Considering the negative effect of the leakage of the labyrinth seal gap close to the stator root on the end-wall in the compressor

a two-stage axial compressor of the stator seal structure was chosen as the research subject. Genetic algorithm (GA) was applied to conduct numerical aerodynamic optimization of this two-stage axial compressor. The optimization variables included the stagger angles and the leading-edge angles of the airfoils close to the hub of the rear-stage stator

and the optimization object was to achieve the maximum isentropic efficiency of the two-stage axial compressor. After the optimization

the isentropic efficiency of the two-stage axial compressor in the design point increased by 0.2 percentage points

and the rear-stage stator obviously showed the end-bend blading close to the hub. The main reason for the improvement of the two-stage axial compressor performance is that after the root airfoils of the rear-stage stator have been modified by the optimization

the incidences of the upstream flow close to the end-wall are located close to the optimal design incidences of these airfoils.