Abstract: A compressor cascade was tested in a low speed two dimensional cascade wind tunnel.The measurements of flow field on blade surface were made at the cascade inlet and exit.Boundary layer development was analyzed under different inlet flow conditions.The pressure gradient on blade surface and their effects on transition from laminar flow to turbulent flow was studied numerically at different inlet Mach numbers and incidences.By means of the experimental data,the viscous boundary layer transition on blade surface was studied in detail.It is very helpful for better understanding of the complex boundary layer transition mechanics.

Key words: Compressor cascade;Boundary layer flow;Flow distribution;Transition flow;Influence factor;Experimentation;Numerical simulation

摘要： 以平面叶栅中的二元叶栅模型为试验对象，测量了在不同来流条件下叶片表面流场分布情况及栅后气流参数，分析了不同来流条件下叶片表面附面层流动状态的变化。并借助数值模拟手段重点研究了在不同来流马赫数和冲角下，叶片表面压力梯度对层流附面层向紊流附面层转捩过程的影响，通过利用实验数据分析研究来流条件对转捩过程的影响，为从机理上更深刻地认识叶片表面粘性附面层转捩机制提供了科学参考依据。

关键词: 压气机叶栅;边界层流;流动分布;转捩流;影响因素;实验;数值仿真