Accurate and reliable turbulence and transition models are needed for prediction heating loads in the hot section of the turbine, and predicting aerodynamic losses when designing new blade profiles. Two dimensional compressible flow simulations were conducted at North Dakota State University on a first stage turbine vane design. Surface pressure results were compared with experimental data collected at the University of North Dakota. Results showed an under prediction of the surface pressure on the suction surface of the vane. Two and three dimensional compressible flow simulations were also conducted at NDSU on an incident tolerant blade design to look at the effect of incidence angle, Reynolds number, and turbulence intensity on transition. Results from these simulations were compared with experimental data collected at UND. The results show good agreement at higher Reynolds numbers with discrepancies being seen on the suction surface of the blade at lower Reynolds numbers.