Effect of Positions of Peak Isentropic Mach Number on Suction Surface of Controlled Diffusion Airfoils on Aerodynamic Performance of Cascades
The isentropic Mach number distribution on the airfoil surface of a subsonic compressor generally complies with the law of controlled diffusion,and the aerodynamic performance of cascades in front peak Mach number position on the suction surface is satisfactory.Designs a controlled diffusion airfoils with given suction surface peak isentropic Mach number position by automatic optimization technique,and analyzes the effect of its positions on the aerodynamic performance of the cascades.The results show that the controlled diffusion rotor and stator airfoils,when the peak isentropic Mach position of the suction surface is 0.20,times the axial chord length under the design condition,the boundary layer of the suction surface develops rapidly along the flow,resulting in a large increase in cascade loss.When the position of the peak isentropic Mach number on the suction surface is ranging from 0.10 to 0.15 times the axial chord length,the inlet angle at design point is approximately in the middle of the operating range,and lower loss is expected in the operating range.
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