To shorten the turbine aerodynamic design cycle and further explore the potential improvement of turbine blades

an aerodynamic optimization platform of twisted S1 stream surface for multi-stage turbine with advantages of fast speed and short design period was presented. The platform could conduct multilayer parallel optimization for multi-column blades under the premise of cooling air

avoid disadvantage of poor matching between blade columns in single column optimization

and overcome the defect of aerodynamic efficiency shift for multilayer S1 stream surface. A two stage high pressure turbine has been optimized; the results showed that

aerodynamic efficiency considering cooling air of three S1 stream surfaces of 10%

50%

90% blade spanwise height was increased by 0.569%

0.490% and 0.405%

the first stage and second stage aerodynamic efficiency considering cooling was improved by 0.18% and 0.05%

and aerodynamic efficiency considering cooling air of the turbine was increased by 0.15%

showing the significant effect of optimization. The analysis indicated that

the optimization reduced the channel transverse secondary flow loss of first stage stator blades and the shock loss of first stage rotor blades effectively

and the original blade design of turbine second stage was more reasonable. Coolant injection of flow channel hub was the important reason to reduce the effectiveness of S1 stream surface optimization.