Abstract: Abstract. The goal of this study was to develop a highly cooled, turbine nozzle designed for use in extremely high temperatures exhausting from a hydrogen-fueled combustor. This design was based on the nozzle being ...

Abstract: Abstract. This study evaluated the overall cooling effectiveness of a newly designed turbine airfoil using optimized internal and external cooling features. A symmetric airfoil, which incorporated advanced cooling schemes ...

Abstract: Abstract. Compressible flow fields associated with engine realistic high-speed conditions can have a significant impact on the performance of shaped film cooling holes in gas turbines. Such flow fields are dependent upon ...

Abstract: The overall cooling effectiveness for gas turbine airfoils is a function of the combined cooling due to internal cooling configurations and film cooling configurations. Typically, film cooling configurations are evaluated ...