Numerical simulation on a three-dimensional twisty high-pressure gas turbine guide vane with the whole body coolant injection was conducted. Detailed analysis of different coolant injection rate affect the blade aerodynamic performance

cooling efficiency and cascade channel loss was performed at the condition of design speed. Comparative analysis was made to learn the influence of changed rotational speed on the performance of turbine stage at the same coolant injection rate. The results show: different coolant injection rate affect static pressure near holes area more obviously

while the impact on the downstream of rotor surface static pressure is very little. Guide vane coolant injection has less influence on the mainstream flow angle in the cascade channel. Coolant injection rate increased from 2.50% of main flow rate to 6.25%

the adiabatic temperature of the blade surface dropped by 11.19%

total pressure loss and energy loss of guide vanes cascade channel increased 12.95% and 12.01% respectively

while the turbine stages power and efficiency dropped by 2.39% and 1.51% respectively.