Sijia Gao, Han Peng, Zhipeng Sun, Huan Lian, Yue Huang, Zijun Zhou, Yancheng You
DOI Number: N/A
Conference number: HiSST-2025-137
Rotating detonation waves exhibit different propagation modes under varying operating conditions. Two-dimensional Navier-Stokes equations and a kerosene/air reaction model based on RYrhoCentralFoam solver were used to simulate the non-premixed two-phase rotating detonation combustion. The transformation trends and evolution processes of the propagation modes of the rotating detonation wave were analyzed in response to variations in the total temperature of the incoming flow and in the fuel droplet proportion. Additionally, the vaporization rate of liquid fuel within the flow field was examined, and the third Damköhler number as well as the transient Rayleigh index of the rotating detonation combustion flow were calculated. The results indicate that increasing the total temperature of the incoming flow and decreasing the fuel droplet proportion lead to an increase
in the number of detonation waves. Higher incoming flow temperatures correspond to lower peak pressures of the detonation waves, more numerous detonation fronts, and a faster mode transition. Conversely, reducing the total temperature maintains the number of detonation waves but results in increased wave intensity. An elevated vaporization rate of liquid droplets induces a quasi-isovolumetric combustion process within the detonation flow field, generating pressure shocks. The interaction between these pressure shocks and heat release contributes to the overall dynamics. Based on the self-sustaining energy growth characteristic of thermoacoustic instability, the system undergoes multiple cycles of decoupling and re-detonation, ultimately forming a stable detonation wave and leading to a transformation in the propagation mode.