Performance Analysis Of Micro-ejector Anti-icing Tunnel

Aircraft icing is a common phenomena when aircraft flying under certain icing conditions, and aircraft icing may lead to severe adverse effect to the aircraft safety. Usually aircraft anti-icing system is used to deal with this problem. The micro-ejector anti-icing system is a kind of efficient and economical way to prevent the ice accretion on aircraft. In this thesis, the performance of a micro-ejector anti-icing system was investigated with computational and experimental methods.This thesis is mainly composed of the following three parts:1. The heat transfer of single-hole jet impinging on concave surface was investigated with numerical simulation package-FLUENT firstly. According to the comparison of the results between numerical method and experiment, it indicates that the numerical simulation can be used to investigate this problem, and the relative computational method and turbulence model was chosen.2. An experiment about a micro-ejector anti-icing system was conducted to investigate its performance.3. The performance of the micro-ejector anti-icing system was studied with computational method, and the results agree well with the experimental data. Then, the performance of micro-ejector anti-icing system with variable structures was investigated with numerical method.Compared with experimental method, the numerical method can give detailed flow field in the anti-icing cavity and the temperature contour in the airfoil skin, which makes it possible to analyze the method to improve the performance of micro-jet anti-icing system. The research in this thesis provides a way for the performance optimization of micro-ejector anti-icing system.