进气畸变在风扇/压气机内传递的数值研究

On Improving the Understanding of Transfer Process of Inlet Pressure Distortion in Axial-Flow Fan/Compressor

发展了准三维压气机流程分析模型 ,实现了对进口流场畸变在压气机内的传递和总温生成系数的数值模拟。对某型发动机三级风扇的数值计算表明 ,进口流场畸变经过压气机通道传递 ,畸变扇形区的位置和形状均发生了明显变化 ,这说明通常使用的古典平行压气机理论是不完善的 ;进口总压畸变沿着压气机通道是逐渐衰减的 ,叶尖区的畸变衰减比叶根处衰减得快。而在叶尖处的总温畸变生成比叶根处的总温畸变生成得大。

Davis's model has been and is still widely used, but it is not quite satisfactory for understanding the transfer process of inlet pressure distortion in axial-flow fan/compressor. A quasi three-dimensional model is proposed to use to improve such understanding. The quasi three-dimensional model takes into consideration the radial momentum equation and circumferential momentum equation and describes the flow field in axial-flow fan/compressor. Cascade experimental data were used to describe the flow through blade row. We used a two-dimensional small perturbation model to accelerate convergence. The numerical simulation results of a three-stage axial-flow fan/compressor with inlet pressure circumferential distortion show that: the position and configuration of the distortion cell are both changed when it passes through axial-flow fan/compressor; the decay of total pressure distortion at tip is faster than that at the hub; the total temperature circumferential distortion generating coefficient at hub is larger than that at the tip.