Study on the Design Method of a New Type of Compressor Slotted Blade

Abstract

the compressor has been developing towards the direction of high pressure ratio, high efficiency and wide stability margin. The flow in the air compressor blade channel presents a strong inverse pressure gradient. In order to reduce losses and improve the stability of the pressure aircraft, this paper adopts a slot structure from the leading edge of the blade to the suction surface. Air is injected from the front edge of the blade and discharged from the suction surface. The automatic optimization method is used to design the slot. The results show that the blade profile with inlet Mach number 0.4 and the diffusion factor 0.6, the total pressure loss of slotted blade profile is lower than that of unslotted blade profile, and the airflow Angle is greater than that of unslotted blade profile in the whole range of low loss incident Angle. In the incidence of 0 degree, due to the control effect of slotted jet on the boundary layer of the blade suction surface, the boundary layer separation zones on the blade suction surface becomes smaller and the wake also decreases, so the total pressure loss of the slotted blade profile decreases by 37%. When the incidence angle is 4°, the separation area of the suction surface boundary layer is larger, and the slotted jet has a better control effect on the boundary layer of the blade suction surface. However, When the incidence angle is -6°, boundary layer separation zones on the suction surface becomes smaller, and the boundary layer separation zones appears on the pressure surface, so the slotting effect is poor.