热气防冰腔结构参数对其热性能影响研究  

Influence of the structural parameters on thermal performance of the hot air anti-icing system

作　　者：彭珑[1,2] 卜雪琴[1,2] 林贵平[1,2] 马文涛[1,2] 赵凯 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]北京航空航天大学人机工效与环境控制重点学科实验室,北京100191 [3]哈尔滨飞机工业集团有限责任公司飞机设计研究所,黑龙江哈尔滨150066

出　　处：《空气动力学学报》2014年第6期848-853,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(51206008);航空基金(2012ZBN2016)

摘　　要：采用数值模拟方法,开展了热气防冰系统结构参数对其热性能影响的研究。首先建立了不同管壁距、喷孔排数、喷口喷射角度的防冰腔结构,运用计算流体力学方法对其内部热气流动与换热进行了模拟,得到了防冰腔热效率以及热气喷射蒙皮内表面的对流传热系数的分布。结果表明:管壁距在4mm至36mm范围内增大,将降低防冰腔的热效率,并且弱化射流正对冲击表面传热性能;流量一致时,喷孔排数由3排减至2排,提高了防冰腔热效率;3排喷孔射流角度朝上表面方向旋转15°,将会提升防冰腔热效率,表明曲面曲率影响射流表面传热性能。The hot air anti-icing system is one of the important ways to prevent aircraft icing.Numerical simulation method was carried out to study the influence of the structural parameters on the thermal per-formance of the hot air anti-icing system.The hot air flow and heat transfer in the anti-icing cavities with different nozzle-to-surface height,number of the nozzle rows and hot air jet angle were simulated using the computational fluid dynamics （CFD）method.The thermal efficiency of the anti-icing system and the convec-tive heat transfer coefficient distribution of the skin inner surface were obtained.The results show that：1） with the increase of the nozzle-to-surface height in the range of 4mm to 36mm,the thermal efficiency of the anti-icing system reduces and the heat transfer performance of the hot air impinging on the surface weakens, 2）with consistent flow flux,the thermal efficiency of the anti-icing system increases from three to two noz-zle rows,3）the thermal efficiency improves with the 15°rotation of the hot air jet angle along the upper sur-face direction,indicating that the surface curvature effects the jet surface heat transfer performance.The results presented in this paper can help to the design of the anti-icing cavity.

关 键 词：热气防冰腔 热效率 结构参数 表面传热系数 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]