Abstract
In the past year, smart rotor technology has been studied significantly as solution to the ever growing turbines. Aeroservoelastic tools are used to asses and predict the behavior of rotors using trailing edge devices like flaps. In this paper an unsteady aerodynamic model (Beddoes-Leishman type) and an CFD model (URANS) are used to analyze the aeroservoelastic response of a 2D three degree of freedom rigid body wind turbine airfoil with a deforming trailing edge flap encountering deterministic gusts. Both uncontrolled and controlled simulations are used to asses the differences between the two models for 2D aerservoelastic simulations. Results show an increase in the difference between models for the y component if the deforming trailing edge flap is used as control device. Observed flap deflections are significantly larger in the URANS model in certain cases, while the same controller is used. The pitch angle and moment shows large differences in the uncontrolled case, which become smaller, but remain significant when the controller is applied. Both models show similar reductions in vertical displacement, with a penalty of a significant increase in pitch angle deflections.
Highlights
Over the last years, smart rotor technology has attracted significant research interest in an effort to meet the challenges imposed by ever growing turbines
Several researchers have demonstrated numerically how efficiently adaptive trailing edge devices can address such load alleviation problems in the blade [1, 2] as well as in the complete turbine [3]. All of these simulations have been performed in aeroelastic software such as HAWC2 [4] and DU-SWAT [5]. Both tools use the same aerodynamic formulations, namely a blade element momentum approach combined with an implementation of the the adaptive trailing edge model that has been developed by the Danish Technical University (DTU) [6]
In addition to the airfoil with controller the uncontrolled cases are simulated to determine the decrease in vertical displacement
Summary
Smart rotor technology has attracted significant research interest in an effort to meet the challenges imposed by ever growing turbines. Several researchers have demonstrated numerically how efficiently adaptive trailing edge devices can address such load alleviation problems in the blade [1, 2] as well as in the complete turbine [3] All of these simulations have been performed in aeroelastic software such as HAWC2 [4] and DU-SWAT [5]. Both tools use the same aerodynamic formulations, namely a blade element momentum approach combined with an implementation of the the adaptive trailing edge model that has been developed by the Danish Technical University (DTU) [6]. The basis of these models is the 2D unsteady aerodynamic model
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