Investigation of the optimization design of the axial fan stator based on the optimal load distribution coefficient

Driven by the demand for higher thrust-to-weight ratios in modern aero engines, challenges have arisen in enhancing fan and compressor performance through increased load and linear velocity. This study investigated the optimal load distribution coefficients for various blades across different inflow Mach numbers and subsequently reselected the load distribution coefficients along each section of a transonic fan stator, achieving geometric optimization and modification. The stator's weight was reduced by 15%, while the total pressure ratio remained nearly unchanged. Improvements of approximately 0.29% in peak efficiency and 1.26% in stall margin were attained. Comprehensive flow field analyses revealed the flow mechanisms underlying these performance gains at both peak efficiency point and near stall point conditions. Despite the aerodynamic benefits of the front-loaded design, intensified corner separation at the stator root was observed in three-dimensional flows lacking significant meridional acceleration. It is suggested that applying a load distribution coefficient below 1 at the stator root can mitigate corner separation and the development of passage vortex, thereby enhancing aerodynamic performance and stall margin.