Abstract: An improvement on Schmidt Patankar low Reynolds number turbulence model by taking into account the favoralbe pressure gradients on the blade pressure surface and the adverse pressure gradients on the blade suction surface is made to simulate heat transfer on turbine blades. Examination calculation is carried out for 18 conditions of six turbine vanes. The parameters are outlet Reynolds number ranging from 0 56×10 6 to 2 73×10 6 ,upstream turbulence intensity ranging from 0 8% to 8 3%,and ratio of wall temperature to stagnation temperature ranging from 0 67 to 0 82. The results show that the predicted heat transfer on the blades agreed well with the experimental data.