The design of a series of electrothermal ice protection systems

This paper focuses on the design of ice protection system of aircraft components under different inflight icing characters. A numerical simulation method based on Euler-Euler multiphase coupling model was adopted to design the electrothermal anti-icing system for aircraft components with atypical shapes such as radomes on fuselages. For the calculation of droplets impingement, 3D N-S equations and standard k-ε turbulence model were applied to improve the simulation precision of flow fields and droplets concentration fields of complex configurations. The Langmuir distribution model of droplet diameters was introduced and the numerical solutions are compared with that of uniform average diameter. Some representative validation examples are presented, including an airfoil, a 2-D cylinder and a 3-D sphere, by comparing our results with the dissertations' ones which come from experiments or numerical simulations of authoritative organizations. The calculated thermal loads of real components are compared with that of the previous used engineering method. The electrothermal anti-icing system designed as a product had been tested in engineering practice for a long time.