Abstract: First-stage stator blade of 9HA.02 gas turbine was calculated using a model that combined zero-dimensional semi-empirical model and quasi-one-dimensional expansion model. The results are verified and the key parameters in the quasi-one-dimensional model are checked to reduce the uncertainty caused by the selection of empirical parameters. Then, the parameter analysis is carried out to determine the cooling technical level parameter Z, the uniform blade temperature T_bu, and the cooling air amount under the condition that the inlet temperature of the main gas is given. The cooling parameters are compared with those of PG9351FA gas turbine. Since the 9HA.02 gas turbine adopted a new directional solidification single crystal alloy material, the maximum allowable temperature difference between the first-stage stator and the remaining cooling turbine blade reach 200℃. The maximum allowable temperature of the first-stage stator blade is 1090℃, which is significantly higher than that of the F-class gas turbine. The calculation results show that the cooling technology level of H-class gas turbine is greatly improved compared with that of F-class gas turbine. The first stator cooling air of 9HA.02 gas turbine accounts for about 1/4 of the total cooling air amount, which is markedly lower than the 1/3 of F-class gas turbine.