| Citation: | Yang Qian, Dai Xinbo, Liu Yu, et al. Optimal design of micro-ejector anti-icing based on thermal calculation and genetic algorithm[J]. Journal of Aerospace Power, 2026, 41（X）：20250592 doi: 10.13224/j.cnki.jasp.20250592
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When aircraft fly through clouds containing supercooled water droplets, ice can accrete on the surfaces, posing a serious risk to flight safety. Effective anti-icing systems are therefore essential to ensure safe operation under such conditions. The micro-ejector hot-air anti-icing system, as a common anti-icing method for transport aircraft, features low hot air consumption and high anti-icing efficiency. Based on the self-developed NNW-ICE software, the computational methodologies for characterizing the micro-ejector, modeling heat transfer, and estimating pressure drop within the anti-icing channel were developed. These methodologies established a thermal calculation framework for the micro-ejector anti-icing system, yielding key parameters, including the entrainment ratio, temperature of the entrained air, external skin temperature distribution, and runback water distribution for a given geometric configuration. Based on this framework and combined with the genetic algorithm, an optimization design framework for the micro-ejector hot-air anti-icing system was established to maximize the average external skin surface temperature by adjusting the structural design parameters such as the width of the anti-icing unit, the height of the double-skin channel and the internal width of the channel. The optimized design achieved significant performance improvements: the average external surface temperature increased by 3.01 K, and the mass flow rate of runback water decreased by 39.00%. The results showed that the anti-icing optimization design framework based on thermal calculation and genetic algorithm can be applied to the micro-ejector hot-air anti-icing system with satisfactory performance.
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