AC-SDBD等离子体激励防结冰特性与机制  

Anti-icing Characteristics and Mechanism of AC-SDBD Plasma Actuation

作　　者：惠伟伟 李昌 蔡晋生[1,2] 孟宣市 Hui Weiwei;Li Chang;Cai Jinsheng;Meng Xuanshi(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Science and Technology on Aerodynamic Design and Research,Xi’an 710072,China)

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]翼型、叶柵空气动力学国家级重点实验室,陕西西安710072

出　　处：《气动研究与试验》2025年第2期82-95,共14页Aerodynamic Research & Experiment

基　　金：国家自然科学基金(12072284,11672245,11772263);沈阳市飞机结冰与防除冰重点实验室项目(XFX20220303);民机项目(CARP-2018F8-3);国家级重点实验室基金项目(9140C420301110C42);飞行器复杂流动与控制引智基地项目(B17037)。

摘　　要：在静止大气中对AC-SDBD等离子体激励下的空气动力效应与热效应进行了显示和测量,通过结冰风洞试验研究了NACA0012翼型表面等离子体激励防结冰特性,对其防结冰机制进行了阐述。静止大气中的试验结果表明,AC-SDBD等离子体激励下激励器表面有明显的热效应;最高温度(120℃)位于裸露电极与掩埋电极的接缝附近;丝状放电部分区域温度高于均匀放电区域;掩埋电极上表面温度保持在40℃以上,沿诱导射流方向逐渐降低;其空间诱导速度场最大速度约4m/s,相应的体积力约800N/m3。结冰风洞试验结果表明,-15~-5℃静温范围,本文的AC-SDBD等离子体防结冰系统可以有效保证翼型前缘关键气动部分不出现积冰;-5℃静温来流条件下可以保证整个翼面不结冰,而-10℃与-15℃静温下不出现结冰面积分别为80%和50%。基于防冰表面积计算的功率密度与来流静温呈线性关系。The aerodynamic and thermal effects excited by an AC-SDBD plasma actuator are visualized and measured in a static atmosphere.The anti-icing characteristics of the actuators placed on a NACA0012 airfoil surface are studied through icing wind tunnel experiment,and its anti-icing mechanism is described.The experimental results in static atmosphere show that there is an obvious thermal effect on the surface of the AC-SDBD plasma actuator.The maximum temperature(120℃)is located near the joint of the exposed electrode and the buried electrode;The temperature in the part of filamentous discharge is higher than that in the uniform discharge area;The temperature of the upper surface of the buried electrode remained above 40℃and gradually decreased along the direction of the induced jet;The maximum velocity of the space induced velocity field is about 4m/s and the corresponding body force is about 800N/m3.The experiment results in icing wind tunnel show that the AC-SDBD plasma anti-icing system in this paper can effectively ensure that the key aerodynamic parts,ie.the leading edge of the airfoil,do not accumulate ice in the static temperature range of-15℃~-5℃.Under the condition of 5℃static temperature incoming flow,the whole surface can be free of ice,while the areas without ice under-10℃and-15℃static temperature are 80%and 50%respectively.The power density calculated based on the anti-icing surface area has a linear relationship with the static temperature of the incoming flow.

关 键 词：表面介质阻挡放电 等离子体 防结冰 流动控制 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]