Rotating detonation engines (RDE) have emerged as a research focus in advanced propulsion systems due to their superior thermal efficiency and compact structure. However, the extreme thermal environment induced by detonation combustion poses severe challenges to engine thermal protection. This study conducts a systematic investigation on the heat transfer characteristics and material ablation behavior of a kerosene-fueled rotating detonation combustor (RDC). Wall temperature distributions were experimentally measured, and the effects of equivalence ratio and mass flow rate on the heat flux were systematically investigated. Subsequently, a time-resolved theoretical ablation model was established to characterize the ablation process. Furthermore, silica/phenolic layer was installed on the RDC to test the ablation performance under rotating detonation conditions. Key findings indicated that the heat flux exhibits an initial increase followed by a decline along the axial direction, with the incoming flow reducing heat flux in the combustion chamber inlet region. Wall heat flux was also observed to rise with increases in both equivalence ratio and mass flow rate. Experimentally, the peak heat flux measured in the detonation wave region reached 8 MW/m2. The degradation rate of the ablative layer was determined based on the theoretical ablation model, and the overall spallation amount of the layer was obtained through Gaussian fitting. The results show good agreement with experimental data from the silica/phenolic layer ablation test, with an error margin of 4.4%. This study provides key experimental data and design guidelines for the thermal protection design and full-life-cycle assessment of RDE, effectively advancing their engineering application process.
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