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Reduction of aerofoil self-noise by surface plasma technique

通过表面等离子体技术降低翼型自身噪声

基本信息

批准号：
EP/K002309/1
负责人：
Tze Chong
金额：
$ 12.47万
依托单位：
Brunel University London
依托单位国家：
英国
项目类别：
Research Grant
财政年份：
2013
资助国家：
英国
起止时间：
2013 至无数据
项目状态：
已结题

来源：
https://gtr.ukri.org/projects?ref=EP%2FK002309%2F1
关键词：
Reduction aerofoil self noise surface

项目摘要

In the aerospace industry, great emphasis is always placed on the lifting components to achieve high-lift, low-drag and low-noise performances. This proposal concerns an 18-month experimental study into the application of surface plasma actuators as an active boundary layer and wake control technique with the aim of reducing the drag and Trailing Edge self-noise of aerofoil. Two configurations will be investigated: (1) an aerofoil with blunt trailing edge - which characteristically combines a superior lift performance with high drag and significant tone noise radiation; (2) an aerofoil with a sharp trailing edge - which typically produces broadband self-noise in high Reynolds number flow. The main technology under investigation here is the relatively new, though rapidly expanding, surface plasma actuators. The usage of surface plasma actuators for flow control is very attractive for industrial applications because this technique is highly energy efficient, has a fast response, a simple structure, can be used for both steady and unsteady actuations and creates no profile drag when not in operation. The proposed research aims to simultaneously optimise the aerodynamical and aeroacoustical performances of aerofoil with blunt as well as sharp trailing edges. The expected outcome of this research is an extensive validation of the effectiveness of surface plasma actuator as a relatively novel technique for the reduction of drag and noise generated by aircraft components such as the turbofan engine and airframe. The outcome of this research is also transferable to the wind turbine industry and fan-based home appliance sector.

在航天工业中，为了实现高升力、低阻力和低噪声的性能，起重部件一直受到高度重视。这项建议涉及一项为期18个月的实验研究，目的是应用表面等离子体激励器作为主动边界层和尾迹控制技术，以降低翼型的阻力和后缘自噪声。将研究两种配置：(1)具有钝化后缘的翼型--其特征是结合了优越的升力性能与高阻力和显著的音调噪声辐射；(2)具有陡峭后缘的翼型--它通常在高雷诺数流动中产生宽带自噪声。这里正在研究的主要技术是相对较新的、尽管发展迅速的表面等离子体激励器。表面等离子体激励器用于流量控制在工业应用中非常有吸引力，因为这种技术具有高能效、响应快、结构简单、既可用于稳定激励又可用于非稳定激励且在不工作时不会产生轮廓阻力的特点。建议的研究旨在同时优化具有钝化和锐化后缘的翼型的气动和气动声学性能。这项研究的预期结果是对表面等离子体致动器作为一种相对新颖的技术的有效性进行广泛验证，以减少涡扇发动机和机身等飞机部件产生的阻力和噪声。本研究成果也可推广到风电行业和风机家电行业。