Effect of Camber on Non-axisymmetric End-wall Contouring Performance in Compressor Linear Cascades

In order to explore non-axisymmetric end-wall's mechanism of secondary flow control in compressor cascade, based on three-dimensional numerical calculation, this paper analysed effects of camber on non-axisymmetric end-wall contouring performance in compressor linear cascades. Results showed that non-axisymmetric end-wall reduces the corner separation loss mainly by suppressing the interaction between the crossflow and the suction surface boundary layer and decreasing the adverse pressure gradient on suction surface. Meanwhile, non-axisymmetric end-wall partly enhances the cross flow, increasing the secondary flow loss. At the incidence of 0°, the increase of the secondary flow loss caused by the non-axisymmetric end-wall plays the leading role when the camber angle is 20°; with the increase of camber angle, the reduction of corner separation loss becomes the leading role. At the incidence of 7°, the hub-corner stall is removed by the non-axisymmetric end-wall when the camber angle increases to 40°, decreasing the loss remarkably.