南京航空航天大学学报（英文版）2023，Vol.40Issue(6)：663-677,15.DOI:10.16356/j.1005-1120.2023.06.004
发动机进口旋转部件的三维积冰数值模拟
Three-Dimensional Numerical Simulation of Ice Accretion on Rotating Components of Engine Entry
摘要
Abstract
The rotating engine components subject to Coriolis and centrifugal forces exhibit distinctive ice accretion characteristics when an aircraft operates under supercooled large droplet conditions.This study establishes the mathematical model of the ice accretion on rotating components of engine entry and considers the dynamic characteristics of terminal velocity,deformation,breakup,splash,and rebound of supercooled large droplets.The multiple reference frame method is employed to deal with the fluid flow and heat transfer under the rotating condition.A three-dimensional numerical simulation is conducted to investigate the droplet impingement and ice accretion characteristics of entry components,including the inlet lip,spinner,and fan blades.The simulation results at rotational speeds of 0,2000,and 4100 r/min show that the ice accretion on the inlet lip moves towards the outer surface of the inlet lip from the inner surface as the rotational speed increases.Moreover,the ice accretion on the blades is mainly concentrated at the blade root,and the ice accumulation decreases with the increase of rotational speed.The ice thickness on the inlet lip and spinner increases with increased rotational speed.The maximum ice thickness on the inlet lip and spinner under the rotational speed of 4100 r/min increases by 0.27 and 2.46 times,respectively,compared to the stationary condition.This work can serve as a reference for developing subsequent anti/de-icing technology.关键词
航空发动机/三维结冰预测/过冷大水滴/旋转叶片/数值模拟Key words
aero-engine/3D icing prediction/supercooled large droplets/rotating blade/numerical simulation分类
航空航天引用本文复制引用
付在国,冯文杰,王子婧,刘斌..发动机进口旋转部件的三维积冰数值模拟[J].南京航空航天大学学报（英文版）,2023,40(6):663-677,15.基金项目
This work was supported by the Na-tional Natural Science Foundation of China(No.51902256)and the Aeronautical Science Foundation of China(No.2020Z057053002).The authors would like to thank Mr.XIA Quanzhong from Sichuan Gas Turbine Establishment of Aero Engine Corporation of China for supporting the calcula-tion. （No.51902256）
