发动机唇口电热防冰系统性能仿真  

Numerical simulation of performance of engine lip electro-thermal anti-icing system

作　　者：吴佩佩 晏涛[1] 马赛强 何泳[1] 任杰[1] WU Peipei;YAN Tao;MA Saiqiang;HE Yong;REN Jie(Chengdu Aircraft Industry Group Company Limited,Aviation Industry Corporation of China Limited,Chengdu 610092,China)

机构地区：[1]中国航空工业集团有限公司成都飞机工业(集团)责任公司,成都610092

出　　处：《航空动力学报》2020年第10期2056-2063,共8页Journal of Aerospace Power

摘　　要：采用三维耦合传热方法对发动机唇口电热防冰系统进行了多状态下的性能仿真,获得了唇口表面平衡温度及动态温升响应时间,以此评估防冰系统性能,并通过与冰风洞试验结果对比,对仿真过程进行了修正。研究表明:唇口表面加热区平衡温度均高于273.15 K,温升响应时间小于60 s,满足防冰需要,较为严酷的防冰状态点主要为飞行速度较大、环境温度较低的状态点;修正唇口材料导热系数后,仿真与试验结果吻合良好。研究结果能有效指导工程研制,对提高防除冰仿真分析结果的准确性提供了很好的借鉴。A three-dimensional coupled numerical simulation method was applied to simulate the performance of an engine lip electro-thermal anti-icing system at different conditions. The balance temperature of engine lip surface and the dynamic response time of surface temperature rise were obtained to estimate the performance of the anti-icing system. The simulated results were compared with experimental results in icing tunnel. And based on the comparison,simulated results were corrected. The study showed that the balance temperature of engine lip heating surface was above 273.15 K and the dynamic response time was less than 60 s,indicating that this anti-icing system could meet the requirement,and the severe anti-icing conditions were mainly those with higher flight speed and lower ambient temperature. And after correction the simulation coincided with experiment. The results can effectively guide the engineering development and provide a reference to improve the accuracy of anti-icing simulation.

关 键 词：发动机唇口 电热防冰 性能仿真 表面温度 温升响应时间 

分 类 号：V244.1[航空宇航科学与技术—飞行器设计]