机翼热气防冰系统设计  

Investigation of the design of wing hot-air anti-icing system

作　　者：卜雪琴[1] 郁嘉[1] 林贵平[1] 宋馨[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院

出　　处：《北京航空航天大学学报》2010年第8期927-930,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：利用热流体系统仿真分析平台Flowmaster和计算流体力学软件Fluent进行联合仿真,对机翼热气防冰系统进行了设计和性能分析.设计参数包括防冰系统笛形管热气喷口孔径、孔数及孔间距等参数.基于Flowmaster对所设计的供气管路进行供气流量分配计算.基于Fluent模拟防冰腔内流动与换热,计算了防冰腔的热效率.根据防冰热载荷及热效率结果预测每段缝翼防冰所需热气流量,引入参数供气余度来分析防冰系统热性能.所提出的热气防冰系统设计方法可为热气防冰系统的工程设计与优化提供重要的帮助.The thermal fluid system simulation tool Flowmaster and the computational fluid dynamic tool Fluent were combined for the simulation of the wing hot-air anti-icing system（WHAIS） design and thermal performance analysis.The design parameters contained the piccolo tube diameter,the jet hole diameter and the distance between holes.Mass flow of the hot air distribution per slat supplied by system was evaluated based on Flowmaster.Thermal efficiency of the WHAIS was predicted based on Fluent.The heat required for anti-icing was determined according to the results of external heat loads and the thermal efficiency of the system.Margin of the hot-air supply was introduced to analyze the WHAIS thermal performance.The method presented can be used in the engineering design and optimization of the WHAIS.

关 键 词：热气防冰系统 设计 笛形管 热性能 供气余度 

分 类 号：V224[航空宇航科学与技术—飞行器设计] V244.15