Optimal Design And Numerical Simulation Of The Hot Air Cavity Structure

Aircraft flying at subsonic speeds through clouds between 3000 meters to 8000 meters can be subject to ice formation on critical, the aircraft icing may lead to serious results, so in icing conditions required the use of ice protection systems. Hot air anti-icing system currently is the most widely used in commercial aircraft, because of the performance limitation of the core engine of current aircraft and the excessive use of hot air and low utilization of the ice protection systems, In this paper, I optimized anti-icing cavity structure by numerical simulation, analysis various parameters impact on the temperature distribution in the protection zone and the efficiency of anti-icing, in order to optimize the design of anti-icing chamber structure, improve heat efficiency.For the structural characteristics of anti-icing cavity, this paper is mainly composed of the following three parts:â‘ design the piccolo structure by the heat load curve along the spanwise of the wing which calculated by the outfield, analysis change of the parameters of the jet nozzle;â‘¡design the anti-icing cavity structure except the piccolo, after install the piccolo, analysis the change of the skin temperature and the efficiency of anti-icing system with the vary of geometric parameters of the thermodynamic parameters;â‘¢B ased on the contents discussed above , Re-optimize the anti-icing chamber and then Coupling calculate the flow field both in and out by CFD, finally, check the results.This paper fully use numerical simulation method, there must be some errors, only provides a qualitative judgments for anti-icing system design, lack of comparison with the experimental results. But laid the foundation for following job, supply a great reference value.