Effect of pressure and temperature distortion on turbine engine stability

A numerical model was presented for prediction of the effects distortion on the stability limit of compressor in turbine engine. A quasi 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 were calculated and analyzed. The numerical results show that the stability limit of compressor is 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 are good.