拐角扩张比与导流片安装角对BHAW风洞流场品质影响的数值研究  

Numerical study of the effects of corner expansion ratio and installation angle of guide vanes on flow fields in BHAW wind tunnel

作　　者：刘沛清[1,2] 陈阅 张瑾 屈秋林[1,2] LIU Peiqing;CHEN Yue;ZHANG Jin;QU Qiulin(Key Laboratory of Aeroacoustics of Ministry of Industry and Information Technology,Beihang University,Beijing 100191,China;School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;Sino-French Engineer School/School of General Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学航空气动声学工业和信息化部重点实验室,北京100191 [2]北京航空航天大学航空科学与工程学院,北京100191 [3]北京航空航天大学中法工程师学院/国际通用工程学院,北京100191

出　　处：《空气动力学学报》2023年第9期82-95,共14页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(122720);气动噪声控制重点实验室开放课题(2002ANCL20200102)。

摘　　要：以北京航空航天大学4 m×3 m低湍流强度、低背景噪声的大型封闭回路气动声学风洞(BHAW)设计需求为工程应用背景,采用k-ωSST湍流模型进行了数值模拟,分析了在多个扩张比下的拐角导流片安装角对流场的影响。研究结果验证了在不同拐角扩张比下的总压损失系数均随导流片安装角增大而先减小后增大,且存在极小值点,极值点对应的导流片安装角与拐角扩张比呈现正相关。在不同的扩张比下,局部损失系数均随导流片安装角增大呈现先减小后增大的变化规律;相同导流片安装角下,拐角中部导流片的摩擦损失系数最大,导流片安装角的变化对中部导流片(即6~8号导流片)的流速影响较小;随着拐角扩张比增大,拐角出口管道内气流不均匀性增大,最佳导流效果的导流片对应的安装角增大。在综合考虑降低总压损失系数和减小管道出口气流偏角两个设计原则后,BHAW风洞为扩张比为1.17的第一拐角选择44°的设计安装角,为扩张比为1的第二、三、四拐角选择44°、43°、42.5°的设计安装角。通过数值计算验证了风洞试验段的核心区动压系数小于0.2%、速度水平偏角小于0.1°,满足BHAW气动设计要求。This article aims to provide technical support for designing the large closed-loop aeroacoustics wind tunnel with low turbulence intensity and low background noise at Beihang University(BHAW).The effects of the corner guide vanes angle on the flow fields are analyzed for several different expansion ratios by numerical simulations with the k-ωSST turbulence model,and the optimal installation angle of guide vanes for the BHAW wind tunnel is determined.Numerical results reveal that the pressure loss coefficient decreases first and then increases with the augmentation of the installation angle of guide vanes at each corner expansion ratio.The results further indicate the existence of a minimum pressure loss coefficient,and the installation angle of the guide vanes corresponding to the minimum value has a positive correlation with the corner expansion ratio.With various expansion ratios,the local pressure loss initially decreases and then increases with the guide vanes installation angle.The results demonstrate that the maximum friction loss coefficient occurs at the middle of the guide plate for a given installation angle;the installation angle mildly affects the flow around the central guide vanes(guide vanes 6,7,and 8).With the increase of the corner expansion ratio,the flow velocity uniformity at the corner outlet deteriorates,and the installation angle of the guide vanes with the best flow guiding effect increases.By minimizing the total pressure loss coefficient and velocity deflection angle at the pipeline outlet,BHAW adopted an installation angle of 44°for the first corner with an expansion ratio of 1.17,an installation angle of 44°for the second corner with an expansion ratio of 1,an installation angle of 43°for the third corner with an expansion ratio of 1,and an installation angle of 42.5°for the fourth corner with an expansion ratio of 1.Such a strategy results in the dynamic pressure coefficient in the core area of the wind tunnel test section being less than 0.2%and the horizontal velocity deflectio

关 键 词：气动声学风洞 数值计算 拐角导流片 导流片安装角 拐角扩张比 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]