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风力涡轮机叶片在挥舞方向的全尺寸疲劳测试以及裂纹扩展对叶片性能影响的研究

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

作者信息

Al-Khudairi Othman, Hadavinia Homayoun, Little Christian, Gillmore Gavin, Greaves Peter, Dyer Kirsten

机构信息

School of Engineering, Kingston University, London SW15 3DW, UK.

Offshore Renewable Energy Catapult (ORE), Blyth NE24 1LZ, UK.

出版信息

Materials (Basel). 2017 Oct 3;10(10):1152. doi: 10.3390/ma10101152.

DOI:10.3390/ma10101152
PMID:28972548
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC5666958/
Abstract

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.

摘要

本文研究了风力涡轮机叶片结构完整性对腹板与翼梁帽脱粘的敏感性。在此方面，对一个45.7米长的叶片在三种状态下进行了模态分析、静态和疲劳测试：（i）初始叶片；（ii）在腹板和翼梁帽之间引入200毫米裂纹时；（iii）当裂纹扩展到1000毫米时。对叶片的所有三种状态进行了校准拉伸试验，以根据叶片在其使用寿命中预计承受的估计目标弯矩（BM）获得叶片的应变-弯矩关系。所得数据用于在疲劳试验中施加适当的载荷。通过对叶片的所有三种状态进行模态测试，找到了在一系列频域内叶片在挥舞方向和摆振方向的固有频率。每种状态下叶片的第一阶固有频率用于挥舞方向的疲劳试验。这些试验按照技术规范IEC TS 61400-23进行。疲劳试验结果表明，对于距叶片根部9米处腹板与翼梁帽之间200毫米的裂纹，在目标BM的50%下，裂纹在62110次循环内未扩展。然而，当载荷增加到目标BM的70%时，在叶片的压力侧检测到了一些损伤。当200毫米的裂纹扩展到1000毫米时，当施加的载荷超过目标BM的100%时，裂纹开始扩展，并且叶片出现了分层、粘结失效、压缩失效和夹心层芯材失效。

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