| Citation: | DING Jing, DENG Yuanhao, SHAN Yong, et al. Experimental and numerical investigation of core and bypass flow mixing characteristics in variable-bypass-ratio afterburner/ram combustor[J]. Journal of Aerospace Power, 2025, 41（X）：20250343 doi: 10.13224/j.cnki.jasp.20250343
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The variable-bypass-ratio afterburner/ram combustor of a variable cycle engine was investigated through scaled-model flow experiments and full-scale three-dimensional numerical simulations. The purpose of the research was to reveal the internal flow characteristics under different bypass ratios (BPR) and parallel mixer exit area ratios, while quantitatively evaluating key parameters including velocity non-uniformity, mixing loss, and peak outer casing temperature of the heat shield cooling channel. The results showed that, compared with the uniform flow at the core flow inlet, the introduction of swirl enhanced shear mixing between the rotating core flow and the bypass stream. Under severe conditions, this caused partial ingress of high-temperature core fluid into the heat shield cooling channel, resulting in localized temperatures as high as 812.97 K on the outer casing. The use of a parallel mixer effectively controlled the total pressure loss in the afterburner/ram combustor, maintaining it within 3.5%. The bypass-to-core exit area ratio served as a critical parameter. An appropriate area allocation ensured sufficient bypass airflow entered the cooling passage while providing adequate momentum to suppress flow separation at the inner side of the heat shield inlet. Under small bypass ratio conditions, increasing the bypass-to-core exit area ratio reduced the cooling flow rate by approximately 20%, which can impair the cooling effectiveness of the heat shield. Additionally, the low-momentum bypass flow struggled to overcome the adverse pressure gradient, leading to the formation of a recirculation zone on the inner side of the heat shield and worsening the radial velocity non-uniformity upstream the flame holder to a range of 0.10—1.20, adversely affecting afterburner performance. In contrast, under large bypass ratio conditions, an excessively small bypass-to-core exit area ratio increased the mixing loss to 3.16%. As the bypass-to-core exit area ratio increased, the matching between the core and bypass flows improved, and the velocity non-uniformity narrowed to a range of 0.85—1.07, demonstrating superior overall performance.
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