摘要
在采用数值模拟方法对某型发动机导向叶片热气防冰腔的流动与换热性能分析基础上,提出了微小通道换热结合气膜排气的新型防冰腔结构。数值模拟中采用分区对接块结构化网格,通过求解EULER型的空气/过冷水滴两相流控制方程,得到了气膜影响下导向叶片外的三维水滴撞击特性,并将改进后防冰腔的换热性能进行了对比。结果表明,改进后的热气防冰腔的换热效率得到了大幅提高,同时气膜对过冷水滴的遮蔽作用明显增强。
Improvement of hot-air anti-icing structure of an engine inlet vane is developed based on the numerical simulation of flow and heat transfer characteristics of the original system. The improved structure is combined with micro channels to enhance heat transfer characteristics and narrow gaps releasing exhausted hot air to protect the surface from droplet impinging. 3-D Euler air/droplet two-phase model is used to solve the droplet impingement characteristics influenced by air film on patched structure mesh. Comparison of heat transfer characteristics of the improved and the original structures is also given. The results indicate that the improved system increases the heat transfer efficiency and prevents the structure from droplets impinging more effectively.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2013年第1期70-74,共5页
Journal of Nanjing University of Aeronautics & Astronautics
基金
南京航空航天大学基本科研业务费专项科研(NS2010002)资助项目
江苏高校优势学科建设工程资助项目
关键词
飞机结冰
发动机导向叶片
防冰
数值模拟
气膜
微小通道
aircraft icing
engine inlet vane
anti-icing
numerical simulation
air film
micro channels
