Trailing Edge Serration & Leading Edge Undulation Aero-acoustic Noise Reduction Mechanisms Through 3-Dimensional Flow Structure Analysis

后缘锯齿

• 批准号: 1818453
• 金额: --
• 依托单位: Brunel University London
• 依托单位国家: 英国
• 项目类别: Studentship
• 财政年份: 2016
• 资助国家: 英国
• 起止时间: 2016 至 无数据
• 项目状态: 已结题
• 来源: https://gtr.ukri.org/projects?ref=studentship-1818453
• 关键词: Trailing; Edge; Serration; Leading; Undulation

The research will focus on three main stages. Stage 1 (approximately 10 months) will focus on the optimisation of aeroacoustic and aerodynamic performances of curved leading edge serrations that were inspired by those found on owl's wing (see Fig. 2). This new concept, which has never been attempted elsewhere before, was initiated in my final year Bachelor's project and the results so far have demonstrated that the serrations can in fact be carefully optimised to achieve simultaneous and significant improvements in aerofoil leading edge noise reductions (Fig. 3) and increased performance in lift generation (Fig. 4). Currently we are preparing to apply for a patent, to be supported by the RSDO, for this owl-inspired leading edge serration technology developed in my undergraduate dissertation project. My PhD proposal is to undertake more in-depth research to determine the fundamental mechanisms and seek to develop control strategies based on the same physical principles on the leading edge serration.

研究将集中在三个主要阶段。第一阶段（大约 10 个月）将重点关注弯曲前缘锯齿的气动声学和空气动力学性能的优化，这些锯齿的灵感来自于猫头鹰翅膀上的锯齿（见图 2）。这个新概念以前从未在其他地方尝试过，是在我最后一年的学士项目中启动的，迄今为止的结果表明，锯齿实际上可以经过仔细优化，以同时实现机翼前缘噪声降低（图 3）和升力产生性能提高（图 4）的显着改进。目前，我们正在准备为我的本科论文项目中开发的这种受猫头鹰启发的前沿锯齿技术申请专利，并得到 RSDO 的支持。我的博士建议是进行更深入的研究，以确定基本机制，并寻求基于与前缘锯齿相同的物理原理开发控制策略。

项目成果

On the spatial-temporal development of synthetic turbulent boundary layer on a serrated trailing edge

锯齿状后缘合成湍流边界层的时空发展

• DOI: 10.2514/6.2019-2457
• 发表时间: 2019
• 作者: Juknevicius A

On the leading edge noise and aerodynamics of thin aerofoil subjected to the straight and curved serrations

• DOI: 10.1016/j.jsv.2018.02.038
• 发表时间: 2018-07
• 期刊: Journal of Sound and Vibration
• 影响因子: 4.7
• 作者: A. Juknevicius;T. Chong

Leading Edge Noise Reduction of Thin Aerofoil by the Straight and Curved Serrations of the Add-on Type

利用附加型直锯齿和弯锯齿降低薄翼型前缘噪声

• DOI: 10.2514/6.2017-3491
• 发表时间: 2017
• 作者: Juknevicius A

The Formation of the Aeroacoustics Feedback Loop for a Laminar Aerofoil

层流翼型气动声学反馈回路的形成

• DOI: 10.2514/6.2021-2261
• 发表时间: 2021
• 作者: Juknevicius A

Reconstruction of the deterministic turbulent boundary layer for the study of aerofoil self-noise mechanisms

重建确定性湍流边界层以研究机翼自噪声机制

• DOI: 10.1007/s00348-022-03486-7
• 发表时间: 2022
• 期刊: Experiments in Fluids
• 影响因子: 2.4
• 作者: Chong T