A study was undertaken to improve the prediction of heat transfer coefficients on the suction surface of turbine blades. The study specifically investigated the effects of coupling turbulent Prandtl number models with boundary layer transition models. A two-dimensional boundary layer code, STAN5, was selected and the turbulence model modified by incorporating several turbulent Prandtl number and boundary layer transition models found in the literature. Results indicated that subtle effects were attributable to the modified turbulence model. However, desired improvements were not obtained in the heat transfer coefficient predictions. It appears that boundary layer transition models predicting natural transition are not appropriate for use in a turbine blade flow field.