Thermal Analysis and Testing of Nonrotating Cone with Hot-Air Anti-Icing System

摘要

A hot-air film-heating method designed for the anti-icing system of a small aeroengine cone is studied as well as an experimental study on its performance. Experiments are conducted under different icing conditions and hot air parameters in an icing wind tunnel, using a full-scale experimental cone model of a small aeroengine. The temperature distributions on the cone surface are measured by thermocouples. Experiment results show that the hot-air film anti-icing method is effective for the cone leading edge. Also presented is a numerical simulation of the temperature distribution of the aeroengine cone under icing condition. The flowfield around the cone is obtained by computational-fluid-dynamics code. The trajectories of supercooled water droplets and the collection efficiency are calculated by the Lagrangian approach. The coupling effects of heat transfer and mass transfer are considered in the temperature computation of the cone. The thermal analysis model considers the mass balance of water and energy balance on the surface of the cone. The simulation results are compared to the experiment measurements. The characteristics of the hot-air film-heating anti-icing method are also discussed.