Study on electrothermal anti-icing system of engine inlet flow guide vane with different heating mode

Aircraft engine inlet icing seriously endangers flight safety, and anti-icing technology is of great significance to ensure flight safety. In this paper, the icing model based on the idea of Messinger is established, and the icing and electrothermal anti-icing of the flow guide vane are studied through numerical simulation and Icing Wind Tunnel (IWT) test. All the results indicate that the icing of the flow guide vane mainly distributes in the region of leading edge, and the icing range does not change with time when the heating flux is constant. The final residual ice thickness of the continuous heating mode is smaller than that of the intermittent heating mode, but the runback water area is more obvious than that of the intermittent heating mode, and the total energy consumption of the continuous heating mode is larger than that of the intermittent heating mode.