Optimal design of micro-ejector anti-icing based on thermal calculation and genetic algorithm
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摘要:
飞机穿越含有过冷水滴的云层时易发生结冰现象，严重威胁飞行安全，高效的防冰系统是飞机应对结冰环境、保障飞行安全的关键。微引射式热气防冰是运输类飞机常用的防冰手段，具有用气量少、防冰效率高等优点。基于自主研发的NNW-ICE软件，实现了微引射特性计算、防冰通道换热计算及沿程压降计算，建立了微引射防冰系统热力计算方法，可获得特定几何结构下引射比、被引射气体温度及蒙皮外表面温度、溢流水分布等参数；基于该热力计算方法，结合遗传算法建立微引射热气防冰系统优化设计框架，以蒙皮外表面平均温度最优为目标，对防冰单元宽度、双蒙皮通道高度及通道内部宽度等结构设计参数进行优化。优化后微引射热气防冰系统蒙皮外表面平均温度较优化前提升3.01 K，溢流水质量流量降低39.00%。结果表明基于热力计算和遗传算法的防冰优化设计框架可以应用于微引射热气防冰系统，并能够取得良好的应用效果。
Abstract: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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Key words:
- hot-air anti-icing /
- micro-ejector /
- thermal calculation /
- genetic algorithm /
- optimum structural design
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图 3 微引射防冰通道沿s坐标分区
Figure 3. Sections of micro-ejector anti-icing channel along the s direction
图 6 基于热力计算及遗传算法的微引射防冰系统优化设计
Figure 6. Optimization design based on micro-ejector anti-icing thermal calculation and Genetic Algorithm
图 8 冷空气流场及水滴撞击特性计算模型
Figure 8. Mesh used for cold air flow field and collection efficiency calculations
图 9 蒙皮表面的表面传热系数和局部水滴收集系数
Figure 9. Surface heat transfer coefficient and local water collection efficiency on the skin surface
图 10 基础设计蒙皮外表面温度和溢流水分布
Figure 10. Temperature and runback water on the skin surface of the baseline design
图 11 基础设计防冰载荷及热气传给蒙皮的能量
Figure 11. Anti-icing heat load and heat exchange by hot air flow to skin with the baseline design
图 12 基础设计蒙皮外表面热流项
Figure 12. Heat transfer rate distributions on the skin surface of the baseline design
图 13 优化结果和对应目标函数值
Figure 13. Solutions and objective function values of optimization runs
图 15 微通道内温度及蒙皮表面温度分布对比
Figure 15. Comparison of temperature distributions on the skin surface
图 16 蒙皮表面溢流水质量流量分布对比
Figure 16. Comparison of the mass flow rate distributions of runback water on the skin surface
图 17 优化设计蒙皮表面热流项
Figure 17. Heat transfer rate distributions on the skin surface of the optimized design
图 18 工况1下基础设计与优化设计对比
Figure 18. Comparison between the baseline and the optimized under condition 1
图 19 工况2下基础设计与优化设计对比
Figure 19. Comparison between the baseline and the optimized under condition 2
表 1 基础设计和设计参数区间
Table 1. Baseline design and the ranges of design variables
mm 设计变量 基础设计 取值范围 a 45 40～50 b 35 20～40 h 3 2～4 
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表 2 微引射优化设计结构参数
Table 2. Optimized design and baseline design
mm 设计变量 优化设计 a 40.25 b 36.33 h 2.04
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