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Full-Scale Fatigue Testing of a Wind Turbine Blade in Flapwise Direction and Examining the Effect of Crack Propagation on the Blade Performance

机译:风力涡轮机叶片沿翼展方向的全尺寸疲劳测试并研究裂纹扩展对叶片性能的影响

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摘要

In this paper, the sensitivity of the structural integrity of wind turbine blades to debonding of the shear web from the spar cap was investigated. In this regard, modal analysis, static and fatigue testing were performed on a 45.7 m blade for three states of the blade: (i) as received blade (ii) when a crack of 200 mm was introduced between the web and the spar cap and (iii) when the crack was extended to 1000 mm. Calibration pull-tests for all three states of the blade were performed to obtain the strain-bending moment relationship of the blade according to the estimated target bending moment (BM) which the blade is expected to experience in its service life. The resultant data was used to apply appropriate load in the fatigue tests. The blade natural frequencies in flapwise and edgewise directions over a range of frequency domain were found by modal testing for all three states of the blade. The blade first natural frequency for each state was used for the flapwise fatigue tests. These were performed in accordance with technical specification IEC TS 61400-23. The fatigue results showed that, for a 200 mm crack between the web and spar cap at 9 m from the blade root, the crack did not propagate at 50% of the target BM up to 62,110 cycles. However, when the load was increased to 70% of target BM, some damages were detected on the pressure side of the blade. When the 200 mm crack was extended to 1000 mm, the crack began to propagate when the applied load exceeded 100% of target BM and the blade experienced delaminations, adhesive joint failure, compression failure and sandwich core failure.
机译:在本文中,研究了风力涡轮机叶片的结构完整性对抗剪腹板从翼梁盖剥离的敏感性。在这方面,在45.7 m的叶片上针对叶片的三种状态进行了模态分析,静态和疲劳测试:(i)作为接收叶片(ii)在腹板和翼梁板之间引入200 mm的裂缝时,以及(iii)当裂纹扩展到1000毫米时。对叶片的所有三种状态进行校准拉力测试,以根据叶片在其使用寿命中所经历的估计目标弯曲力矩(BM)来获得叶片的应变弯矩关系。所得数据用于在疲劳测试中施加适当的载荷。通过对叶片的所有三个状态进行模态测试,发现了在一定频域范围内沿叶片方向和边缘方向的叶片固有频率。每种状态下的叶片第一固有频率用于襟翼疲劳测试。这些是根据技术规范IEC TS 61400-23执行的。疲劳结果表明,对于距叶片根部9 m处的腹板和梁帽之间的200 mm裂纹,直至62,110个循环,裂纹在目标BM的50%处均不会扩展。但是,当负载增加到目标BM的70%时,在叶片压力侧会发现一些损坏。当200 mm的裂纹扩展到1000 mm时,当施加的载荷超过目标BM的100%时,裂纹开始扩展,并且叶片发生分层,粘合接头失效,压缩失效和夹芯失效。

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