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.