Exploration On Aeroelastic Stability Of Large-scale Horizontal-axis Wind Turbine Blade In Engineering Application

The problem about aeroelastic stability of large-scale horizontal axis wind turbine blade is a key point in designing.If blades had unstable self-excited vibration, the entire wind turbine is extremely dangerous. In this paper, using theory of tail vortex system designs 650W horizontal axis wind turbine blades, and in accordance with the classic "strip theory" analyses the aerodynamic performance of blade. Then from the air force, inertial force and elastic force of the coupling point of view to study the aeroelastic wind turbine blade performance.The blades of a large horizontal axis wind turbine are operated by the air force, inertial force and elastic force, so the force of wind turbine is the most complex parts.In order to solve aeroelastic problem of wind turbine blade quickly and easily, often need to simplify the wind turbine blade modle.Based on past experiences, this paper get the simplified engineering aeroelastic wind turbine blade modle on the ground to 0.58 relative radius section as uniform beam regular section. And actual conditions of the machines can simplify the model with 0.84 relative radius section as uniform beam regular section to make fast engineering aeroelastic analysis. Finally comparing with past experiences about aeroelastic wind turbine blade model,this paper verifies its rationality.Second, bonding application of simplified uniform beam model about wind turbine blade at the actual operating condition, using the classic "strip theory" to analyse the aeroelastic performance about 650KW horizontal axis wind turbine. In engineering applications specially in the wind turbine blade design , designers need to quickly and easily determine whether the wind turbine blade has aeroelastic stability.Thus the purpose of this paper wish to proceed through the derivation about aeroelastic stability discrimination number of ahorizontal axis wind turbine blade S~hy in order to facilitate future aeroelastic stability analysis. Finally, using discrimination number to receive aeroelastic stability conclusions and blade section aeroelastic numerical results were compared with it to verify its legitimacy.Then, using blading section in two-dimensional beam model to establish differential equations of fluttering motion .By using 4th order Runge - Kutta numerical method, fluttering dynamic parameters were analyzed which fluence the structure of blade . Then a preliminary rule can be used in designed reference . Finally, its legitimacy is verified by the conclusions determined with the aeroelastic stability discrimination number S~hy were compared to numerical results received from the blade aeroelastic problem.