| Citation: | XU Guangchuan, CHEN Zheng, WANG Xiaokun, et al. Experimental study on rotating detonation wave propagation characteristics of subcritical aviation kerosene[J]. Journal of Aerospace Power, 2025, 40（12）：20240265 doi: 10.13224/j.cnki.jasp.20240265
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In order to explore the rotating detonation wave propagation characteristics of aviation kerosene mixed with incoming air in the subcritical state, the ambient aviation kerosene was heated and pressurized to the subcritical state, an experimental study of the combustion characteristics of the rotating detonation under different incoming flow temperatures and combustion chamber widths was carried out, and the influencing factors of the initiation and propagation of the rotating detonation wave were analyzed. The experimental results showed that the initiation process of subcritical aviation kerosene was divided into three stages: ignition, deflagration to detonation and sustained and stable detonation wave propagation. When the total incoming flow temperature ranged from 300 K to 700 K, the detonation characteristics of subcritical aviation kerosene can be improved by increasing the total incoming flow temperature. When the total incoming flow temperature increased from 500 K to 700 K, the detonation time can be shortened from 30 ms to 16 ms. The rotating detonation chamber width can effectively influence the propagation stability of the detonation wave. In case of the same combustion chamber outer diameter, the 50 mm wide annular combustion chamber under the same working condition can only form sporadic detonation waves, while the hollow combustion chamber can realize stable single-wave detonation combustion.
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