Optimization of Dielectric Barrier Discharge Plasma Actuators for Icing Control
Optimization of Dielectric Barrier Discharge Plasma Actuators for Icing Control
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用于结冰控制的介质阻挡放电等离子体致动器的优化
DOI：
10.2514/1.c035697
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发表时间：
2020-03-01
影响因子：
2.2
通讯作者：
Hu, Hui
中科院分区：
文献类型：
--
作者：
Hu, Haiyang;Meng, Xuanshi;Hu, Hui
ICING被认为是航空和风能等行业在寒冷天气中的严重安全问题，因为当过冷水滴撞击并冻结在翼型和旋转叶片的表面上时，它会降低性能。流线型线的污染将导致气动效率的严重下降和整个转子系统的不平衡。因此，许多研究都集中在这种结冰现象和各种防/除冰技术已在过去几十年中开发[1-5]。然而，当前的防冰/除冰技术不足以满足空气动力学、材料和能源消耗方面不断变化的要求[6]。因此，延长耐久性和有效防/除冰性能的新方法和技术被认为是理想的[7-13]。等离子体流量控制由于其无运动部件、响应速度快、易于安装在表面而不改变形状等特点，在过去的几十年里受到了越来越多的研究关注。一个这样的重要发展是使用表面介质阻挡放电（SDBD）等离子体致动器，其由以不对称方式布置的介电材料分隔的两个电极组成[14-17]。最常见的SDBD等离子体流量控制方法包括交流表面介质阻挡放电（AC-SDBD）和纳秒脉冲表面介质阻挡放电（NS-SDBD）等离子体激励。近年来，不同的研究人员研究了AC-SDBD等离子体流量控制的机制[14，16]。不同研究人员的结果是一致的，即，在电极之间施加足够高的电压AC信号会使覆盖封装电极的电介质上的空气弱电离。空气的电离是交流循环中的一个动态过程。电离的空气，在电场的存在下，导致体积力矢量。这种诱导气流可以向流传递动量，就像流抽吸或吹送一样，但没有质量注入。NS-SDBD等离子体激励器在高速流动控制中具有巨大的潜力，但其在不同时间尺度上的气动效应不同，使得其流动控制机理更加复杂。此外，由于输入是纳秒级的高压信号，其电磁干扰比AC-SBDB强得多，对结冰风洞的控制和测量设备造成严重干扰。最近，研究人员通过优化致动器几何形状、基底材料和其他参数，在更高风速和雷诺数下实现了有效的流动控制结果[18-20]。使用AC-SDBD等离子体激励，Zhang等人[19]展示了使用对称布置的封装电极激励器对翼型进行的有效流动控制，其流入速度为100 m/s; Kelley等人[18]使用3.175 mm厚的陶瓷作为绝缘材料，实现了流入速度为Ma 0.4和雷诺数为2.3 × 10的有效流动控制。Nishihara等人[20]使用NS-SDBD等离子体激励，证明了在来流马赫数为5时有效的弓形激波扰动。然而，等离子体流量控制的缺点是其能量转换效率低（表面放电诱导的动力学效率与放电电流的关系仅为百分之几）[14]。就流量控制应用而言，转化为热量的电能部分仍然是无用的[21-24]。Meng等[25，26]和Cai等[27]提出了一种利用AC-SDBD等离子体激励进行结冰控制的研究方法，该方法可以充分利用SDBD等离子体放电的气动和热效应。Meng等人[26]和Cai等人[27]证明了在圆柱模型上SDBD等离子体结冰控制的可行性。在结冰风洞中，基于可视化和热图像评估了AC-SDBD等离子体激励器的防/除冰性能。与传统的防/除冰系统相比，AC-SDBD等离子体几乎可以满足下一代飞机设计的所有结冰控制要求。首先，它可以齐平地安装在表面上而不干扰流动以保持自然层流，并且当飞机在飞行期间不处于结冰条件时，它可以用于流动控制。第二，它可以充分利用AC-SDBD的放电能量，即，热效应和空气动力学效应。此外，放电的自限制性质限制了AC-SDBD等离子体的温度上升，从而保护复合结构在防冰/除冰期间免于过热。最后，随着模型电池技术的发展，AC-SDBD致动器可以由电池驱动的袖珍高压发电机供电，该发电机已在几次现场测试中安装在无人驾驶飞行器上作为电子方向舵[28]。因此，AC-SDBD执行器可以舒适地安装在全电动飞机上，作为一种全电动结冰控制技术。2019年8月8日接收; 2019年10月7日接受出版; 2020年2月13日在线出版。版权所有© 2020由美国航空航天研究所，公司。All rights reserved.所有复制和允许重印的请求应提交给CCC，网址为copyright.com;使用eISSN 1533-3868启动您的请求。另请参阅AIAA权利和许可www.aiaa.org/randp。* 研究生;现博士，爱荷华州立大学，爱荷华州50011。教授; mxsbear@nwpu.edu.cn（通讯作者）。教授; jcai@nwpu.edu.cn。助理教授; zhouww@sjtu.edu.cn。助理教授; liuya19@ecu.edu。** 教授; huhui@iastate.edu。
I CING is regarded as a severe safety issue for the industry, such as aviation and wind energy in cold weather, because it will degrade the performance when supercooled water droplets impinge and freeze onto the surface of the airfoil and rotating blades. The contamination of the streamlined profile will cause serious degradation of the aerodynamic efficiency and unbalance the whole rotor system. Therefore numerous studies have focused on this icing phenomenon and various anti-/de-icing technologies have been developed in the past few decades [1–5]. However, the current anti/ de-icing technology is not sufficient to address the ever-evolving requirements in aerodynamics, materials and energy consumption [6]. As a result, the novel methods and techniques for extended durability and efficient anti-/deicing performance are considered desirable [7–13]. Plasma flow control has received growing research attention in the past few decades for its unique features, such as nomoving parts, fast response, and exceptional ease of installation on the surface without changing the shape. One such significant development is the use of surface dielectric barrier discharge (SDBD) plasma actuators, which are composed of two electrodes separated by a dielectric material arranged in an asymmetric fashion [14–17]. The most common SDBD plasma flow control methods include alternative-current surface-dielectric-barrier-discharge (AC-SDBD) and nanosecond-pulse surface-dielectric-barrier-discharge (NS-SDBD) plasma actuations. The mechanism of AC-SDBD plasma flow control has been studied by different researchers in recent years [14,16]. The results for different researchers are consistent, i.e., application of a sufficiently high-voltage ac signal between the electrodes weakly ionizes the air over the dielectric covering the encapsulated electrode. The ionization of the air is a dynamic process within the ac cycle. The ionized air, in the presence of the electric field, results in a body force vector. Such induced airflow can impart momentum to the flow, just like flow suction or blowing, but without mass injection. For the NS-SDBD plasma actuator, it has great potential in highspeed flow control; however, its different aerodynamic effects at different timescales make its mechanism in the flow control much more complicated. In addition, because the input is a high-voltage signal of the nanosecond level, its electromagnetic interference is much stronger than that of the AC-SBDB, causing serious interference to the control and measurement equipment of the icing wind tunnel. Recently, researchers have achieved effective flow control results at higher wind speeds and Reynolds numbers through the optimization of the actuator geometry, substrate materials, and other parameters [18–20]. Using AC-SDBD plasma actuation, Zhang et al. [19] showed the effective flow control over an airfoil with an inflow velocity of 100 m/s using a symmetrically arranged encapsulated electrodes actuator; Kelley et al. [18] achieved effective flow control with an inflow velocity at a Ma 0.4 and a Reynolds number of 2.3 × 10 using 3.175-mm-thick ceramics as the insulatingmaterials. Using NS-SDBD plasma actuation, Nishihara et al. [20] demonstrated effective bow shock perturbations with an incoming flow Mach number of five. However, the drawback of plasma flow control is its low efficiency of energy conversion (the surface discharge-induced kinetic efficiency versus the discharge current is only several percent) [14]. The part of the electrical energy which is converted to heat remains useless as far as flow control applications are concerned [21–24]. Meng et al. [25,26] and Cai et al. [27] proposed a researchmethod for icing control using AC-SDBD plasma actuation, which can make full use of the aerodynamic and thermal effects of SDBD plasma discharge. Meng et al. [26] and Cai et al. [27] showed the feasibility of SDBD plasma icing control on a cylinder model. The anti-/deicing performance of the AC-SDBD plasma actuator was evaluated based on visualization and thermal images in an icing wind tunnel. Compared with the traditional anti-/de-icing system, AC-SDBD plasma almost satisfies all the icing control requirements of the nextgeneration aircraft design. First it can be flush mounted on the surfaces without interfering with the flow to keep the natural laminar flow, and it can be used for flow control when the aircraft is not in the icing condition during flight. Second, it can fully use the discharge energy of the AC-SDBD, i.e., both the thermal and aerodynamic effects. Besides, the self limiting nature of the discharge limits the rise in temperature of the AC-SDBD plasma thereby protecting the composite structures from over-heating during anti-/deicing. Lastly, with the development of the model battery technology, the AC-SDBD actuator can be powered by battery-driven pocket highvoltage generators, which have been installed on unmanned aerial vehicles in several field tests as electronic rudders [28]. Therefore, the AC-SDBD actuators can be comfortably mounted on an all-electric aircraft as a full electric-based icing control technique. Received 8 August 2019; accepted for publication 7 October 2019; published online 13 February 2020. Copyright © 2020 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www .copyright.com; employ the eISSN 1533-3868 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. *Graduate Student; currentyDoctorate, IowaStateUniversity, Iowa 50011. Professor; mxsbear@nwpu.edu.cn (Corresponding Author). Professor; jcai@nwpu.edu.cn. Assistant Professor; zhouww@sjtu.edu.cn. Assistant Professor; liuya19@ecu.edu. **Professor; huhui@iastate.edu.