Effects of blade positive curving on aerodynamic performance of compressor cascades

To investigate the influence of the blade positive curved angle on the performance of compressor cascade, experiments were conducted in a low speed wind tunnel with planar cascade. Rectangle compressor stator cascades consisting of four types of blades with controlled diffusion airfoils were tested. These include: Straight blades, positive curved angle 15°, 20°, and 25° blades. The distribution of energy loss coefficient and vorticity at all cascade qxits and static pressure coefficient on blade surface are acguired. The results show that the loss of curved blade cascade is reduced. When the degree of curved angle is 20°, the loss of the cascade is least, and it is 16.15% less than the straight blade cascade. On suction surface of positive curved blade, the C type static pressure distribution is created, and this distribution is enhanced with the increase of the blade curved angle.