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首页> 外文会议>Congress of the International Council of the Aeronautical Sciences; 20060903-08; Hamburg(DE) >THE DESIGN OF A SERIES OF ELECTROTHERMAL ICE PROTECTION SYSTEMS
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THE DESIGN OF A SERIES OF ELECTROTHERMAL ICE PROTECTION SYSTEMS

机译：一系列电热冰保护系统的设计

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摘要

This paper focuses on the design of ice protection system of aircraft components under different inflight icing characters. A numerical simulation method based on Euler-Euler multiphase coupling model was adopted to design the electrothermal anti-icing system for aircraft components with atypical shapes such as radomes on fuselages. For the calculation of droplets impingement, 3D N-S equations and standard k-ε turbulence model were applied to improve the simulation precision of flow fields and droplets concentration fields of complex configurations. The Langmuir distribution model of droplet diameters was introduced and the numerical solutions are compared with that of uniform average diameter. Some representative validation examples are presented, including an airfoil, a 2-D cylinder and a 3-D sphere, by comparing our results with the dissertations' ones which come from experiments or numerical simulations of authoritative organizations. The calculated thermal loads of real components are compared with that of the previous used engineering method. The electrothermal anti-icing system designed as a product had been tested in engineering practice for a long time.
机译：本文着重研究了飞机不同结冰特性下飞机部件的防冰系统的设计。采用基于Euler-Euler多相耦合模型的数值模拟方法，设计了机身上天线罩等非典型形状的飞机部件的电热除冰系统。为了计算液滴的撞击，使用3D N-S方程和标准的k-ε湍流模型来提高复杂构造的流场和液滴浓度场的模拟精度。介绍了液滴直径的朗缪尔分布模型，并将数值解与均匀平均直径的数值解进行了比较。通过将我们的结果与来自权威机构的实验或数值模拟的论文的结果进行比较，提出了一些代表性的验证示例，包括机翼，二维圆柱体和三维球体。将计算出的实际部件的热负荷与以前使用的工程方法进行比较。设计为产品的电热防冰系统已经在工程实践中进行了长时间的测试。

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