Effects of Film Holes Position on Anti-icing Characteristics of Aero-engine Inlet Adjustable Blade

In order to obtain the influence of film hole position on the anti-icing characteristics of aero-engine inlet adjustable blade, numerical simulation and experimental investigation was carried out for different film hole structure of the blade. The performance of different film hole position (include the trailing edge, the side wall and the rotating shaft of strut) and blowing ratio on the heating effects of the adjustable blade surface were analyzed, and experimental verification was carried out under ice wind tunnel conditions. The results show that with the increasing of blowing ratio, the temperature of adjustable blade increases gradually. The surface with film holes located at the trailing edge has the highest temperature, which is 315 K. Under the same working conditions of mainstream and hot air, the trailing edge inclined hole structure has the smallest ice thickness among the 3 structures. Based on the calculation and experimental results for anti-icing of different positions film hole structures on the adjustable blade, the inclined film holes at the trailing edge has better heating and icing protection effect.