THE PERFORMANCE COMPUTATION OF THE HOT AIR ANTI-ICING SYSTEM OF AN AERO-ENGINE CONE

摘要

Ice accretion on the inlet of an aero-engine could adversely affect the characteristics of the inlet flow field and degrade the engine 's performance. When the accrued ice sheds, the ice sucked into the engine could induce serious damages. In order to reduce the hazards caused by in-flight icing, an anti-icing or de-icing system should be used. Hot air bleeding from high pressure compressor is widely used in the inlet anti-icing system, such as the cone and inlet guide vane. The anti-icing system can prevent ice accretion on the inlet component's surface, and consequently ensure the flying safety. A numerical method of the temperature prediction on the cone surface under icing conditions is presented. The flow field of external and internal flow is solved in 2D axisymmetric coordinate by using Fluent. The droplets impingement property and surface temperature of the cone are predicted by external solver which based on the energy balance analysis. Comparisons between the computational results and the experimental data are presented.