3D Numerical Simulation on Disk Type RDE Used Hydrogen-Air Non-Premixed Gas: Investigation of Pressure Loss Factors

A three-dimensional viscosity simulation of a rotating disk detonation engine (DRDE) using the Navier-Stokes equations with the UT-JAXA reaction mechanism for H2-air Premix and Non-premix gas is presented. DRDE has been actively discussed since its proposal in 2018. Previous studies have shown that DRDEs exhibit transient propagation behavior with wavefront acceleration and deceleration when multiple wavefronts are generated and can achieve comparable pressure gains compared to RDEs. On the other hand, it is suggested that the internal flow of a DRDE is different from that of an RDE, which is important when a turbine is inserted in a DRDE and the DRDE is used as a generator. In this study, we visualized the propagation patterns in a DRDE combustor for two injection methods, non-premixed and premixed. We investigated the effect of the injection method on the propagation patterns. The objective is to clarify which factors of pressure drop are related to the pressure gain. The results show that DRDE has comparable performance in pressure gain compared to RDE, and that it is important to suppress the steep pressure drop at the outer wall of the bend in order to obtain pressure gain.