Research on Numerical Simulation of Glaze Ice for Aircraft and Aero-Engine Entry Components

Abstract

A 3D glaze icing numerical method for aircraft and aero-engine entry Components was presented. The Eulerian - lagrangian model was employed to simulate the air- water two phase, and the distribution of impingement droplet was obtained. Mass and energy balance were established in a control volume, then ice accretion code was completed using UDF (User Defined Function), which was provided by FLUENT. This program can calculate glaze icing, Rime icing and mixed icing. The calculation of icing on NACA0012 3D airfoil is carried out, and compared with the experimental results in literature. The results show that the maximum icing thickness is in good agreement with the experimental results, and the predicted ice shape is consistent with the experimental ice shape development trend. The calculation results show that the proposed icing calculation method is effective and reliable. On the basis of this, centre conical body is calculated, the qualitative analysis of results. It can be seen from the calculation results that three typical ice types are formed near the stationary point of the centre conical body under different inlet temperature conditions. It is also found that the temperature has not a great effect on the amount of icing. The research results provide an alternative way for the calculation of three-dimensional icing formation for aircraft and aero-engine, and can be used to improve the design technology of anti icing system.