An experimental study on different plasma actuator layouts for aircraft icing mitigation
An experimental study on different plasma actuator layouts for aircraft icing mitigation
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DOI：
10.1016/j.ast.2020.106325
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发表时间：
2020-12-01
影响因子：
5.6
通讯作者：
Hu, Hui
中科院分区：
文献类型：
--
作者：
Kolbakir, Cem;Hu, Haiyang;Hu, Hui
通过实验研究了介质阻挡放电等离子体(DBD)驱动器布局对等离子体热特性的影响，并评价了其对飞机防冰效果的影响。实验研究在爱荷华州立大学结冰研究隧道(即ISU-IRT)进行，翼型/机翼模型在翼型前缘周围嵌入了DBD等离子体致动器阵列。将等离子体激励器布置成不同的布局(例如，暴露电极的方向、数目和宽度)，以评估它们在与飞机飞行结冰现象相关的典型釉面结冰条件下对防冰性能的影响。用高分辨率成像系统记录了启动等离子体激励器前后翼型表面的动态结冰或防冰过程，用高速红外热成像系统定量地绘制了翼型表面的温度分布。实验结果清楚地表明，在相同的功率消耗水平下，流线型布局的等离子体激励器与展开型布局相比，具有更高的等离子体感生表面热和更快的未冻水在翼型表面的回流，从而具有明显更好的抗冰性能。结果表明，流型布局的等离子体激励器不仅能够防止翼型前缘附近的结冰，而且可以使等离子体诱导的表面加热进一步向下游对流，从而延缓/防止翼型后缘附近的Runback结冰。研究发现，等离子体激励强度和翼型表面等离子体放电覆盖率的适当组合可使飞机防冰性能达到最佳。(C)2020年爱思唯尔·马森公司。版权所有。
An experimental study was conducted to examine the effects of dielectric-barrier-discharge plasma (DBD) actuator layout on the plasma-induced thermal characteristics and evaluate their effectiveness for aircraft icing mitigation. The experimental investigation was performed in the Icing Research Tunnel of Iowa State University (i.e., ISU-IRT) with an airfoil/wing model embedded with an array of DBD plasma actuators around the airfoil leading edge. The plasma actuators were arranged in different layouts (e.g., orientation, number, and width of exposed electrodes) to evaluate their effects on the anti-icing performance under a typical glaze icing condition pertinent to aircraft inflight icing phenomena. While the dynamics ice accretion or anti-icing process over the airfoil surface before and after turning on the plasma actuators was recorded by using a high-resolution imaging system, a high-speed infrared thermal imaging system was used to quantitatively map the temperature distributions over the airfoil surface. The experimental results clearly reveal that, with the same power consumption level, the plasma actuators in streamwise layout would result in higher plasma-induced surface heating and faster runback of the unfrozen water over the airfoil surface, thereby, having a noticeably better anti-icing performance, in comparison to those in spanwise layout. The plasma actuators in streamwise layout were found to not only be able to prevent ice accretion near the airfoil leading edge, but also allow the plasma-induced surface heating to convect further downstream to delay/prevent the runback ice formation near the airfoil trailing edge. A proper combination of the plasma actuation strength and the plasma discharge coverage over the airfoil surface was found to result in the optimum performance for aircraft anti-icing applications. (c) 2020 Elsevier Masson SAS. All rights reserved.