Computational prediction of airfoil dynamic stall

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The current state of offshore wind energy technology development

This paper deals with the aeroelastic instabilities that have occurred and may still occur for modern commercial wind turbines: stall-induced vibrations for stall-turbines, and classical flutter for pitch-regulated turbines. A review of previous works is combined with derivations of analytical stability limits for typical blade sections that show the fundamental mechanisms of these instabilities. The risk of stall-induced vibrations is mainly related to blade airfoil characteristics, effective direction of blade vibrations and structural damping; whereas the blade tip speed, torsional blade stiffness and chordwise position of the center of gravity along the blades are the main parameters for flutter. These instability characteristics are exemplified by aeroelastic stability analyses of different wind turbines. The review of each aeroelastic instability ends with a list of current research issues that represent unsolved aeroelastic instability problems for wind turbines. Copyright © 2007 John Wiley & Sons, Ltd.

Aeroelastic instability problems for wind turbines

Wind models for simulation of power fluctuations from wind farms

Dynamic Stall Model for Wind Turbine Airfoils

The present invention relates to a design concept by which the power, loads and/or stability of a wind turbine may be controlled by typically fast variation of the geometry of the blades using active geometry control (e.g. smart materials or by embedded mechanical actuators), or using passive geometry control (e.g. changes arising from loading and/or deformation of the blade) or by a combination of the two methods. The invention relates in particular to a wind turbine blade, a wind turbine and a method of controlling a wind turbine.

Control of power, loads and/or stability of a horizontal axis wind turbine by use of variable blade geometry control

There seems to be a significant uncertainty in aerodynamic and aeroelastic simulations on megawatt turbines operating in inflow with considerable shear, in particular with the engineering blade element momentum (BEM) model, commonly implemented in the aeroelastic design codes used by industry. Computations with advanced vortex and computational fluid dynamics models are used to provide improved insight into the complex flow phenomena and rotor aerodynamics caused by the sheared inflow. One consistent result from the advanced models is the variation of induced velocity as a function of azimuth when shear is present in the inflow. This gives guidance to how the BEM modeling of shear should be implemented. Another result from the advanced vortex model computations is a clear indication of influence of the ground, and the general tendency is a speed up effect of the flow through the rotor giving a higher power than in uniform flow. On the basis of the consistent azimuthal induction variations seen in the advanced model results, three different BEM implementation methods are discussed and tested in the same aeroelastic code. A full local BEM implementation on an elemental stream tube in both azimuth and radial direction seems to be closest to the advanced model results. Copyright © 2011 John Wiley & Sons, Ltd.

Blade element momentum modeling of inflow with shear in comparison with advanced model results

A dynamic stall model is used to analyze and reproduce open air blade section measurements as well as wind tunnel measurements. The dynamic stall model takes variations in both angle of attack and flow velocity into account. The paper gives a brief description of the dynamic stall model and presents results from analyses of dynamic stall measurements for a variety of experiments with different airfoils in wind tunnel and on operating rotors. The wind tunnel experiments comprises pitching as well as plunging motion of the airfoils. The dynamic stall model is applied for derivation of aerodynamic damping characteristics for cyclic motion of the airfoils in flapwise and edgewise direction combined with pitching. The investigation reveals that the airfoil dynamic stall characteristics depend on the airfoil shape, and the type of motion (pitch, plunge). The aerodynamic damping characteristics, and thus the sensitivity to stall induced vibrations, depend highly on the relative motion of the airfoil in flapwise and edgewise direction, and on a possibly coupled pitch variation, which is determined by the structural characteristics of the blade.

Dynamic stall and aerodynamic damping

A deformable trailing edge section (3) of a wind turbine blade (1), at least part of said section (3) being formed in a deformable material. The blade section (3) comprises one or more cavities (5) being in connection with or connectable to a fluid source in a way that allows fluid to stream from the fluid source to the cavity or cavities (5), so that the shape of the deformable trailing edge section (3) and thereby the camber of the blade cross-section (3) is changeable by the pressure of fluid in the cavity or cavities (5) with insignificant changes of the thickness and chord wise length of the deformable trailing edge section. Furthermore a wind turbine blade (1) is described, having at least one of such trailing edge section (s) (3) and to a system (11) for mounting a blade section (3) on a main blade (2) of a wind turbine. In addition a method of manufacturing a deformable trailing edge section (3) of a wind turbine blade (1) is disclosed.

Variable trailing edge section geometry for wind turbine blade

The double-stall phenomenon of aerofoil flows is characterized by at least two distinct stall levels for identical inflow conditions. In the present work a likely explanation of double stall is presented. Observations on full-scale rotors, in wind tunnel experiments and in CFD calculations could show at least two different distinct lift levels for identical inflow conditions, with sudden shifts between them. CFD calculations revealed the generation of a small, laminar separation bubble at the leading edge of the aerofoil for incidences near maximum lift. The bursting of this bubble could explain the sudden shift in lift levels. This investigation indicated that bursting will occur if the position of the free transition is only a small distance upstream from the position where forced transition would first cause leading-edge stall. Thus the investigation indicated that double stall is closely related to the actual geometry of the leading edge of the aerofoil and that it probably can be avoided in the design of new aerofoils. The investigation indicated further that double stall can be predicted from CFD calculations. Copyright © 1999 John Wiley & Sons, Ltd.

Flemming Rasmussen

Papers

Control of power, loads and/or stability of a horizontal axis wind turbine by use of variable blade geometry control

Blade element momentum modeling of inflow with shear in comparison with advanced model results

Dynamic stall and aerodynamic damping

Variable trailing edge section geometry for wind turbine blade

Observations and hypothesis of double stall