Effects of detonation wave direction and moment of inertia on the performance and flow structures of a disk rotating detonation combustor

This study presents a systematic investigation of turbine-coupled disk rotating detonation combustor (RDC) dynamics, establishing novel relationships between detonation wave direction, turbine inertia, and flow field characteristics. A two-dimensional simulation of stoichiometric hydrogen–air mixtures is performed using a six degrees of freedom solver. The results indicate that both the direction of the detonation wave and the turbine's moment of inertia significantly affect the reflection characteristics of the oblique shock wave (OSW) and the turbine's choking effect, thereby influencing the characteristics of the detonation. An increase in the angle between the OSW and the blade chord, coupled with a decrease in the moment of inertia, reduces the reflected shock wave intensity and the choking effect. Furthermore, the rotating detonation flow has the potential to directly drive the rotor, suggesting a possible reduction in engine mass. This research proposes three formation mechanisms for multiple detonation modes, as well as an attenuation mechanism for the number of rotating detonation waves, which is dominated by hot spots. Three types of coupling effects between the detonation wave and the reflected wave, along with a stable spiral shock wave system, have been identified, and the relationship between the spatial position of the shock wave and the physical dimensions of the combustor has been established. These findings offer new insights for optimizing the design of disk RDCs and their integration with downstream turbines.