Effects of end-bowed blade and dihedral blade technology on vortex structure and aerodynamic performance in a compressor cascade

In order to study the effects and interaction of the dihedral angle, end-bowed height and angle on vortex structure and aerodynamic performance, the result in an annular compressor cascade were analyzed through orthogonal experimental design. The results show the existence of best dihedral angle to balance the effect on exit total pressure loss distribution of concentrated shedding vortex and corner vortex. The improvement of dihedral angle leads to the weakening of concentrated shedding vortex and the vortex core towards the end wall, while concentrated shedding vortex is enhanced and the core of it is close to the middle span. The change of vortex structure makes the loss decrease in the high loss region and the region gets close to the core of concentrated shedding vortex, while the loss of middle span gets thickening and shrinks to the center. The influence of end-bowed height and angle is more significant on the end region than on the middle span. The improvement of corner vortex strength makes the loss of end region increase, while the movement of concentrated shedding vortex's core leads to the proliferation of loss to the end region from the middle, but the decrease of loss is limited.