Numerical Optimization of a High-Pressure Turbine Vane and End-Wall with High Inlet Mach Number

The studies on innovative methods to achieve the maximization of the efficiency and specific power in the fields of energy production and propulsion brought to a modification of the conventional thermodynamic cycles: Pressure Gain Combustors (PGCs) are based on the introduction of new methods of combustion. The conventional and existing turbine configurations show some issues concerning the interaction with PCGs, in particular for Rotating Detonation Engine (RDE): it is necessary to re-design the High Pressure Turbine Stage in order to achieve a greater integration with the unsteadiness of the flow field out of a PGC. During this analysis, the nominal configuration of two conventional turbine vane profiles is considered as the starting point to perform a Numerical Optimization in order to maximise the vane efficiency, ensuring an inlet Mach number not too much far from 0.6. More than one optimization method will be performed in order to better understand how does the optimization work and to find with more than one approach the optimal configuration to be coupled with a Rotating Detonation Combustor.