This project wants to investigate the role of the pulsating flow generated by RDE combustors on the performance of a downstream subsonic turbine. The aerodynamics of a turbine vane exposed to combustor-representative unsteady inflow conditions will be experimentally tested in a high-speed cascade rig. VKI will investigate an appropriate geometry of a research uncooled turbine vane. The turbine geometry will be selected from a range of vane designs optimized for operation at high-subsonic inlet Mach numbers (Min~0.6-0.7). Ideally, the vane geometry will be open-access and chosen in consultation with the other research groups (POLITO, TUB, POLIMI and KTH) involved in WP4 for the design, simulation, and testing of subsonic and supersonic turbines. VKI will design and build a dedicated unsteady flow generator mimicking realistic RDC conditions upstream of the turbine. The combustor simulator will be integrated into the existing C-3 high-speed wind tunnel of the VKI for testing the turbine vane cascade over a range of combustor-representative non-dimensional flow conditions. The turbine rig allows testing of large size cascades at transonic Mach numbers and high Reynolds numbers, representative of the operating flow regimes of integrated RDC-turbine systems. The pulsating flow at the exit section of the simulator will be characterized under different operating conditions considering the possibility to vary pulsation frequency, inlet flow speed and direction. Wind tunnel testing will be performed on the linear cascade of uncooled turbine vanes mounted downstream of the simulator. The turbine flow will be measured by means of state-of-art fast-response aerodynamic probes, airfoil surface instrumentation and optical techniques (Schlieren, PIV). The aerodynamics and performance of the vane cascade will be investigated at different pulsating and steady inflow regimes to identify the effects of combustor-turbine interactions. The time-resolved measurements will be used to characterize local excursions to supersonic flows, unsteady cascade starting and unstarting mechanisms and their characteristic time scales, the evolution with the instantaneous vane inlet flow of airfoil boundary layers, wakes and shock interactions.