1) compressor cascade
扩压叶栅
1.
Effects of inlet boundary layar on aerodynamic performance of bowed compressor cascades with large camber angle;
进口附面层对大转角弯曲扩压叶栅气动性能的影响
2.
The surface-flow topology structures of the compressor cascade with groove surfaces were studied using oil-visualization techniques.
采用油流显示技术研究了沟槽面扩压叶栅表面流动的拓扑结构,通过与光滑叶栅壁面流动拓扑图像的比较,发现沟槽面能抑制叶背附面层的发展,减小附面层内低速流体的展向流动,减弱叶背附面层与叶背角区旋涡的相互作用。
3.
The effects of the stacking line shape on the aerodynamic performance of the compressor cascade with the positive curved blades had been simulated numerically.
数值研究了积迭型线构造型式对正弯曲扩压叶栅气动性能的影响。
3) curved compressor cascade
正弯扩压叶栅
4) annular diffusion cascade
环型扩压叶栅
1.
On an annular diffusion cascade experimental wind tunnel detailed measurements of traditional straight, positive leaned, positively curved and S type blades of annular axial flow compressor cascades were carried out under an inlet flow field distortion at near zero incidence.
在环型扩压叶栅实验风洞上对近零冲角进口流场畸变下的常规直叶栅、正倾斜叶栅、正弯曲叶栅、S型叶栅进行了叶片表面静压测量,分析了不同的弯曲叶片对表面静压分布的影响。
5) staggered arrangement cascade diffuser
错排叶栅扩压器
6) Compound Lean Compressor Cascade
弯曲扩压叶栅
1.
Investigation on Aerodynamics Performance of Application Slot Injection Technology in Compound Lean Compressor Cascades
采用缝隙射流技术的弯曲扩压叶栅气动性能研究
补充资料：冲击波超压与动压