Performance Analysis Of Hot Air Anti-icing System Of Aeroengine Inlet Guide Vane Of Complex Material

The main research in this thesis is designing a new anti-icing thermal system of aeroengine inlet guide vane.First, numerical simulation is taken, a three-dimensional numerical model is established in this thesis according to the ice tunnel experimental condition. Then, the momental equations of super-cooled water droplets are established by Euler method, and the distribution of water collection coefficient on the guide vane surface is calculated by solving these equations. Finally, the anti-icing thermal loads of both evaporative systems and running wet systems are calculated by establishing and solving the mass and energy conservation equations. By summarizing the results, the influences of elements including flying speed, air temperature, and mean vali diameter on water collection coefficient as well as thermal loads are concluded.In the experimental research, an icing wind tunnel experiment is carried out to test the result of the thermal loads. An open-circuit icing wind tunnel is constructed to simulate both the flight condition and the weather condition of the guide vane, and hot-air is added to the thermal anti-icing system according to the calculated thermal loads. The results show that the method used in numerical simulation is correct.