Mohammed N NEJAAMTHEEN, Bu-Kyeng SUNG, Jeong-Yeol CHOI
DOI Number: 10.60853/b89s-z658
Conference number: HiSST-2024-00352
Detonation engines are likely to be integrated into various aerospace propulsion systems in the forthcoming era. Among the various types of detonation engines being investigated, the rotating detonation engine (RDE) stands out. Despite experimental explorations of the RDE, the intricate mechanism behind the propagation of rotating detonations remains inadequately understood. This work presents a comprehensive study focused on the wave dynamics along with key features of the detonation process and its effects on the flow-field. After reaching a quasi-steady state, the detonation structure in the azimuthal direction is investigated. The high temperature at the detonation front is determined to be around 2800⁓3100 K. Lowering the p0 results in decreased velocities, with the maximum Udef occurring at the lowest pressure value. Conversely, increasing p0 leads to a more robust propagation of the detonation wavefront. Similar trends are observed for variations in T0, indicating a weaker wavefront propagation with higher temperatures. The study further explores the time-taken for wave stabilization, finding a correlation between wave number and the required stabilization time. The investigation of pressure peaks indicates an inverse relationship with the number of waves, suggesting significant dynamics influenced by the number of waves present.