民用大涵道比涡扇发动机风扇机匣声衬设计  

Fan Case Acoustic Liner Design of the High Bypass Ratio Turbofan Engine

作　　者：李旦望 夏烨 陈垂文 LI Dan-wang;XIA Ye;CHEN Chui-wen(AECC Commercial Aircraft Engine Co., Ltd., Shanghai 201108, China;Shanghai Center of Research for Commercial Aircraft Engine Engineering Techniques, Shanghai 201108, China)

机构地区：[1]中国航发商用航空发动机有限责任公司,上海201108 [2]上海商用飞机发动机工程技术研究中心,上海201108

出　　处：《科学技术与工程》2022年第17期7206-7211,共6页Science Technology and Engineering

基　　金：国家重点研发计划(2018YFA0703300)。

摘　　要：为了研究民用大涵道比涡扇发动机风扇机匣声衬的降噪效果,基于Wiener-Hopf管道声传播预测方法和声阻抗模型,形成了风扇机匣声衬设计流程和方法,对某民用大涵道比涡扇发动机风扇机匣开展声衬设计研究,包括风扇前和风扇/外涵出口导流叶片(outlet guide vane,OGV)之间两段声衬的设计。首先,选择边线和飞越两个适航工况的管道可传播声模态作为降噪目标声源,以工程要求为设计边界,获得最优声阻抗和声衬结构参数;其次,在真实流道形状下,对所设计声衬在目标声源和其他频带声源的消声量进行评估。结果表明:所设计的两段风扇机匣声衬在目标声源插入损失和低阶叶片通过频率(blade passing frequency,BPF)其他声源处的消声量可观,达到声衬降噪的目的。In order to investigate the noise reduction effects of fan case acoustic liner of the high bypass ratio turbofan engine,the fan case acoustic liner design process were established based on Wiener-Hopf duct sound propagation method and perforate liner impedance model,researches were done for the purpose of fan case acoustic liner designing of a certain turbofan engine,including the acoustic liner near the leading edge of fan blade,and the acoustic liner between fan blade and outlet guide vane(OGV).Firstly,two acoustic modes were selected as the target source for acoustic liner designing,considering engineering design demand,the optimized impedance and acoustic liner structure parameter were calculated.Then the reduction loss of real duct was calculated.The results show that the designed two-stage fan casing sound lining has a considerable amount of noise elimination at the insertion loss of target sound source and other sound sources of low-order blade passing frequency(BPF),so as to achieve the purpose of noise reduction.

关 键 词：大涵道比涡扇发动机 风扇机匣 声衬设计 WIENER-HOPF 管道声传播 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]