine. The variation of aerodynamic stability limit of compressor due to the total pressure distortion are calculated and analyzed. The numerical results show that the stability limit of compressor moved down very much due to the pressure distortion. The model presented in this paper is reasonable and reliable. The repetition and sensitivity of prediction results were good.