Page 45 - 《应用声学》2022年第6期
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第 41 卷 第 6 期                                                                       Vol. 41, No. 6
             2022 年 11 月                         Journal of Applied Acoustics                 November, 2022

             ⋄ 研究报告 ⋄



                          大型航空声学风洞消声室建设与校测





                                   周国成      1,2†  陈 宝     1,2  李周复     1,2   姜 涛    1,2


                            (1  中国航空工业空气动力研究院        低速高雷诺数气动力航空科技重点实验室            哈尔滨   150001)
                           (2  中国航空工业空气动力研究院        空气动力噪声及其控制黑龙江省重点实验室             哈尔滨   150001)

                摘要：风洞试验是进行民用飞机机体噪声研究的重要手段。为了满足航空飞行器低噪声设计在大型风洞中进
                行气动噪声试验的需求，中国航空工业空气动力研究院建设了 FL-10 大型低速风洞全消声室。通过在 FL-10
                风洞试验大厅壁面安装吸声尖劈、对洞体外表面进行声学处理、对支撑系统进行隔声处理、对消声换气窗进行
                降噪处理等手段，建成了气动噪声风洞试验所需的声学环境。按照国家标准中给定的方法，利用张线方法实现
                了校准声源的布置，测量了消声室内沿不同路径、不同频率噪声的衰减规律，表明 FL-10 风洞消声室自由场特
                性达到了相应标准的要求，为后续在该风洞中进行大尺寸机体模型噪声试验奠定了基础。
                关键词：声学风洞；消声室；气动噪声；自由场校测
                中图法分类号: O429           文献标识码: A          文章编号: 1000-310X(2022)06-0891-10
                DOI: 10.11684/j.issn.1000-310X.2022.06.006




                Anechoic chamber establishment and calibration of large scale aeroacoustic

                                                      wind tunnel


                              ZHOU Guocheng   1,2  CHEN Bao  1,2  LI Zhoufu 1,2  JIANG Tao 1,2

                 (1 Low Speed and High Reynolds Aerodynamics Aeronautics Key Laboratory, AVIC Aerodynamics Research Institute,
                                                    Harbin 150001, China)
                 (2 Aerodynamic Noise and Control Key Laboratory Of Heilongjiang Province，AVIC Aerodynamics Research Institute,
                                                    Harbin 150001, China)

                 Abstract: FL-10 wind tunnel is the largest low speed return-flow wind tunnel in China so far, the aero-acoustic
                 experiment ability was taken into consideration since the design period, a series of noise reduction design
                 methods were applied ever since its construction. In order to meet the aero-acoustic wind tunnel requirement
                 of aircraft low noise design, a large anechoic chamber was built and auxiliary equipment was acoustic treated
                 to guarantee the acoustic environment of aero-acoustic wind tunnel experiment. The construction of FL-10 low
                 speed wind tunnel aero-acoustic experimental environment, acoustic free field calibration and background noise
                 measurement was introduced in this paper, the background noise level of FL-10 is presented. The free field
                 calibration and background noise measurement results show that FL-10 wind tunnel has excellent aero-acoustic
                 properties and capable of undertaking large size aero-acoustic experiments for the low noise design of aircraft.
                 Keywords: Aeroacoustic wind tunnel; Anechoic chamber; Aeroacoustic noise; Acoustic free filed calibration

             2021-09-25 收稿; 2021-12-22 定稿
             作者简介: 周国成 (1984– ), 男, 湖南耒阳人, 硕士, 研究方向: 气动噪声风洞试验技术。
             † 通信作者 E-mail: zgc84111@163.com
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