航空工程学院系列学术讲座

讲座时间：2021年8月16-18日下午15：30-17：30
讲座地点：腾讯会议ID：367 8492 4804 密码2200

主办单位：航空工程学院 国际合作部 研究生处

讲座内容：流动和传热
面向对象：全校师生
讲座专家：吴宏伟

1、专家简介：

吴宏伟（Hongwei Wu）

University of Hertfordshire, UK.  Associate Professor（副教授）

PhD (Distinction) Mechanical & Thermal Engineering (Thermofluids), 2004, Beihang University & HongKong University of Science and Technology, China MSc (Distinction) Mechanical & Thermal Engineering(Thermofluids)

工作经历：

学术成就：

发表期刊论文被SCI收录90余篇，发表高层次会议论文3余篇，出版专著4部，先后担任近40本国际学术期刊编委和审稿人，担任近20次国际学术会议的主持人和召集人，在近30次国际会议上被邀请大会发言；指导博士后、博士和接受国际访问学者20余人。

2、讲座内容简介

（1）Flow and Heat Transfer in Microchannel

Miniaturization of electronic devices has led to advances in various engineering fields, including space technology, defense systems, aerospace applications, manufacturing technology, industrial processes and consumer electronics. Heat dissipation in the electronic components, however, is being a critical issue due to the faster increase in the components’ heat flux and increasing demand for the miniature in features’ size. The heat flux of the electronic chips may exceed 400 W/cm² in order to meet the demand for high performance electronic components. Since overheating of the electronic components degrades the components’ performance, reliability and even cause failure of the components, high performance cooling techniques are required to keep device temperatures low for acceptable performance and reliability. The microchannel heat sink (MCHS) is a concept well suited for many electronic applications because of its ability to remove a large amount of heat from a small area.

（2）3D Modelling and Simulation of Ice Accretion Process on Aircraft Wings

Aircraft icing has long been recognized for over sixty years and continues to be an important flight safety issue in the aerospace community. Ice accretion on an aircraft wing occurs when supercooled water droplets in the atmosphere impact on the surface of aircraft’s wings. The formation of ice on an aircraft wing results in a sharp increase in drag and a reduction in maximum lift. Furthermore, ice accretion on aircraft wings also leads to a reduction in stall angle and increment in moment coefficient of the wing. This causes a deterioration in the aerodynamic performance of the aircraft. Although many significant results in numerical models of ice accretion have been already obtained by now, the comprehension of the ice accretion mechanism on aircraft wing is still quite limited, especially for the cases of 3D, and there is still much room for improvement.

（3）Performance Analysis of a Loop Heat Pipe Integrated with Thermoelectric Cooler Under Acceleration Field

Loop heat pipe (LHP) is a high efficient and reliable two-phase heat transfer device, which utilizes the vapor-liquid phase change of working liquid in evaporator and condenser. Compared with traditional heat pipe, LHP possess the advantages of long-distance heat transfer capability, flexible installation, precise temperature control and anti-overload acceleration. Over the past three decades, LHPs have been widely applied in various aircraft, spacecraft and electronic cooling equipment. Different from conventional LHP, the dual compensation chamber loop heat pipe (DCCLHP) has two compensation chambers (CCs) distributed at both ends of the evaporator, which enables the capillary core to be more effectively infiltrated under gravity field or acceleration field. Some previous researches have proven that DCCLHP could work successfully under some extreme conditions such as anti-gravity or subjected to acceleration forces.