Redesign of counter-rotating compressor with boundary layer suction

Boundary layer suction and blade optimization are employed in the redesign of a dual-stage counter-rotating compressor with numerical simulation. Further experimental research will be carried out according to the numerical results. At near stall point, there is serious flow separation at the tip region of the original outlet guide vane (OGV). Airfoil optimization makes smooth acceleration at the leading edge, and decreases the recirculation zone in the blade passage. Up to 70% spanwise of OGV, total pressure loss coefficient has a 38.4% drop in average. Isentropic efficiency of the compressor is improved by 0.3%. An axisymmetric suction slot located at 66% chordwise of Rotor 2 (R₂) tip region with 1 mm width is designed at the shroud case. 1% comparative mass flow at near stall point can optimize the loading level of R₂ tip region, bringing a 10% improvement in average on R₂ isentropic efficiency in higher spanwise from 65%. These result in a positive effect on the flow condition of the OGV: corner separation is limited to a smaller region, total pressure loss coefficient has a 25% drop in average in the region up to 85% spanwise, and the isentropic efficiency of the compressor is further improved by 0.5%.