Numerical Simulation of Icing Characteristics on the Surface of an Aero-engine Guide Blade

Abstract This paper takes the guiding blade of a type aero-engine needle as research object for icing problem and uses numerical simulation method to simulate airflow field, supercooled water droplet impact situation on surface under different flight conditions, analyze influence speed blade. It is found that incoming flow velocity has significant effect guide vanes, with increasing from 34m/s 102m/s, leading edge vanes increases by 98.1%; meanwhile, range significantly related velocity, increasing, expands significantly; in addition, gradually root outermost end The maximum at 102m/s was extended 17% 20% chord length.