Validation of a 20 m Wind Turbine Blade Model

In the projects Smartblades and Smartblades 2 a full-scale 20 m rotor blade for the NREL CART3 wind turbine was designed, built and tested. The rotor blade was intended to have a strong bending–torsion coupling. By means of the experiments, the proof for the technology in question was supposed to be provided. The experimental work was accompanied by simulations. The aim of the paper was to describe and publish a reference finite element model for the 20 m rotor blade. The validation procedure is presented, as are the modelling strategy and the limitations of the model. The finite element model is created using quadratic finite shell elements and quadratic solid elements. Different data sets were used for the validation. First, the data of static test bench experiments were used. The validation comprised the comparison of global displacement and local strain measurements for various flap and edge bending tests and for torsion unit loading tests. Second, the blades’ eigenfrequencies and eigenvectors in clamped and free–free scenarios were used for validation. Third, the mass distributions of the finite element and real blade were investigated. The paper provides the evaluated experimental data, and all analysed scenarios and the corresponding finite element models in Abaqus, Ansys and Nastran and formats as a reference dataset.

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Research on seismic behavior of special-shaped CFST column to H-section steel beam joint

Advances in Structural Engineering ◽

10.1177/13694332211007392 ◽

2021 ◽

pp. 136943322110073

Author(s):

Yu Cheng ◽

Yuanlong Yang ◽

Binyang Li ◽

Jiepeng Liu

Keyword(s):

Finite Element ◽

Finite Element Model ◽

Seismic Behavior ◽

Failure Modes ◽

Joint Stiffness ◽

Load Ratio ◽

Element Model ◽

Steel Tube ◽

Steel Beam ◽

Static Test

To investigate the seismic behavior of joint between special-shaped concrete-filled steel tubular (CFST) column and H-section steel beam, a pseudo-static test was carried out on five specimens with scale ratio of 1:2. The investigated factors include stiffening types of steel tube (multi-cell and tensile bar) and connection types (exterior diaphragm and vertical rib). The failure modes, hysteresis curves, skeleton curves, stress distribution, and joint shear deformation of specimens were analyzed to investigate the seismic behaviors of joints. The test results showed the connections of exterior diaphragm and vertical rib have good seismic behavior and can be identified as rigid joint in the frames with bracing system according to Eurocode 3. The joint of special-shaped column with tensile bars have better seismic performance by using through vertical rib connection. Furthermore, a finite element model was established and a parametric analysis with the finite element model was conducted to investigate the influences of following parameters on the joint stiffness: width-to-thickness ratio of column steel tube, beam-to-column linear stiffness ratio, vertical rib dimensions, and axial load ratio of column. Lastly, preliminary design suggestions were proposed.

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Finite Element Modeling of Unidirectional Non-Crimp Fabric for Manufacturing of Composites with Embedded Cabling

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.554-557.484 ◽

2013 ◽

Vol 554-557 ◽

pp. 484-491 ◽

Cited By ~ 3

Author(s):

Alexander S. Petrov ◽

James A. Sherwood ◽

Konstantine A. Fetfatsidis ◽

Cynthia J. Mitchell

Keyword(s):

Finite Element ◽

Finite Element Model ◽

Element Model ◽

Explicit Finite Element ◽

Shell Elements ◽

Beam Elements ◽

Hybrid Finite Element ◽

International Benchmarking ◽

Unidirectional Glass ◽

Forming Simulations

A hybrid finite element discrete mesoscopic approach is used to model the forming of composite parts using a unidirectional glass prepreg non-crimp fabric (NCF). The tensile behavior of the fabric is represented using 1-D beam elements, and the shearing behavior is captured using 2-D shell elements into an ABAQUS/Explicit finite element model via a user-defined material subroutine. The forming of a hemisphere is simulated using a finite element model of the fabric, and the results are compared to a thermostamped part as a demonstration of the capabilities of the used methodology. Forming simulations using a double-dome geometry, which has been used in an international benchmarking program, were then performed with the validated finite element model to explore the ability of the unidirectional fabric to accommodate the presence of interlaminate cabling.

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ACTIVE TWIST OF MODEL ROTOR BLADES WITH D-SPAR DESIGN

Transport ◽

10.3846/16484142.2007.9638094 ◽

2007 ◽

Vol 22 (1) ◽

pp. 38-44 ◽

Cited By ~ 10

Author(s):

Andrejs Kovalovs ◽

Evgeny Barkanov ◽

Sergejs Gluhihs

Keyword(s):

Finite Element ◽

Finite Element Model ◽

Rotor Blade ◽

Element Model ◽

Rotor Blades ◽

Helicopter Rotor ◽

3D Finite Element ◽

3D Finite Element Model ◽

Helicopter Rotor Blade ◽

Active Twist

The design methodology based on the planning of experiments and response surface technique has been developed for an optimum placement of Macro Fiber Composite (MFC) actuators in the helicopter rotor blades. The baseline helicopter rotor blade consists of D‐spar made of UD GFRP, skin made of +450/‐450 GFRP, foam core, MFC actuators placement on the skin and balance weight. 3D finite element model of the rotor blade has been built by ANSYS, where the rotor blade skin and spar “moustaches” are modeled by the linear layered structural shell elements SHELL99, and the spar and foam ‐ by 3D 20‐node structural solid elements SOLID 186. The thermal analyses of 3D finite element model have been developed to investigate an active twist of the helicopter rotor blade. Strain analogy between piezoelectric strains and thermally induced strains is used to model piezoelectric effects. The optimisation results have been obtained for design solutions, connected with the application of active materials, and checked by the finite element calculations.

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AEROTAXI ground static test and finite element model validation

INCAS BULLETIN ◽

10.13111/2066-8201.2011.3.2.6 ◽

2011 ◽

Vol 3 (2) ◽

pp. 57-64

Author(s):

LOZICI-BRÎNZEI Dorin ◽

◽

TǍTARU Simion ◽

BÎSCĂ Radu

Keyword(s):

Finite Element ◽

Finite Element Model ◽

Model Validation ◽

Element Model ◽

Static Test

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Dynamic Analysis of Tapered Thin-Walled Beams Using Spectral Finite Element Method

Shock and Vibration ◽

10.1155/2019/2174209 ◽

2019 ◽

Vol 2019 ◽

pp. 1-13 ◽

Cited By ~ 2

Author(s):

Yiping Shen ◽

Zhijun Zhu ◽

Songlai Wang ◽

Gang Wang

Keyword(s):

Finite Element ◽

Finite Element Model ◽

Wind Turbine ◽

Element Model ◽

Rotor Blades ◽

Mode Shapes ◽

Modal Frequency ◽

Thin Walled Structures ◽

Thin Walled ◽

Spectral Finite Element

Tapered thin-walled structures have been widely used in wind turbine and rotor blade. In this paper, a spectral finite element model is developed to investigate tapered thin-walled beam structures, in which torsion related warping effect is included. First, a set of fully coupled governing equations are derived using Hamilton’s principle to account for axial, bending, and torsion motion. Then, the differential transform method (DTM) is applied to obtain the semianalytical solutions in order to formulate the spectral finite element. Finally, numerical simulations are conducted for tapered thin-walled wind turbine rotor blades and validated by the ANSYS. Modal frequency results agree well with the ANSYS predictions, in which approximate 30,000 shell elements were used. In the SFEM, one single spectral finite element is needed to perform such calculations because the interpolation functions are deduced from the exact semianalytical solutions. Coupled axial-bending-torsion mode shapes are obtained as well. In summary, the proposed spectral finite element model is able to accurately and efficiently to perform the modal analysis for tapered thin-walled rotor blades. These modal frequency and mode shape results are important to carry out design and performance evaluation of the tapered thin-walled structures.

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Finite Element Model Updating for Helicopter Rotor Blade Using Genetic Algorithm

AIAA Journal ◽

10.2514/2.1983 ◽

2003 ◽

Vol 41 (3) ◽

pp. 554-556 ◽

Cited By ~ 13

Author(s):

Veerabhadra Rao Akula ◽

Ranjan Ganguli

Keyword(s):

Genetic Algorithm ◽

Finite Element ◽

Finite Element Model ◽

Rotor Blade ◽

Model Updating ◽

Element Model ◽

Helicopter Rotor ◽

Finite Element Model Updating ◽

Helicopter Rotor Blade

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Load application method for shell finite element model of wind turbine blade

Wind Engineering ◽

10.1177/0309524x18759897 ◽

2018 ◽

Vol 42 (5) ◽

pp. 467-482 ◽

Cited By ~ 2

Author(s):

Damien Caous ◽

Nicolas Lavauzelle ◽

Julien Valette ◽

Jean-Christophe Wahl

Keyword(s):

Finite Element ◽

Structural Analysis ◽

Finite Element Model ◽

Wind Turbine ◽

Turbine Blade ◽

Element Model ◽

Wind Turbine Blade ◽

Detailed Structural Analysis ◽

Body Load ◽

Shell Finite Element

It is common to dissociate load computation from structural analysis when carrying out a numerical assessment of a wind turbine blade. Loads are usually computed using a multiphysics and multibody beam finite element model of the whole turbine, whereas detailed structural analysis is managed using shell finite element models. This raises the issue of the application of the loads extracted from the beam finite element model at one node for each section and transposed into the shell finite element model. After presenting the methods found in the literature, a new method is proposed. This takes into account the physical consistency of loads: aerodynamic loads are applied as pressure on the blade surface, and inertial loads are applied as body loads. Corrections imposed by pressure and body load computation in order to match loads from the beam finite element model are proposed and a comparison with two other methods is discussed.

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