涡扇发动机旋转声模态发生与测试试验研究  

Research on Acoustic Spinning Mode Synthesizer and Measurement of Turbofan Engine Method Validating Experiment

作　　者：高翔[1] 薛东文[1] 燕群[1] 黄文超[1] GAO Xiang;XUE Dong-wen;YAN Qun;HUANG Wen-chao(Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所,西安710065

出　　处：《科学技术与工程》2018年第23期128-133,共6页Science Technology and Engineering

基　　金：国家973计划项目(2012CB720200)资助

摘　　要：开展了涡扇发动机旋转声模态发生与测试技术研究。首先,通过对涡扇发动机旋转声模态发生与测试技术的原理分析,得出声模态发生与测试试验装置设计方法;结构设计与电气系统设计相结合,完成了试验装置的搭建;最后经过以某高阶声模态为例进行试验验证工作,证明了声模态发生与测试技术的正确性和试验装置设计的合理性。开展的声模态发生与测试技术研究对消声短舱声衬的声学效果验证试验意义重大,填补了中国该工程领域的空白,具有较好的工程应用价值。The development and measurement of acoustic spinning mode synthesizer were put forward to carry out the aero engine nacelle liner validating experiment.Firstly,the design methods of mode generating and measuring were concluded by principle analyzing on turbofan engine noise formation mechanism.The correctness of acoustic spinning mode synthesizer was proven by inlet nacelle liner validation experiment on a high mode number.The results fills gaps in the field and will provide scientific basis for the Nacelle Liner design,Validating test technology of the nacelle liner.

关 键 词：发动机噪声 短舱声衬 旋转声模态 测试技术 试验验证 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]