| Citation: | Zhang Dongqing, Pei Chongzhi, Shi Wen, et al. Impact of fuel injection schemes on combustion characteristics in supersonic combustors with non-symmetric inflow[J]. Journal of Aerospace Power, 2026, 41（10）：20250286 doi: 10.13224/j.cnki.jasp.20250286
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A numerical simulation study of combustion flow fields under different fuel injection schemes was conducted for an S-shaped isolator-supersonic combustor configuration. The results were compared with those of a baseline straight isolator-supersonic combustor to analyze the effects of the S-shaped isolator on combustion characteristics and the backpressure transmission process within the isolator. Additionally, the cold flow fields, combustion flow fields, and combustion performance of different configurations and injection schemes were compared. The study revealed the following: Under cold conditions, the S-shaped isolator had little impact on fuel mixing characteristics; however, under combustion conditions, the strongly coupled nonlinear system amplified the asymmetry of the inflow, leading to significant non-uniformity in the combustion field. At the same time, it reduced the combustion efficiency from 82% to 65%. To address the non-uniform inflow under combustion conditions, the injection scheme was optimized by combining rail injection and adding additional injection positions on the combustor wall. This improved both the uniformity and efficiency of the combustion field. The combustion efficiency at the combustor exit increased from 65% to 85%, and the total temperature distribution coefficient decreased from 64% to 26%, achieving nearly the same combustion efficiency and uniformity as under uniform inflow conditions.
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