| Citation: | WANG Jinduo, HUI Xin, WU Jihong, et al. Effects of design parameters of two-stage axial swirler on combustor ignition performance[J]. Journal of Aerospace Power, 2022, 37（11）：2544-2552 doi: 10.13224/j.cnki.jasp.20220296
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To improve the ignition performance of the aero-engine combustor, different configurations of two-stage axial swirlers were designed based on the swirler design parameters. Ground and high-altitude ignition tests were carried out to obtain the ignition fuel-air-ratios for a model combustor equipped with the designed swirlers. The effects of outer swirl number, the air split ratio between the inner and outer swirlers, and Venturi throat size on combustor ignition performance were analyzed. The results showed that under the same total air flow rate and inner swirl number, when the outer swirl number increased from 1.77 to 2.15, the combustor ignition performance first decreased and then increased, and the ignition characteristic was better when the outer swirl number was smaller. The inner and outer swirler flow ratios had a significant impact on the combustor ignition performance under high altitude and low pressure conditions, and the ignition characteristic was the best when the ratio was 3∶7. If other structural parameters were kept unchanged, the Venturi throat radius had a significant impact on the high altitude ignition performance of the combustor, and it had good ignition characteristics when the throat radius was 8 mm.
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