摘要
针对发动机进气声衬在声载荷作用下的结构设计选型需求,依次对简化的声衬有限元模型进行静力分析、模态分析和声激励分析,计算出声衬的应力分布,并通过改变声衬结构参数,研究腔深、面板厚度、孔径、蜂窝边长4种结构参数对全尺寸声衬在声激励下响应的影响规律。仿真结果表明,腔深改变引起的声衬总质量每增加1kg,声载应力减小0.484MPa;面板厚度改变引起的声衬总质量每增加1kg,声载应力减小0.105MPa;孔径和蜂窝边长对声衬质量和声载应力的影响很小。在声衬结构选型时,为了使总质量和声载应力尽量小,优先方法是增加声衬腔深,其次是增加面板厚度。
According to the structural design and type selection requirements of the engine intake acoustic liner under the acoustic load,the static analysis,modal analysis and acoustic excitation analysis of the simplified finite element model of the acoustic liner are carried out,and the stress distribution of the acoustic liner is calculated.By changing the structural parameters of acoustic liner,the influence of cavity depth,panel thickness,aperture and honeycomb side length on the response of full-scale acoustic liner under acoustic excitation is studied.The simulation results show that the acoustic stress decreases by 0.484MPa for every 1kg increase of the total mass of the acoustic liner caused by the change of the cavity depth.The acoustic stress decreases by 0.105MPa for every 1kg increase of the total mass of the acoustic liner caused by the change of the panel thickness.The influence of the pore diameter and honeycomb side length on the acoustic lining quality and acoustic stress is very small.In order to make the total mass and acoustic stress as small as possible,the first method is to increase the depth of acoustic liner cavity,and the second is to increase the thickness of panel.
作者
杭超
王晨
薛东文
徐健
Hang Chao;Wang Chen;Xue Dongwen;Xu Jian(AVIC Aircraft Strength Research Institute,Xi’an 710065,China)
出处
《航空科学技术》
2021年第2期44-49,共6页
Aeronautical Science & Technology
关键词
短舱声衬
声激励
模态
结构参数
有限元分析
naclle acoustic liner
acoustic excitation
modal
structural parameters
finite element analysis