CAMBRIDGE UGTP WHOLE ENGINE COMPUTATIONAL AEROACOUSTICS CONSORTIUM

剑桥 UGTP 整机计算气动声学联盟

• 批准号: EP/G027633/1
• 负责人: Paul G. Tucker
• 金额: $ 11.5万
• 依托单位: University of Cambridge
• 依托单位国家: 英国
• 项目类别: Research Grant
• 财政年份: 2009
• 资助国家: 英国
• 起止时间: 2009 至 无数据
• 项目状态: 已结题
• 来源: https://gtr.ukri.org/projects?ref=EP%2FG027633%2F1
• 关键词: CAMBRIDGE; UGTP; WHOLE; ENGINE; COMPUTATIONAL

With the projected demand for air transport set to double the world aircraft fleet by 2020 it is becoming urgent to take steps to reduce the environmental impact of take off noise from aircraft. In worst case noise can be more than just annoying, potentially being a contributory factor towards illnesses such as hypertension. Hence, the Advisory Council for Aeronautics Research in Europe (ACRE) has set the target of reducing perceived noise levels by 50% by the 2020. A key noise source is caused by the powerfully turbulent flow field generated at the high Reynolds numbers associated with aerospace flows. Hence, the acoustician must be able to accurately predict the turbulent flow field, and its interaction, where necessary with combustion, and then manipulate it to reduce the acoustic signature. The only means of reliably predicting turbulence is through direct or near direct simulation of the Navier-Stokes equations. This, at realistic Reynolds numbers needs massive computational resources. Hence, access to the HECToR resource is sought to study various aeroengine flows/systems to produce noise reductions. The areas considered include the engine inlet rotor/fan zones, the combustor, turbine and exhaust.

预计到2020年，世界航空运输需求将增加一倍，因此迫切需要采取措施减少飞机起飞噪音对环境的影响。在最坏的情况下，噪音可能不仅仅是令人讨厌的，可能是导致高血压等疾病的一个因素。因此，欧洲航空研究咨询理事会（ACRE）制定了到2020年将感知噪音水平降低50%的目标。一个关键的噪声源是由与航空航天流相关的高雷诺数下产生的强大湍流场引起的。因此，声学家必须能够准确地预测湍流场及其相互作用，必要时与燃烧，然后操纵它以减少声学特征。唯一可靠地预测湍流的方法是通过直接或接近直接的Navier-Stokes方程模拟。这在现实的雷诺数需要大量的计算资源。因此，寻求获得HECToR资源来研究各种航空发动机流/系统以产生降噪。所考虑的区域包括发动机进气道转子/风扇区、燃烧室、涡轮机和排气。

项目成果

Numerical Investigation of Installation Effects in Open Jet Wind Tunnel Airfoil Experiments

开式射流风洞翼型试验安装效果数值研究

• DOI: 10.2514/6.2014-1118
• 发表时间: 2014
• 作者: Sheikh-AlShabab A

An assessment of far-field noise prediction for subsonic jets using large eddy simulation and Ffowcs Williams-Hawkings method

使用大涡模拟和 Ffowcs Williams-Hawkings 方法评估亚音速喷气机的远场噪声预测

• 发表时间: 2014
• 作者: Naqavi I. Z.

Reduced-order Jet Noise Modelling for Chevrons

V 形的降阶射流噪声建模

• DOI: 10.2514/6.2012-2083
• 发表时间: 2012
• 作者: Depuru Mohan N

Modelling Velocity Correlations with LES and RANS for Prediction of Noise from Isothermal or Hot Jets

使用 LES 和 RANS 对速度相关性进行建模，以预测等温或热射流的噪声

• DOI: 10.2514/6.2016-2810
• 发表时间: 2016
• 作者: Rosa V

Large-Eddy Simulation of Complex Geometry Jets

复杂几何射流的大涡模拟

• DOI: 10.2514/1.b34322
• 发表时间: 2012
• 期刊: Journal of Propulsion and Power
• 影响因子: 1.9
• 作者: Eastwood S