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0225U003313,
(0124U004405)
,
Scientific and Technical Principles for Reducing Aerodynamic Noise in Wind Turbine Blades
Визначення впливу нагнітання повітря в область задньої кромки лопаті на формування тонального шуму
Aleksieienko Serhii V., Доктор технічних наук
18-06-2025
Dnipro University of Technology
The main goal is to study and develop the scientific and technical principles of reducing the level of aerodynamic noise of small and medium-sized wind turbines, which occurs as a result of the formation of vortex emissions from the leeward side of the wind turbine blade and their further interaction with the trailing edge of the blade.
Experimental studies of the acoustic characteristics of a modified test blade segment with a NACA0012 profile were conducted. The well-known effect of noise reduction due to serrations on the trailing edge of the profile was successfully reproduced. The results obtained confirm the applicability of the developed experimental methodology and its suitability for further evaluation of other innovative methods for reducing aerodynamic noise. The numerical method for investigating the aerodynamic noise of a blade segment was refined by transitioning from a two-dimensional to a three-dimensional problem formulation, with the segment span length up to 20% of the chord length. Numerical simulations were also performed to analyze the influence of air injection into the leeward part of the trailing edge of the blade segment on pressure fluctuations. Using the NACA0012 test profile, the effect of injection directly into the trailing edge region, as well as at various points along the leeward surface, was investigated. The optimal design features and locations of the air injection elements were identified. These were shown to significantly reduce the intensity of vortex structure development in the boundary layer and, consequently, decrease both acoustic radiation from the trailing edge and near-field aerodynamic pressure levels. Experimental study of the influence of air injection into the leeward part of the trailing edge of the blade segment on the level of aerodynamic noise was performed using the example of a DU93-W-210 profile segment with incident flow parameters. Theт results confirmed the effectiveness of the proposed solution, demonstrating a reduction in the sound pressure level by 2-5 dB in the frequency range of 200–800 Hz; can be used in the design of fan blades of various types, to improve the designs of aircraft wings, propellers, propellers of unmanned aerial vehicles
Harkavenko Dmytro V.
Derbaba Vitalii A.
Dreus Andrii Yu.
Dron Mykola М.
Nakashydze Liliia V.
Shcherbyna Yevhen Yu.
2025-06-18
Updated: 2025-12-20
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