摘要
当飞机在低温、多云等气象条件下飞行时,航空发动机前端部件极易发生结冰现象,严重影响发动机的气动性能和飞机的飞行安全。当前防冰结构设计主要是通过热气引气进行防护,不可避免会降低发动机性能。为应对这一问题,针对某型航空发动机进口整流支板,提出了热管与热气耦合方法,设计了一种热气热管复合防冰结构,并对其性能展开深入研究。研究表明,热气热管复合防冰结构可将传统通道热气防冰结构所需引气量的12 g/s降至8 g/s,部分非恶劣工况可降至7 g/s,同时保证整流支板前部水滴撞击区域表面温度均在2℃以上;在慢车状态下,该结构的前缘最大温差为26.14 K,较传统结构减少55.7%,显著提升了均温性;在最大连续状态下,其温差为79.46 K,较传统结构减少25%,且在引气量需求上仍具优势。相较传统热气结构方案,热气热管方案大幅减少了热气消耗,降低了发动机性能损失,为高效节能的航空发动机整流支板防冰设计提供了新的技术路径和理论依据。
When an aircraft flies in icy weather conditions such as low temperature and cloudy weather,the front-end components of the aircraft engine are prone to icing,which seriously affects the aerodynamic performance of the engine and the flight safety of the aircraft.The current anti-icing structure design mainly relies on thermal protection through hot air entrainment,which inevitably reduces engine performance.To address this issue,a heatpipe and hot gas coupling method is proposed for the imported rectifier strut of a certain type of aircraft engine.A hot gas heatpipe composite anti-icing structure is designed,and its performance is extensively studied.Research shows that the composite anti-icing structure of hot air heatpipes can reduce the required air intake of traditional channel hot air anti-icing structures from 12 g/s to 8 g/s,and in some non harsh working conditions,it can be reduced to 7 g/s.At the same time,it ensures that the surface temperature of the water droplet impact area in the front of the strut is above 2℃.Compared to traditional hot gas structure schemes,the hot gas heatpipe scheme significantly reduces hot gas consumption and engine performance loss,providing a new technical path and theoretical basis for efficient and energy-saving anti icing design of aircraft engine rectifier strut.
作者
朱宇轩
连文磊
陈小明
ZHU Yuxuan;LIAN Wenlei;CHEN Xiaoming(Nanjing University of Aeronautics and Astronautics,Nanjing Jiangsu 210001,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou Hunan 412002,China)
出处
《海军航空大学学报》
2026年第1期167-176,共10页
Journal of Naval Aviation University
