In order to obtain a more suitable blade profile for compressor stator to reduce aerodynamic loss

the blade profile at mid-span of stator was extracted. The loss characteristics of the original blade profile were obtained through linear cascade experiment

finding that the aerodynamic loss of original blade profile was relatively high

making it necessary to match the design parameters properly to reduce the loss. For this reason

a numerical optimization platform was built to search for blade profile with lower aerodynamic loss in constrained design space. The objective function was constructed by taking the total pressure loss coefficient at multiple incidence angles into account to improve the design and off-design performance. The optimization results showed that

the value of objective function was reduced by about 9%. Further experimental studies showed that the optimized blade profile had lower total pressure loss coefficient than the original one in the whole Mach numbers and incidence angles involved in the experiment. The total pressure loss coefficient in the design condition was reduced by 31.3% compared with the original one

and the stall resistance capacity of the blade profile near positive incidence angle boundary was improved

the airflow inflection angle increased by 1° at the design inlet Mach number with an incidence angle of 4°. The mechanism of blade profile performance improvement was explained through in-depth analysis of experimental results

and suggestions for the design and multi-objective optimization of blade profiles working in similar environment were given.