Influence of Load Distribution on Aerodynamic Performance of Slotted Compressor Blade
As the flow in aviation compressor blade channel assumes a strong reverse pressure gradient,this paper proposes a new type of slotted blade for the compressor stator blade in order to reduce the flow loss and expand the stable working range.Through the channel,the pressure inlets from the leading edge of the blade and exhales from the suction surface,and the inflow velocity impulse is used to effectively suppress the development of the suction surface and the boundary layer.The influence of controlled diffusion blade slot with different suction surface peak isentropic Mach number positions on the aerodynamic performance of cascade is studied by computer numerical simulation.The results show that under the design condition,slotting can effectively suppress the development of the suction surface boundary layer,reduce the cascade loss and increase the flow angle.The more the position of peak isentropic Mach number of the suction surface is toward the trailing edge,the greater the degree of loss reduction by slotting is in the whole range of inlet angle;the larger the angle of attack is,the thicker the boundary layer on the suction surface is,and the greater the reduction loss of slotting is.
compressorcascadeload distributionslotted blade profileaerodynamic performanceflow control
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