Study on icing multiphase heat transfer process based on phase interface data exchange
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摘要:
发动机结冰会对飞行安全造成影响，研究发动机结冰过程机理可以帮助提高飞行安全性能和完成适航验证。使用欧拉法计算了水滴运动过程，使用能量平衡法计算了结冰的多相传热流动过程，使用一维导热模型矫正了壁面导热过程，并提出了基于相界面导热平衡方程的数据交换模型。基于此模型进行了发动机进口部件的冰风洞实验数据数值验证，模拟计算最大结冰厚度与试验误差能够控制在10%左右。相界面数据交换模型能够对近壁的水膜流动和温度梯度进行精细化模拟，并且将用户自定义函数（UDF）与求解器进行流场参数的实时交换，经验证后表明该模型在计算结冰最大厚度时具有较好的精度。
Abstract:Aero-engine icing can affect flight safety. Studying the mechanism of aero-engine icing process can help improve the flight safety performance and accomplish airworthiness verification. The Eulerian method was used to calculate the motion of water droplet. The energy balance method was adopted to calculate the multiphase heat transfer and flow process of icing, and the one-dimensional heat conduction model was employed to correct the process of heat conduction with wall. The data exchange model based on phase interface heat conduction equilibrium equation was proposed. Based on this model, numerical verification of icing wind tunnel test data on the engine inlet part was accomplished. The maximum icing thickness error compared by simulation and test could be controlled at about 10%. The phase interface data exchange model can accurately simulate the water film flow and the temperature gradient near wall, and can also currently exchange the flow parameters between the user defined function (UDF) and the solver. The results showed that the model had good accuracy in calculating the maximum icing thickness.
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图 3 当量导热系数随冰层厚度变化
Figure 3. Equivalent heat conductivity coefficient varies with ice thickness
图 7 数据交换模型冰形与实验、LEWICE软件、CIRA软件冰形比较
Figure 7. Ice shape comparison of data exchange model, test, LEWICE software and CIRA software
表 1 不同冰层厚度当量导热系数
Table 1. Equivalent heat conductivity coefficient with different ice thicknesses
时间/s $ \kappa $/（W/（m3·K）） δ=0.5 mm δ=1 mm δ=2 mm δ=4 mm δ=6 mm 0.2 12394 11704 7864 7851 7851 0.4 8760 7468 4593 4580 4580 0.6 7624 5912 3446 3423 3420 0.8 7078 5119 2848 2813 2813 1 6725 4654 2479 2430 2430 
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