进气畸变对发动机压缩系统稳定性影响的数值模拟

介绍了一种在发动机环境下评定航空燃气涡轮发动机压缩系统稳定工作边界的数学物理模型。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。主要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 the prediction of the effects distortion on the stability limit of compressor in turbine engine. The identification of stability of compression system was conducted under the condition when compressors nm in engine. The varia- tion 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 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 were good,