进气畸变对压缩系统稳定性影响的数值模拟

Effect of pressure and temperature distortion orientation on turbine engine stability

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 ,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 ,在一定物理转速和流量条件下的压气机稳态工作点参数则采用级堆叠方法进行计算。对总压畸变、总温畸变等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和进气总温畸变对发动机稳定性有很大的影响 ,畸变进气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。

A numerical model was presented for the prediction of the effects of distortion on the stability limit of the 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 the actuator-lag-volume model was adopted to model the stage of compressor. A stage stacking technique was used to compute the steady flow parameters in axial flow compressor. The variation of aerodynamic stability limit of compressor due to the total pressure distortion, total temperature distortion are calculated and analyzed. The numerical results show that the stability limit of compressor is moved down very much due to the pressure and temperature distortion.