RESEARCH ON DYNAMIC TEST TECHNOLOGY FOR WIND TURBINE BLADE AIRFOIL

doi:10.6052/0459-1879-18-108

Abstract

Abstract:

The dynamic oscillation process of wind turbine blades is usually accompanied by pitching and yaw. Due to the unclear understanding of many dynamic problems previously, a safer design is adopted at the expense of increasing the weight of the blade structure in engineering, usually neglecting the influence of the yaw oscillation. The design of large wind turbines has put forward higher requirements for obtaining more comprehensive and accurate dynamic loads of airfoils. It is of great significance to study the influence of yaw oscillation on the dynamic aerodynamic characteristics of airfoil. In view of this, the dynamic wind tunnel test on yaw oscillation of airfoil is carried out in this paper for the first time. The “electronic cam” technology is used instead of the mechanical cam to realize the stepless adjustment of oscillation frequency and oscillation angle. Based on the designed electronic external trigger device, the real-time measurement of the dynamic flow field is realized. Meanwhile, the synchronous acquisition of wind tunnel flow, model angular displacement and dynamic pressure data is realized. Furthermore, the static pressure measurement, pitching / yaw dynamic pressure measurement, PIV and fluorescent wire test are carried out respectively. The accuracy of the test results is high, and the regular pattern is reasonable. Besides, the influence mechanism of wall interference in dynamic test is analyzed. Research shows that: there is also obvious hysteresis effect on the dynamic aerodynamic parameters of yaw oscillation airfoil with the changing of the angle of attack. And with the increase of oscillation frequency, the aerodynamic hysteresis characteristics of the airfoil under pitching and yaw oscillation are all enhanced. The dynamic stall vortex at the positive stroke is delayed due to the pitching oscillation. The pressure distribution of the airfoil is greatly influenced by the strong three-dimensional effect at the intersection of the wind tunnel wall and the model tip. Overall, the dynamic test technique of yaw oscillation established in this paper can provide technical support for the study of the dynamic swept effect of the wind turbines.

Key words: wind turbine, airfoil, yaw oscillation, pressure measurement, wind tunnel test

CLC Number:

O355

Li Guoqiang, Zhang Weiguo, Chen Li, Nie Bowen, Zhang Peng, Yue Tingrui. RESEARCH ON DYNAMIC TEST TECHNOLOGY FOR WIND TURBINE BLADE AIRFOIL[J]. Chinese Journal of Theoretical and Applied Mechanics, 2018, 50(4): 751-765.

Figures/Tables 22

Fig.1 Schematic of airfoil oscillation types

Fig.2 Control of driving device

Fig.3 S809 airfoil model

Fig.4 The shape and performance of potentiometer

Fig.5 Size and shape of dynamic pressure sensor (8510B type)

Fig.6 Pitot-static tube for measuring wind speed

Fig.7 PIV system and external triggering device for airfoil pitching oscillation test

Table 1 Technical index of the camera and laser

Index	Value
resolution	$1024 × 1024$
full frame frequency	3.6 kHz
maximum frame	2*13.5 kHz at $512 × 512$
frequency
minimum frame interval	<1 μs
dynamic range	12 bit
laser wavelength	527 nm
laser energy	$2 × 100$ mJ
laser frequency	$# x 2264;$ 50 Hz

Table 1 Technical index of the camera and laser

Index	Value
resolution	$1024 × 1024$
full frame frequency	3.6 kHz
maximum frame	2*13.5 kHz at $512 × 512$
frequency
minimum frame interval	<1 μs
dynamic range	12 bit
laser wavelength	527 nm
laser energy	$2 × 100$ mJ
laser frequency	$# x 2264;$ 50 Hz

Fig.8 Fluorescent-wire method for measuring the flow of yaw oscillating airfoil

Fig.9 Schematic diagram for the sinusoidal oscillation of model driven by the driving device

Fig.10 Scheme of synchronous measurement and acquisition for airfoil dynamic pressure test

Fig.11 Comparison of surface pressure distribution of airfoil with OSU wind tunnel data at 16.1 °AOA

Fig.12 CL-α curve of airfoil measured by dynamic pressure sensors

Fig.13 Comparison of dynamic and static results with Re=6.2×105

Fig.15 Dynamic aerodynamic characteristics of airfoil under different conversion frequencies

Fig.16 α0=14°,β1=20°, lift and pitching moment Coefficient under different oscillating frequencies

Fig.17 q∞=540Pa,α0=10°,α1=15°,f=0.5Hz, PIV results

Fig.18 The flow regime on the top surface of yaw oscillation reverse-loading airfoil

Fig.19 q∞=540Pa,α0=10°,α1=10°,f=0.5Hz, ↓15.52°, velocity contour and streamline of airfoil

Fig.20 The 3-D airfoil dynamic stall vortex under wall interference, Q isosurface development

Fig.21 q∞=540Pa,α0=10°,α1=10°,f=3Hz, ↓19.6°, comparison of pressure distribution of airfoil

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