Prediction of Delamination in Wind Turbine Blade Structural Details

[+] Author and Article Information
John F. Mandell, Douglas S. Cairns, Daniel D. Samborsky, Robert B. Morehead, Darrin J. Haugen

Montana State University, Bozeman, MT 59717

J. Sol. Energy Eng 125(4), 522-530 (Nov 26, 2003) (9 pages) doi:10.1115/1.1624613 History: Received February 15, 2003; Revised June 30, 2003; Online November 26, 2003
Copyright © 2003 by ASME
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Common structural elements which generate interlaminar stress concentrations 1
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The three modes of cracking, Mode I (opening), Mode II (sliding) and Mode III (tearing) 4
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Mode I DCB geometry and loading (ASTM D5528)
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Mode II ENF geometry and loading
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Typical load versus actuator displacement for an ENF specimen
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Sketches of actual observations of crack growth in a (90/45 deg) interface under (a) static DCB testing, (b) fatigue DCB testing, (c) static ENF testing and (d) fatigue ENF testing 3
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R-curve data for (+45/+45) and (90/45) interfaces, calculated with Eq. (1)
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Mode I—(da/dN) versus GI max⋅[(±45)9/90/(±45)8] laminates cracked in the (90/45) interface. Short crack data (less than 5 mm), R=0.1, DCB Specimens.
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Mode II—(da/dN) versus GII max⋅[(±45)9/90/(±45)8] laminates cracked in the (90/45) interface, R=0.1, ENF Specimens
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Standard (thin flange) skin-stiffener loading, geometry and dimensions
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Typical skin-stiffener fatigue test
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Typical static tensile load versus displacement curve for a skin-stiffener specimen
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Location of delamination and nomenclature for crack fronts under static loading (crack is in the 0/45 deg interface)
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Skin-stiffener crack sequence during fatigue loading
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FEA tangential strain plot with crack front locations
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Photograph of flange tip delamination for thick-flanged, thin-skin stiffener specimens
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Fatigue crack growth rate versus Gmax in the 0/45 deg interface of ortho-polyester skin-stiffeners
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Comparison of different matrix materials in fatigue life S-N data for skin-stiffeners. (Maximum cyclic load versus number of cycles to reach a deflection of 0.43 cm).




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