To deepen the knowledge of endwall flow in the large-scale low-speed axial compressor

reduce accordingly its flow loss and improve its aerodynamic performance

numerical simulation and optimization were presented. With numerical tool

three-dimensional stacking principle was optimized to improve the design operation point aerodynamic performance for the prototype rotor of a large-scale low-speed axial compressor in low speed simulation. Results show that

near-hub region of the optimized rotor cannot undertake large blade loading; compared with the prototype rotor

the main region of performance improvement of optimized rotor locates near the hub region

and a certain degree of positive bend in this region effectively helps to reduce its flow loss. It shows the effect of “loaded leading edge”

which suppresses flow separation near the trailing edge; consequently nearly 19.4% of total pressure loss is reduced.