摘要
飞机发动机防冰对飞行安全具有十分重要的意义，对于热气防冰系统，前缘防冰器的结构型式对防冰的效果影响很大．本文针对常见的周向及双蒙皮波纹板型弦向飞机发动机进气道热气防冰器进行了热分析，在此基础上对其传热性能及防冰表面温度场进行了比较，结果表明双蒙皮弦向防冰器的防冰效率较高；在通常情况下，周向防冰器也可达到防冰的目的，并且结构简单，因而更为实用．
Two patterns of air plane engine inlet hot air anti icer are introduced in this paper,one is circumferential anti icer,the other is double skin corrugated chord direction anti icer.Based on the thermal analysis of the two anti icers,the heat transfer performance and temperature field of ice protected surface are compared.The results indicate that the structure of frontal anti icer affects anti icing effectiveness obviously for a hot air anti icing system,the double skin chord direction anti icer is more efficient,but under the normal conditions,a circumferrential anti icer can attain the goal of ice protection and its structure is more simple,so it is more practical.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1999年第2期201-203,共3页
Journal of Beijing University of Aeronautics and Astronautics
关键词
进气道
防冰系统
热平衡
航空发动机
engine inlet
anti icing system
properties
heat balance
