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

作　　者：付在国 冯文杰 王子婧 刘斌[2] FU Zaiguo;FENG Wenjie;WANG Zijing;LIU Bin(College of Energy and Mechanical Engineering,Shanghai University of Electric Power,Shanghai 201306,P.R.China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,P.R.China)

机构地区：[1]上海电力大学能源与机械工程学院,上海201306 [2]西北工业大学航空学院,西安710072

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2023年第6期663-677,共15页南京航空航天大学学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (No.51902256);the Aeronautical Science Foundation of China (No. 2020Z057053002)。

摘　　要：飞机在过冷大水滴条件下运行时,受科里奥利力和离心力作用的发动机旋转部件会表现出与静止部件不同的积冰特性。本文考虑了过冷大水滴的终端沉降速度、变形破碎和飞溅反弹动力学特性,并采用多重参考坐标系方法处理旋转条件下的流动和传热,对发动机进口部件包括进气道唇口、整流罩和风扇叶片的液滴撞击及积冰特性进行了三维数值模拟。转速为0、2 000和4 100 r/min情况下的模拟结果表明,随着转速的增加,进气道唇口上的积冰从唇口内表面向其外表面移动。此外,旋转叶片上的积冰主要集中在叶片根部位置,且积冰量随转速增加而减少。进气道唇口和整流罩上的冰层厚度随转速的增加而增加,转速为4 100 r/min下的进气道唇口和整流罩上的最大积冰厚度与静止状态相比分别增加了0.27倍和2.46倍。此项工作能够为后续的防/除冰技术发展提供参考。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 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]