Effect of turbine blades on rotating detonation wave propagation characteristics

This study investigated the impact of turbine blades on the rotating detonation combustion process and analyzes the interaction mechanisms between detonation-induced oblique shock waves and the turbine blades. The results revealed that oblique shock waves induce multiple reflected shock waves within the blade passageways, leading to boundary layer separation and vortex flow on the blade surfaces. This phenomenon leads to a total pressure loss in turbine flow reaching 13%, compared to 8.3% with steady deflagration combustion. The influence of turbines on detonation combustion revealed that turbine rotor blades impede flow within the combustor, resulting in elevated the combustor pressure and detonation wave pressure, while the propagation speed of detonation waves remains unaffected. At low rotational speeds, ineffective fuel-air premixing leads to unstable detonation, while higher speeds stabilize the process. These findings advance understanding of detonation-turbine coupling and provide a basis for optimizing turbine blade design in rotating detonation engines.