Acoustic and Vibration Response of Flow-Excited Panels: Laboratory Reproduction and Panel Configuration Studies

流激励面板的声学和振动响应：实验室复制和面板配置研究

• 批准号: 435866-2013
• 负责人: Rocha, Joana
• 金额: $ 1.82万
• 依托单位: Carleton University
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2017
• 资助国家: 加拿大
• 起止时间: 2017-01-01 至 2018-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=638611
• 关键词: Acoustic; Vibration; Response; Flow; Excited

The external turbulent boundary layer (TBL), always present around the fuselage of an aircraft during flight, is typically the major source of jet aircraft cabin noise in cruise flight. During long exposure periods, high noise levels produce hearing loss, fatigue, loss of concentration, and can influence the respiratory rate, heart functions and central nervous system. Most aircraft manufacturers are interested in a better understanding of the physics associated with aircraft acoustics. In spite of the growing interest, there is still a lack of understanding of the mechanisms involved in TBL-induced noise in aircraft. Furthermore, in-flight measurements of aircraft noise are extremely costly and time-consuming, and therefore, the laboratory reproduction of in-flight conditions has attracted more attention in recent years. In this context, the present research proposal aims to advance the current state-of-the-art in the understanding of the physics associated with TBL-induced noise, and the laboratory reproduction of the acoustic and vibration response of TBL-excited aircraft panels. Piezoelectric (PZT) actuators, strategically embedded in the test panel, will be used to excite the structure, to reproduce the panel response to the TBL. Different panel configurations will be tested and analyzed, to investigate the best configuration for the noise reduction goal. The proposed research will create an experimental platform that enables the development of a solid methodology for the laboratory reproduction of the acoustic and vibration response of TBL-excited panels. The availability of experimental data will allow the validation of computational approaches for the prediction of noise and vibration of TBL-excited structures. The successful outcome of this research will bring extremely valuable knowledge involving the development of innovative technology, which can be applied to the aircraft industry, in Canada and internationally. The availability of this technology will bring an economic advantage to aircraft industry. In addition, a better understanding in both experimental and computational analysis of TBL-excited structures would benefit numerous other areas, such as, fluid flow in pipes, engine nacelle design, and the automotive industry.

外部湍流边界层（TBL），总是存在于飞行期间的飞机机身周围，通常是巡航飞行中的喷气式飞机机舱噪声的主要来源。在长时间暴露期间，高噪声水平会导致听力损失、疲劳、注意力不集中，并会影响呼吸频率、心脏功能和中枢神经系统。大多数飞机制造商有兴趣更好地了解与飞机声学相关的物理学。尽管人们的兴趣越来越大，但对TBL引起的飞机噪声的机理仍然缺乏了解。此外，飞机噪声的飞行中测量是极其昂贵和耗时的，因此，近年来，飞行中条件的实验室再现引起了更多的关注。在这种情况下，本研究建议的目的是推进目前的国家的最先进的理解与TBL引起的噪声的物理，和实验室再现的TBL激励的飞机面板的声学和振动响应。压电（PZT）致动器，战略性地嵌入在测试面板中，将用于激励结构，以再现面板对TBL的响应。将测试和分析不同的面板配置，以研究实现降噪目标的最佳配置。拟议的研究将创建一个实验平台，使一个坚实的方法，为实验室再现的TBL激励面板的声学和振动响应的发展。实验数据的可用性将允许TBL激励结构的噪声和振动预测的计算方法的验证。这项研究的成功成果将带来涉及创新技术开发的极其宝贵的知识，这些知识可以应用于加拿大和国际上的飞机工业。该技术的应用将为航空工业带来经济优势。此外，更好地理解TBL激励结构的实验和计算分析将有利于许多其他领域，如管道中的流体流动，发动机短舱设计和汽车工业。