Research on the optimization of the leading edge for transonic airfoil of axial flow compressors

DOI:	10.11809/bqzbgcxb2023.03.035
Keywords:	axial flow compressor; transonic airfoil; leading edge ellipticity; optimized design
Abstract:	The geometry of the leading edge of the blade shape directly affects the overall aerodynamic performance of an axial flow compressor. In order to investigate the optimal interval variation of the leading edge ellipticity, this paper optimizes the design of the mid section of transonic airfoil Stator35. Based on a parametric method and a meta heuristic algorithm, an optimization seeking model of the leading edge ellipticity of the blade is established, and the aerodynamic performance of the circular and elliptical leading edge blades is discussed. The flow field structures of a variety of elliptical leading edge blades are compared and analyzed, and the aerodynamic optimization of the three dimensional elliptical leading edge blades is carried out. The results show that, under a full range of operating conditions, the elliptical leading edge blades reduce the total pressure loss coefficient, widen the 3° angle of attack and improve the performance of trailing and turning angles. It is clarified that there is an optimal ellipticity interval ［0.8, 0.9］ for the elliptical leading edge design of transonic airfoil, and the distance between the turning point and the leading edge is negatively correlated to the separation bubble length. After optimization, the adiabatic efficiency of the elliptical leading edge blades at the design point increases by 0.4%, which is higher than the original blades in the full flow range, and the surge margin increases from 9.8% to 12.4%.
Published:	2023-03-28
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