The aim of the activity is the design of optimized high-pressure vanes integrated in transition ducts to allow for the high-performance coupling to rotating detonation combustors. In details, boundary conditions obtained from the test rigs analysed in H2POWRD will be used to design a subsonic vane, thus providing realistic design solutions to partners working experimentally on the turbine module. The subsonic solution will be designed in cooperation with VKI, who will analyse a subsonic vane. Target boundary conditions will be defined and used by POLITO to design the ducts and by the experimental partners to design the devices that will mimic the pulsating condition in the test rig. The design procedure aims at reducing fluctuations from the rotating detonation engine, at designing a vane mostly insensitive to the inlet angle fluctuations, and at obtaining the highest possible aerodynamic efficiency of the vane by weakening the losses associated to the unsteady development of secondary flow structures and shocks. As far as the latter are concerned, a solution based on end-wall contouring and vane optimization will be initially designed. A flow control solution will hence be added by considering unsteady blowing of coolant that both energizes the boundary layer and shields the metal parts that are subject to high temperature levels. The subsonic solution without flow control will be manufactured and analysed by TUB in a dedicated campaign. A rotor row will be selected or designed for the duct/vane geometry to numerically evaluate stage performance.