CAJ | 학술논문

随着商用航空发动机涵道比的增大，风扇噪声已是目前飞机最主要的噪声源之一。通过在进气道内壁安装声学声衬，可以有效降低风扇前传声。针对某型飞机发动机进气道，利用管道模态方法对该进气道不同声衬拼缝宽度和不同声衬拼缝数量进行降噪量计算和分析。计算结果表明，在拼缝数量不变的情况下，随着拼缝宽度的增大，进气道对一阶风扇通过频率噪声的降噪效果逐步下降。在拼缝总宽度不变的情况下，拼缝数目越多，单个拼缝宽度越小，则进气道降噪效果越好。
수착상용항공발동궤함도비적증대，풍선조성이시목전비궤최주요적조성원지일。통과재진기도내벽안장성학성츤，가이유효강저풍선전전성。침대모형비궤발동궤진기도，이용관도모태방법대해진기도불동성츤병봉관도화불동성츤병봉수량진행강조량계산화분석。계산결과표명，재병봉수량불변적정황하，수착병봉관도적증대，진기도대일계풍선통과빈솔조성적강조효과축보하강。재병봉총관도불변적정황하，병봉수목월다，단개병봉관도월소，칙진기도강조효과월호。
With the increase of commercial aircraft engine bypass ratio, fan noise becomes one of the main noise sources in aircraft. Acoustic liner installed at the inner wall can reduce forward fan noise effectively. Directed at one aircraft engine inlet, duct mode method is utilized to calculate noise reduction with different acoustic liner widths and different acoustic liner splices. The results show that inlet noise reduction capability to first order blade pass frequency decreases with splice quantity unchanged and width increase. Under the condition of total splice width unchanged, noise reduction capability increases with more splices and single splice width decreases.