孔隙率对风电叶片用大厚度复合材料结构弯曲刚度影响研究

doi:10.19936/j.cnki.2096-8000.20260728.017

复合材料科学与工程 ›› 2026, Vol. 0 ›› Issue (7): 141-149.DOI: 10.19936/j.cnki.2096-8000.20260728.017

孔隙率对风电叶片用大厚度复合材料结构弯曲刚度影响研究

胡聪丽¹, 王晓菁¹, 丁安心^2*

1.上海艾港风电科技发展有限公司,上海 201306;
2.武汉理工大学材料科学与工程学院,武汉 430070

收稿日期:2026-02-10 出版日期:2026-07-28 发布日期:2026-08-06
通讯作者: 丁安心(1987—),男,博士,教授,硕士生/博士生导师,研究方向为复合材料制备与设计,axding@whut.edu.cn。
作者简介:胡聪丽(1981—),女,硕士,主要从事大型风电叶片复合材料的开发和测试。

Study on the effect of porosity on flexural performance of thick composite structures for wind turbine blades

HU Congli¹, WANG Xiaojing¹, DING Anxin^2*

1. Shanghai Aigang Wind Energy Technology Development Co., Ltd., Shanghai 201306, China;
2. School of Materials Science and Engineering, Wuhan University of Technology, Wuhan 430070, China

Received:2026-02-10 Online:2026-07-28 Published:2026-08-06

摘要/Abstract

摘要： 研究了孔隙率对风电用大厚度复合材料结构弯曲刚度的影响,通过真空导入工艺制备了孔隙率为0.64%、2.04%和5.42%的大厚度复合材料层合板,按照ISO 14125标准制备四点弯曲试样,开展100万次弯曲疲劳循环试验。基于应变法和挠度法,分别计算了疲劳试验前及循环20万、60万、80万、100万次后试样的弯曲模量。试验结果表明:对于高孔隙率(5.42%)试样,两种测试方法计算的模量差异显著,应变法计算的模量值偏高61%,这源于应变片仅能捕捉表层应变,无法反映含层间分层等内部缺陷结构的整体承载能力;孔隙率对结构弯曲模量的衰减具有显著影响,低孔隙率(0.64%)试样经100万次疲劳循环后模量下降3.7%,从52.18 GPa 衰减到50.27 GPa,而高孔隙率(5.42%)试样在20万次疲劳循环后模量下降38.4%,从50.65 GPa 衰减到31.21 GPa,并在100万次疲劳循环后进一步降至28.90 GPa。最后,基于试验数据建立了考虑孔隙率的弯曲模量衰减模型。该模型可为大厚度复合材料壳单元在弯曲载荷下的力学仿真分析提供数据支持。

关键词: 大厚度层合板, 疲劳循环, 孔隙率, 弯曲刚度

Abstract: The study investigated the effect of porosity on the flexural stiffness of thick composites used in wind turbines. Thick composite laminate test panels with porosities of 0.64%, 2.04%, and 5.42% were fabricated using vacuum infusion molding. Four-point bending specimens were prepared according to ISO 14125 standard, and cyclic bending fatigue tests up to 1 000 000 cycles were conducted. The flexural modulus of the specimens before fatigue testing and after 200 000,600 000, 800 000, and 1 000 000 cycles was calculated using strain gauge and deflection methods, respectively. Experimental results revealed that for high-porosity (5.42%) specimens, a significant discrepancy (61% higher modulus via strain method) existed between the two measurement approaches. This discrepancy arises because strain gauges only capture surface strain and fail to reflect the global load-bearing capacity of structures with internal defects such as interlaminar delamination. Porosity significantly influenced the degradation of flexural modulus in thick structures after fatigue. Low-porosity (0.64%) specimens exhibited a mere 3.7% modulus reduction from 52.18 GPa to 50.27 GPa after 1 000 000 cycles, whereas high-porosity (5.42%) specimens experienced a 38.4% modulus drop from 50.65 GPa to 31.21 GPa after 200 000 cycles, further declining to 28.90 GPa after 1 00 0 000 cycles. Finally, a porosity-dependent flexural modulus degradation model was established based on experimental data, providing critical support for mechanical simulation of thick composite shell structures under bending loads.

Key words: thick composite, fatigue cycles, porosity, flexural stiffness

中图分类号:

TB332

胡聪丽, 王晓菁, 丁安心. 孔隙率对风电叶片用大厚度复合材料结构弯曲刚度影响研究[J]. 复合材料科学与工程, 2026, 0(7): 141-149.

HU Congli, WANG Xiaojing, DING Anxin. Study on the effect of porosity on flexural performance of thick composite structures for wind turbine blades[J]. COMPOSITES SCIENCE AND ENGINEERING, 2026, 0(7): 141-149.

参考文献

[1] Mishnaevsky L, Branner K, Petersen H, et al. Materials for wind turbine blades: an overview[J]. Materials, 2017, 10(11): 1285.
[2] 王宝萱, 董敏, 梁旭, 等. 海上风电叶片结构设计中的前沿问题与挑战[J]. 船舶工程, 2023, 45(11): 18-24, 53.
Wang Baoxuan, Dong Min, Liang Xu, et al. Frontier issues and challenges in the structural design of offshore wind turbine blades[J]. Ship Engineering, 2023, 45(11): 18-24, 53.
[3] 肖远航, 陆承志, 王国军, 等. 风电叶片用碳/玻层内混杂VARI成型复合材料结构与性能研究[J]. 高科技纤维与应用, 2022, 47(6): 61-66.
Xiao Yuanhang, Lu Chengzhi, Wang Guojun, et al. Study on structure and properties of carbon/glass intralayer hybrid VARI composites for wind power blades[J]. Hi-Tech Fiber & Application, 2022, 47(6): 61-66.
[4] Feddal I, Khamlichi A. Delamination buckling of a laminated composite shell panel using cohesive zone modelling[J]. InternationalReview of Applied Sciences and Engineering, 2022, 13(2): 228-238.
[5] 杨斌, 王继辉, 赵明明, 等. 风电叶片拉挤梁帽真空灌注成型工艺数值优化[J]. 太阳能学报, 2023, 44(7): 380-385.
Yang Bin, Wang Jihui, Zhao Mingming, et al. Numerical optimization of vacuum infusion process for pultruded spar cap of wind turbine blade[J]. Acta Energiae Solaris Sinica, 2023, 44(7): 380-
385.
[6] Chambers A R, Earl J S, Squires C A, et al. The effect of voids on the flexural fatigue performance of unidirectional carbon fibre composites developed for wind turbine applications[J]. International Journal of Fatigue, 2006, 28(10): 1389-1398.
[7] Bennati S, Fisicaro P, Taglialegne L, et al. An elastic interface model for the delamination of bending-extension coupled laminates[J]. Applied Sciences, 2019, 9(17): 3560.
[8] 李向前, 孔维夷, 张婷, 等. 铺层复合材料中孔隙与褶皱缺陷对性能的影响[J]. 纤维复合材料, 2019, 36(4): 27-32.
Li Xiangqian, Kong Weiyi, Zhang Ting, et al. Effect of porosity and wrinkle defects on properties of laminated composites[J]. Fiber Composites, 2019, 36(4): 27-32.
[9] Kinawy M, Butler R, Hunt G W. Buckling and postbuckling of a delaminated composite beam in bending[J]. AIAA Journal, 2011, 49(3): 670-672.
[10] Kinawy M, Butler R, Hunt G W. Bending strength of delaminated aerospace composites[J]. Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences, 2012, 370(1965): 1780-1797.
[11] 刘志文, 苗涛, 周康康, 等. 风力机叶片主梁分层损伤扩展研究[J]. 电气技术, 2025, 26(10): 23-31, 54.
Liu Zhiwen, Miao Tao, Zhou Kangkang, et al. Study on the extension of delamination damage in the main beam of wind turbine blades[J]. Electrical Engineering, 2025, 26(10): 23-31, 54.
[12] Xia Fei, Wang Zikun, Wang Yi.Post-bucking response ofcarbon/epoxy laminates with delamination under quasi-static compression: experiments and numerical simulations[J]. Materials, 2024, 17(20): 5047.
[13] Salpekar S A, O’Brien T K. Combined effect of matrix cracking and free edge on delamination[M]//O’Brien T K.Composite Materials: Fatigue and Fracture: Third Volume.West Conshohocken, PA: ASTM International, 1991: 287-311.
[14] Xin Wen, Li Hui, Lu Xiaolong, et al. Study on the effect of initial delamination on tensile behavior of offshore wind turbine blade spar cap[J]. Energies, 2023, 16(8): 3607.
[15] Wang Qiang, Chen Qiuyu, Chen Yujie, et al. The effect of internal delamination damage on the tensile strength of aeronautical composites[J]. Acta Mechanica Solida Sinica, 2022, 35(6): 979-986.
[16] Shen Rulin, Liu Taizhi, Liu Hehua, et al. An enhanced vacuum-assisted resin transfer molding process and its pressure effect on resin infusion behavior and composite material performance[J]. Polymers, 2024, 16(10): 1386.

孔隙率对风电叶片用大厚度复合材料结构弯曲刚度影响研究

Study on the effect of porosity on flexural performance of thick composite structures for wind turbine blades

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