For a film-cooled first stage turbine vane

gas-solid-thermal coupled simulation was used to analyze the effect of radiation factors on the temperature distribution and cooling efficiency by comparing the temperature ratio and cooling efficiency with consideration/without consideration of the radiation heat flux over the vane. It showed that when the inlet blackbody temperature changed from 1200K to 1900K and the emissivity of vane surface changed from 0.3 to 0.7

the vane surface temperature increased obviously while considering the effect of radiation factors. When the inlet blackbody temperature was 1600K and the surface emissivity of the blade was 0.5

the temperature rise of the pressure surface was about 100K

and the maximum temperature（1350K） of the blade surface increased about 50K. The gas radiation caused about 5% temperature rise on the surface of suction side and trailing edge. The cooling efficiency decreased while considering the thermal radiation

the vane leading edge and pressure surface were not able to meet the cooling requirements even though the gas film holes were close together

the overall cooling efficiency reduced to 0.3 or less.