A number of turbulence models were employed to investigate the heat transfer and aerodynamic characteristics through a nozzle cascade of a high-pressure gas turbine. Isentropic Mach number and Nusselt number around the vane were predicted and compared to existing experimental data obtained at a supersonic flow condition. According to the result presented by different models, possible source of the prediction error was identified: and the performance of different turbulence closures in predicting the heat transfer characteristics around the vane was discussed. It shows that the calculated heat transfer result was affected directly by the predicted turbulence transportation throughout the boundary layer. Finally considering the computational cost and the performance of the models, the suitable model(s) are recommended for the further 3D applications. (C) 2012 Elsevier Ltd. All rights reserved.