A fundamental difficulty associated with turbomachinery integration in the rotating detonation combustor is the transonic, highly unsteady, high temperature, combustion exhaust gas that have a detrimental effect on turbine operability. In order to mitigate these effects, several options are available. The first is to accelerate the RDC exhaust gas into an exclusively supersonic regime, and realize the coupling with a supersonic turbine. On the other hand, a viable solution consists of driving a subsonic turbine using a flow ejector. The flow mixes between the burned gases coming from the detonation chamber with the fresh air coming from the compressor. This will result in drastic reduction in flow speed, fluctuations and temperature. This option is retained in this project. The work will be an extension of preliminary studies conducted in the previous INSPIRE project, where a first attempt has shown the relevance of using ejectors for turbine coupling. This research will be performed in close association with CERFACS and TUB.