Numerical simulation of electro-thermal anti-icing system for an engine inlet lip

Freezing of supercooled water droplets on engine inlet surfaces is a dangerous situation in aircraft icing, and hot air-based de- icing methods are commonly employed to avoid the build-up of ice. However, electro-thermal anti-icing systems are needed for the aircraft with small flow rate of hot air. In this paper, an engine inlet with a bypass passage is simulated numerically during take-off, cruise and descend to analyse its air flow, the supercooled water droplets impingement characteristics and the electro-thermal anti-icing temperature of the engine inlet lip. The phenomena show that the surface pressure distribution of the engine inlet is affected by flight altitude and intake air flow rate under the action of the bypass branch. Supercooled water droplets hit the front edge of the engine inlet lip, and the impingement characteristics are affected by the flight speed and intake flow rate. The anti-icing surface temperature of the engine inlet lip corresponding to the electric heating device is high, but the temperature decreases rapidly after leaving the heating area. The electro-thermal anti-icing system of the engine inlet lip has good performance in take-off, cruise and descend. This research has certain guiding value for the plan and check of engine anti-icing systems.