进气畸变对发动机压缩部件气动稳定性的影响

发展了一种在发动机环境下评定航空涡轮发动机压缩系统稳定工作边界的数学物理模型。压缩系统模型采用基于平行压气机理论的准一维时间相关模型方程以及激盘-滞后-容积的压气机级模型，稳定性模型则采用了对整个压缩系统统一判别的方式。计算过程与发动机非设计点性能计算相关联，使得压缩系统稳定性分析在真实的发动机运行环境（调节规律）下进行。研究了进气畸变对航空燃气涡轮发动机压缩系统稳定工作边界的影响。对总压畸变进气条件下压气机稳定工作边界的变化进行了计算分析，结果表明，进气总压畸变对发动机稳定性有很大的影响，使得压气机稳定工作边界在压气机的特性图中向右下方移动，降低了发动机的喘振裕度。发展的数学物理模型可以正确地反映发动机压缩系统的工作状况，用它判断发动机不稳定工作点的重复性和灵敏度都比较好。

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.