Effect of Asymmetric Leading Edge on Aerodynamic Performance of Diffusion Cascade

The leading edge plays an important role on compressor performance. The typical profile shapes of leading edge are mostly symmetric, and there is less research on the asymmetric leading edge. In order to explore the effect of asymmetric leading edge on the aerodynamic performance of diffusion cascade, the SST turbulence model coupled with γ - Re_θ transition model was used to numerically study a controlled diffusion airfoil cascade with asymmetric leading edge. The results showed that, compared with the circular leading edge, the asymmetric leading edge reduced the suction peak strength by 21.8% at the inlet angle of 50.83 degrees, and the leading-edge separation was controlled. The laminar flow was maintained, and the total pressure loss was reduced by 54.8%. By expanding the suction surface side leading edge space, the asymmetric leading edge reduces the large curvature distribution range and improves the excessive expansion, thereby having better aerodynamic performance.