https://orcid.org/0000-0001-6938-2295
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ABSTRACT
Remote areas in Northwest China are blind regions without large-scale power grid coverage. To satisfy the residential electricity demand, it is essential to utilize small-scale distributed wind power systems and increase wind energy utilization. The seagull airfoil wind energy conversion device is adopted to improve the aerodynamic performance and increase the use of wind energy. Based on the wind tunnel experiment and numerical simulation, the bending shape of the seagull airfoil is optimized. Further, the cascade structure is constructed using the central bending seagull airfoil to explore the flow mechanisms. The front and rear cascades are the main and secondary regions, accounting for 84% and 16% of the force generated, respectively. The deformation of the blade is significantly larger at the trailing edge than at the leading edge, thereby exhibiting unique deformation characteristics of seagull airfoils. When the impeller is rotated, the average force of each seagull airfoil was 15.1% more than that of the flat airfoil, thereby enabling the absorption of more wind energy and device optimization. Owing to the stress and deformation distribution, the seagull airfoil blade can adapt to different aerodynamic loads by changing the cambers and angles of attack to ensure smooth operation of the device.
Acknowledgments
This project is supported by the sponsorship of Inner Mongolia Science & Technology Project Plan “Research on Dynamic Response of Wind Turbine Blade Structure and Application Demonstration of Crack Detection” (2019).
Nomenclature
| a | = | Angle of attack (AOA) |
| C | = | Airfoil chord length (mm) |
| Cp | = | Pressure coefficient |
| CL | = | Lift coefficient |
| CD | = | Drag coefficient |
| CPL | = | Airfoil lower surface pressure coefficient |
| CPU | = | Airfoil upper surface pressure coefficient |
| ΔCL | = | Difference in L under adjacent conditions |
| Cle | = | Experimental lift coefficient |
| CLs | = | Simulated lift coefficient |
| |ΔCL| | = | Absolute value of the difference between CLe and CLs |
| 3D | = | Three dimensional |
| Δ | = | Relative error between experimental and simulated lift coefficients (%) |
| E | = | Elastic modulus (MPa) |
| F | = | Tension force caused by wind |
| FS | = | Full scale (%) |
| f | = | Mean cambers of airfoils |
| L | = | Airfoil span length (mm) |
| L | = | Lift force (N) |
| N | = | Grid number |
| P∞ | = | Pressure of the wind tunnel inlet (Pa) |
| Pu | = | Upper surface of the blade |
| Pl | = | Lower surface of the blade |
| Pi | = | Dynamic pressure (Pa) |
| ρair | = | Air density (kg/m3) |
| ρm | = | Material density (kg/m3) |
| ξ | = | Thickness of the seagull airfoil (mm) |
| μ | = | Poisson’s ratio |
| vmax | = | Max wind speed (m/s) |
| Δs | = | Micro-element area of the blade |
| TI | = | Turbulence intensity (%) |
| V∞ | = | Wind velocity of wind tunnel inlet |
| w | = | Growth rate w of each blade F |
| X | = | Distance along chord from the leading edge (mm) |
| Z | = | Distance along span from the leading edge (mm) |
| Zu | = | Curvilinear coordinates of the upper surface of the airfoil |
| Zl | = | Curvilinear coordinates under the airfoil surface |
| Z(c) | = | Airfoil shape line coordinates |
| Z(t) | = | Profile coordinates of airfoil thickness distribution |
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