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首页> 外文会议>Third Asia-Pacific International Symposium on Aerospace Technology >Electro-thermal Anti-icing Characteristics of Composite Strut of Aeroengine Inlet
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Electro-thermal Anti-icing Characteristics of Composite Strut of Aeroengine Inlet

机译：航空发动机进气口复合支柱的电热防冰特性

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摘要

Composite part is of low quality and high intensity, and composite is a kind of material preferred for aeroengine inlet part now. Under icing conditions, the inlet of aeroengine is prone to icing. Icing in inlet of aeroengine causes degradation of performance and menaces the safety of the aeroengine, so the composite inlet must be protected from icing. Electric ice protection is the way forward and is one of key technologies for composite part. The 3D Reynolds averaged Navier-Stokes equations and 冋 儃 k model are used to simulate the airflow over the strut in aeroengine composite inlet. A Eulerian model for airflow containing water droplet is used to get the water droplet trajectories. The supercooled water impingement on the strut surface is achieved based on a certain flight icing condition, and anti-icing heat-load and overflow-water distribution on its surface is also obtained on both complete evaporation and incomplete evaporation. On the basis of the results, the configuration and heater mats for composite strut was designed. The experiment for electro-thermal anti-icing characteristics was made on certain icing condition, and anti-icing effect was got on different electro-thermal conditions. A comparision between calculation and experiment results was made, and the two fitted each other well.
机译：复合材料零件质量低，强度高，复合材料是目前航空发动机进气件的首选材料。在结冰条件下，航空发动机的进气口容易结冰。航空发动机进气口的结冰会降低性能，并危及航空发动机的安全性，因此必须防止复合进气口结冰。电冰保护是前进的方向，并且是复合零件的关键技术之一。使用3D雷诺平均Navier-Stokes方程和冋k模型来模拟航空发动机复合进气道中支杆上的气流。使用包含水滴的气流的欧拉模型来获得水滴轨迹。根据一定的飞行结冰条件，实现了过冷水在支柱表面的撞击，并且在完全蒸发和不完全蒸发的情况下，都获得了其表面的除冰热负荷和溢水分布。根据结果​​，设计了复合支柱的配置和加热垫。在一定的结冰条件下进行了电热除冰性能试验，在不同的电热条件下均获得了防冰效果。在计算和实验结果之间进行了比较，两者相吻合。

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