Optimization of a Transonic High-Pressure Stage aimed at Coupling with Pressure Gain Combustors

Nowadays the main aim of Gas Turbine manufacturers is the maximization of efficiency and specific power in energy and propulsion applications. One of the innovative methods to achieve such objectives is a modification of the engine cycle with the introduction of new techniques of combustion: Pressure Gain Combustors. Other than thermodynamic performance, such novel designs bear other advantages such as engine compactness and cleaner energy production. On the other hand, Pressure Gain Combustors pose still unanswered questions concerning their interaction with current turbine stages designs. In order to make the most out of these new technologies, it is necessary to re-design High-Pressure Turbine Stages to achieve full integration with the high temperature, supersonic and unsteady flow field out of a Pressure Gain Combustor and avoid excessive aerodynamic losses and machine failures. In this research, a subsonic high-pressure turbine stage has been investigated for future integration with a Pressure Gain combustor. Starting from a low subsonic vane design, new designs have been numerically studied to prevent unstarting at higher inlet Mach numbers. After an initial assessment of the performance of the stage with a varying number of vanes, a numerical optimization has been performed to achieve the highest performance in terms of efficiency and specific power.