Influences of a kind of groove-blade on the flow field in a compressor cascade

This paper presents an experimental investigation of effects of a kind of streamwise-grooved blades on the flow field in a compressor cascade. The flow field downstream the cascade and the boundary layer on the suction surface were measured using a mini 5-hole pressure probe at different incidence angles. The flow field in the groove cascade was compared with that in the smooth cascade. The measurement results indicate that: (1) the groove surface can restrain the development of the boundary layer on the suction surface; (2) the grooves can restrain the radial migration of the low-energy fluids in the boundary layer on the suction surface; (3) the groove blades can reduce total pressure loss and flow blockage in the cascade at the incidence angles of 0°, 5° and 8°; (4) the maximum benefit of 8.6% loss reduction was obtained at the incidence angle of 5° while negative benefit of -3.0% loss reduction occurred at the incidence angle of -5°.