In view of the complex and variable characteristics of the turbine shroud in actual operat-ing conditions,an impingement-film cooling test platform for turbine shroud with vertical gas-intake and adjustable aerothermal parameters was built in this paper.Infrared temperature measurement technology was used to conduct orthogonal experiment to study the correlation between mainstream Mach number,blower ratio and temperature ratio on turbine shroud cooling characteristics.The results show that the surface average overall cooling efficiency of the turbine shroud presents a trend of decreasing-increasing-decreasing with the increase of mainstream Mach number.In the research range of Mach number is 0.5～0.8,the turbine shroud has the best overall cooling effect when Mach number is 0.6.By increasing the blowing ratio,the impingement and film cooling effects inside and outside turbine shroud can be gained by increasing the cool-gas flow rate and dynamic pressure.When the blowing ratio increases by 0.5,the surface average overall cooling efficiency of the turbine shroud increases by 1.46％～9.08％.When the temperature ratio changes from 1.5 to 1.6,the surface average overall cooling efficiency of the turbine shroud decreases by 0.85％～7.95％.
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