全场辐射下涡轮导叶耦合换热特性的多参数影响研究

With the aviation industry and gas turbine manufacturing industry increasing the inlet gas temperature of turbines to improve their work efficiency，the impact of thermal radiation on the wall temperature of turbine guide vanes is becoming increasingly severe. Through numerical simulation，the multi-sensitive parameters of radiation heat transfer in turbine guide vanes were studied. The Weighted Sum of Gray Gases Model calculation principle was used to analyze the influence of radiation heat transfer on the temperature distribution of the outer surface of turbine guide vanes under different parameters. The distribution of radiation contribution of vane media was also calculated using effective radiation. The results show that the inlet blackbody radiation temperature has the greatest impact on the temperature changes at the leading edge and pressure surface of the vane，and the temperature difference is more significant in the area covered by the gas film. As the inlet blackbody radiation temperature increases，the contribution of the medium radiation to the blade is greater，with the most significant contribution at the two exhaust film holes at the leading edge. The outlet radiation intensity is the most influential factor on the radiation heat transfer of the blade，followed by the influence of high-temperature gas components on the radiation heat transfer of the blade. The surface temperature of the blade is positively correlated with the emissivity，and at an emissivity of 0.5，the medium radiation contribution at the leading edge and the leading edge gas film hole is the highest. At an emissivity of 0.2，significant medium radiation is received at the pressure surface gas film hole and the trailing edge slot.