Effect of blade bowing and local modification on high-turning angle compressor stator performance;

By using of numerical simulation,the effect of applying boundary layer suction on end-wall to the aerodynamic performance for a van with a high-turning angle and meridional divergence was discussed.

The experimental study of curved compressor cascades with large camber angles at different incidences shows that the curved compressor cascades establish obvious opposite "C" type pressure distribution along the blade height on the suction section, which helps move the low energy fluid from the two endwalls to the midspan.

To have a better understanding of how air injection slot position affect surface pressure and surface streamline, a detailed experimental investigation has been undertaken in a large camber angle compressor cascade with air injection slot.

Experiments of a large turning angle linear compressor cascade with air injection slot were carried out,and detailed outlet flow field characteristics at design incidence were described in this paper.

To further discuss the application conditions of bowed blade in compressor, with incidence equal to zero and other boundary conditions unchanged, a computational investiga- tions on four series of linear stators with different aerofoil turning angles are achieve.

Through a numerical simulation investigated is the impact on the cascade performance of the curved height and curved angle in a curved diffuser cascade having different turning angles.

A experimental investigation was performed for two different turbine cascades with high-turning angles of 113°and 160°.