A series of systematic computational studies have been conducted for transonic HPT nozzles and blades to evaluate the impact of free stream turbulence on boundary layer growth and downstream wake mixing. Transition modeling is first compared to measurements for an uncooled nozzle. The computational results are compared against measurements of loading, HTC, and wake predictions. The approach is then applied to a cooled trail-edge nozzle. The added complexity of cooling flow injection at the trail-edge showed an increase in deviation between the SST Transition model predictions and wake measurement. By applying a scale resolve model (WALE LES), wake mixing predictions are found within 1% of measurement. Finally, the computational approach is extended to a coupled uncooled nozzle/blade stage analysis. Given the favorable results for an uncooled nozzle using the SST transition model, preliminary assessment of boundary layer impact on HTC and the overall stage loss was made for the nozzle/blade stage design.

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