| Citation: | GU Yefeng, WANG Yibo, LIU Yunpeng, et al. Study on combustion flow field characteristics of integrated afterburner with non-uniform inflow[J]. Journal of Aerospace Power, 2025, 40（7）：20240138 doi: 10.13224/j.cnki.jasp.20240138
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When the real afterburner operated in a fast transient transition state, the complex incoming flow caused the flow field to deviate from the design points, resulting in a poor combustion performance. In order to study the influence of non-uniform inflow on the combustion flow field characteristics of an afterburner, the flow field of an integrated afterburners with non-uniform velocity inflow and non-uniform cosine rotation angle inflow was studied numerically. The results showed that: with the increase of non-uniform inlet velocity, the velocity gradient in the integrated afterburner flow field increased radially. In the combustion flow field, the chemical reaction core zone and the high-temperature zone shrank, indicating the combustion performance became worse; With the increase of non-uniform inlet cosine rotation angle, the vortex structure between the struts expanded while the vortex intensity strengthened gradually. In the combustion flow field, the chemical reaction rate increased. The high-temperature zone became larger and shifted towards the center of the flow field radially which indicated a superior combustion performance; with the increase of inflow non-uniformity, the flow resistance loss coefficient of the integrated afterburner increased while the total pressure recovery coefficient declined, showing the increment of the flow resistance loss.
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