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Synergistic flame stabilization and oscillation dynamics in a dual-zone supersonic combustor
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DOI：10.1016/j.combustflame.2026.115031.png)
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Abstract
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The flame stabilization and oscillation characteristics in a dual-zone supersonic combustor are investigated. The Mach number, stagnation temperature, and stagnation pressure are 2.52, 1486 K, and 1.6 MPa, respectively. Ethylene is used as the fuel, with global equivalence ratios (φ) of 0.30, 0.35, and 0.40. The results show that under all tested equivalence ratios, the combustor consistently exhibits a cavity-stabilized supersonic combustion mode when the flame is stabilized only by the cavity. The subsequent establishment of the backward-facing step (BFS) flame significantly enhances the cavity combustion efficiency, thereby altering the combustion mode in the combustor. At φ = 0.30, a stable supersonic combustion mode is observed, with cavity and BFS flames. However, at φ = 0.35 and 0.40, the combustor transitions to dual-zone subsonic combustion mode, which are characterized by statistical stability and low-frequency quasi-periodic oscillations. The synergistic flame stabilization mechanism of these two combustion modes is analysed. In the supersonic mode, the BFS and cavity flames stabilize relatively independently along their respective shear layers. Moreover, in the subsonic combustion mode, the overall flame stabilization is maintained through periodic interactions between the cavity and BFS flames. Coupled heat release from two zones induces flow choking and pressure rise, triggering flame transitions and energy transfer that sustain the quasi-periodic behaviours. This study advances the understanding of combustion processes in the dual-zone supersonic combustor and provides insights for design of engineering-relevant supersonic combustor.
Keywords:
flame stabilization
supersonic combustion
oscillation dynamics
dual-zone combustor
flame interaction
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