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Airfoil design for large horizontal axis wind turbines in low wind speed regions

机译:低风速地区大型水平轴风力发电机的翼型设计

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Low wind speed technology helps to reduce the cost of energy, but also creates huge challenge on the wind turbine blade design. To essentially address the particular blade requirements in low wind speed regions with high inflow turbulence, this study extends previous airfoil design optimization methods. Firstly, special design criteria were proposed besides traditional considerations, concerning efficiency, loads, noise and in particular the high inflow turbulence effects on the enlarged blades. Then through improved mathematic models and modified auto optimization platform, an extended airfoil design optimization framework dedicated to low wind speed sites was established. The case design results show that key features of the new airfoil tailed to low wind speed sites are effectively enhanced: the design lift coefficient and lift-to-drag ratio are fairly increased, and the maximum lift coefficient is well constrained. In addition, the acoustic parameter of the new airfoil is successfully reduced. More important is that the airfoil performance sensitivity to surface roughness and inflow turbulence intensity are evidently eliminated. These finally contribute to an improved overall performance. The rotor blade performance evaluation with the new design airfoil in further verified the case design. Results indicate the proposed framework is able to design special airfoils suited for site-specific blade requirements, contributed by the customized considerations, parameterization model, robust calculation method and global algorithms. (c) 2019 Elsevier Ltd. All rights reserved.
机译:低风速技术有助于降低能源成本,但也给风力涡轮机叶片设计带来了巨大挑战。为了从根本上解决具有高流入湍流的低风速区域中的特殊叶片需求,本研究扩展了以前的机翼设计优化方法。首先,除了传统考虑因素外,还提出了特殊的设计标准,涉及效率,负载,噪声,尤其是对加大叶片的高湍流影响。然后,通过改进的数学模型和改进的自动优化平台,建立了专门针对低风速站点的扩展翼型设计优化框架。案例设计结果表明,新型机翼尾风偏低的关键特征得到了有效增强:设计升力系数和升阻比得到了相当大的提高,最大升力系数得到了很好的约束。此外,新机翼的声学参数已成功降低。更重要的是,明显消除了机翼性能对表面粗糙度和入流湍流强度的敏感性。这些最终有助于提高整体性能。带有新设计翼型的转子叶片性能评估进一步验证了机壳设计。结果表明,通过定制的考虑因素,参数化模型,鲁棒的计算方法和全局算法,提出的框架能够设计出适合特定位置叶片需求的特殊机翼。 (c)2019爱思唯尔有限公司。保留所有权利。

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