In aircraft engines, especially in turbomachinery components, large part of the flow along the surface is laminar or transitional. The boundary layer development, losses, efficiency and heat transfer are greatly affected by the location and extend of the laminar-to-turbulent transition. The accurate prediction of the transition process is necessary for the design of efficient and reliable machines. The accuracy of current models to predict the transition location and extend is limited. In the present work curvature effects are implemented in a flow solver developed at Stanford University in order to improve predictions of turbulent transition over a gas turbine blade.