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

Abstract

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