首页> 外文会议>ASME Turbo Expo: Turbomachinery Technical Conference and Exposition >EXPERIMENTAL INVESTIGATION OF THE PERFORMANCE OF H-DARRIEUS WIND TURBINES WITH TUBERCLE LEADING EDGE BLADES
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EXPERIMENTAL INVESTIGATION OF THE PERFORMANCE OF H-DARRIEUS WIND TURBINES WITH TUBERCLE LEADING EDGE BLADES

机译:H-Darrius风力涡轮机与结节前缘叶片性能的实验研究

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The most significant challenge associated with employing small-scale H-Darrieus wind turbines is to ensure that they self-start without compromising their efficiency at the design operating condition. One of the key and straightforward methods to improve the turbine performance is to choose an optimized blade profile. It has been shown that by creating rounded protuberances (tubercles) around the blade leading edge, not only do the blades demonstrate a more gradual stall characteristic but also that the tubercles significantly increase the blade lift performance in the post-stall regime at the expense of slightly degraded lift performance in the pre-stall regime. This effect might be beneficial for the H-Darrieus turbine application where the blades experience extreme incidence range during the turbine start-up period. Therefore, in this study the performance of standard NACA0021 blades is compared experimentally to a modified set of blades which have a sinusoidal tubercle configuration along the original NACA0021 blade leading edge (0≤x≤0.3c). Time-accurate, self-starting data were recorded from wind tunnel tests under different flow conditions and the power coefficient (C_p) versus tip speed ratio (λ) curve was calculated. It is demonstrated conclusively that blades with an appropriate configuration of tubercle leading edges can considerably improve turbine self-starting capability. To the best of the authors' knowledge, this study provides the first experimental data of H-Darrieus wind turbine performance with tubercle leading edge blades and the data are valuable for future designs and for the validation of simulation models.
机译:与采用小型H-Darrieus风力涡轮机相关的最重要的挑战是确保他们在不影响其在设计操作条件下效率的情况下自动启动。改善涡轮机性能的关键和直接方法之一是选择优化的刀片轮廓。它已经表明,通过创建圆润突起(瘤)围绕叶片前缘,不仅做到了叶片表现出更渐进的失速特性,而且还可以为结节显著增加在后失速政权铲提升性能为代价的在术前制度中略微降低提升性能。这种效果可能对H-Darrius涡轮机应用有益,其中叶片在涡轮机启动期间经历极端入射。因此,在本研究中标准NACA0021叶片的性能是通过实验的组修改的含有沿原NACA0021正弦结节构型叶片的相比叶片前缘(0≤x≤0.3c)。时间精确,自启动数据从不同的流动条件和与叶尖速比的功率系数(C_P)下风洞测试记录(λ)曲线计算。最终证明,具有适当配置结节前缘的叶片可以显着提高涡轮机自动启动能力。据作者所知,本研究提供了H-Darrius风力涡轮机性能的第一个实验数据,带有结节前沿刀片,数据对于未来的设计和仿真模型的验证是有价值的。

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