航空发动机动叶积垢数值模拟研究

Numerical simulation of blade fouling in aero engine

基于NASA公布的Stage 36叶型及进气道数据,利用DPM离散相对ash,CaCO3及Al2O3颗粒不同粒径、颗粒入射速度等条件对颗粒运动轨迹及叶片壁面颗粒沉积速率进行研究。颗粒直径增大、材料密度增加、低入射速度情况下将造成压气机叶片表面的颗粒物沉积速率逐渐加剧。叶片压力面区域相对于吸力面积垢沉积率较大,叶根区域相对于叶尖区域更容易产生积垢。

Based on the NASA’sinformation on the Stage 36 blade profile and inlet,the analysis is conducted on the motion trajectories of different particles(ash,CaCO3 and Al2O3)and the deposition rate on the blade surface,by means of the DPM discrete relative to particle size,incident velocity and other conditions.Such factors as ever-growing particle diameter and material density,and low incident velocity will gradually enhance the deposition rate particles on the compressor’s blade surface.Compared with the blade’s suction area,the pressure area has a larger fouling deposition rate,and the root area is more likely to produce fouling than the tip area.