Impact of Rotating Detonation Combustor Shock Wave Patterns on Supersonic Inlet Turbine Stage Performance
Rotating Detonation Engines (RDEs) offer a promising path toward more efficient and compact propulsion and power systems. However, the highly unsteady and transonic outlet flow generated by the detonation process, characterized by oblique shock wave patterns, introduces significant challenges for turbine integration and overall performance. The present work focuses on the impact of the oblique shock waves exiting the rotating detonation combustor (RDC) on a supersonic inlet high-pressure turbine stage. The analysis examines how the shock pattern, the number of detonation fronts, and their rotation direction affect the unsteady aerodynamics and the overall turbine performance. In addition, the effect of shock waves on the stator and rotor unsteady loads is investigated to provide a preliminary aeromechanical assessment of the supersonic turbine. Full-annulus unsteady simulations were performed to capture the complex RDC–turbine interaction and its effects on blade loading and flow structures. The numerical framework has been validated against a previous Large Eddy Simulation (LES) analysis of the turbine stage under RDC-representative conditions. The comparisons highlight the key mechanisms driving shock–turbine interactions, showing how shock synchronization and rotation direction affect turbine efficiency and power extraction. These findings provide valuable insights into the design configurations and coupling scenarios of turbines operating under detonation-based flow conditions.