增升装置连式襟翼噪声抑制技术试验研究  

Experiment Research of the High Lift Device Noise Reduction Technology Based on Continuous Mold-line Links

作　　者：周国成[1,2] 陈宝[1,2] 谭啸[1,2] ZHOU Guo-cheng;CHEN Bao;TAN Xiao(Low Speed and High Reynolds Aerodynamics Aeronautics Key Laboratory,AVIC Aerodynamics Research Institute,Harbin 150001,China;Aerodynamic Noise and Control Key Laboratory of Heilongjiang Province,AVIC Aerodynamics Research Institute,Harbin 150001,China)

机构地区：[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

出　　处：《科学技术与工程》2023年第2期838-844,共7页Science Technology and Engineering

摘　　要：机体噪声控制是当前民用飞机降噪技术研究的热点,增升装置的襟翼边缘噪声是机体噪声的重要组成。为了研究增升装置降噪技术,以L1T2翼型增升装置为对象,设计了两种不同偏角下的连式襟翼模型,通过声学风洞试验对其降噪效果进行研究。采用传声器相位阵列以及远场线阵等测试设备,结合波束形成、声压级积分、频谱分析等分析方法,研究了不同襟翼偏角和迎角下L1T2增升装置气动噪声特性以及连式襟翼的降噪效果。研究表明:襟翼偏角0°/30°时,襟翼边缘噪声成为L1T2翼型襟翼噪声的主要噪声源,并随着迎角的增大而增大;襟翼偏角为0°/20°和0°/30°时,连式襟翼均能产生明显的降噪效果,且偏角越大,降噪效果越明显;此外,连式襟翼的降噪效果随着迎角的增大略有减小。Airframe noise reduction is the hotspot of civil aircraft noise reduction currently,the flap side noise of high lift device is a major component of airframe noise.In order to study high lift device noise reduction,L1T2 was chosen as the research object,two kinds of continuous mold-line links of different deflection angles were designed and experimentally studied in aero-acoustic wind tunnel.Microphone phased array and far-field line array combining conventional beamforming.SPL integration and spectral analysis was adopted to study the acoustic characteristic and noise reduction effect of continuous mold-line links applied to L1T2 high lift device at different flap deflection angles and angle of attack.Test results show that flap side edge noise becomes a major noise source of L1T2 at flap deflection angle of 0°/30°,and the noise level increases with angle of attack.Continuous mold-line links provides substantial noise reduction effect at flap deflection angle of 0°/20°and 0°/30°,the noise reduction effect become more profound when the flap deflection angle increases,besides,the noise reduction effect decreases slightly when the angle of attack increases.

关 键 词：连式襟翼 襟翼边缘噪声 风洞试验 降噪特性 声源定位 

分 类 号：V211.79[航空宇航科学与技术—航空宇航推进理论与工程]