Www.risoe.dk LOAD ALLEVIATION ON WIND TURBINE BLADES USING VARIABLE AIRFOIL GEOMETRY Thomas Buhl, Mac Gaunaa, Peter Bjørn Andersen and Christian Bak ADAPWING.

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Presentation transcript:

LOAD ALLEVIATION ON WIND TURBINE BLADES USING VARIABLE AIRFOIL GEOMETRY Thomas Buhl, Mac Gaunaa, Peter Bjørn Andersen and Christian Bak ADAPWING 1

Outline Motivation for the present work 2D computations Tools Main Results 3D computations Tools Main Results Wind tunnel testing The model Preliminary results Conclusions Future work

Motivation for the work State of the art active load reduction employs pitching of whole wing Reductions of fatigue loads of up to 28% have been predicted But… Very long flexible blades may keep us from pitching fast enough to further reduce fatigue loads What if much faster load control could be possible? What if local load control on the blade could be possible?

Motivation for the work State of the art active load reduction employs pitching of whole wing Reductions of fatigue loads of up to 28% have been predicted But… Very long flexible blades may keep us from pitching fast enough to further reduce fatigue loads What if much faster load control could be possible? What if local load control on the blade could be possible? Inspiration: Mother nature Idea: Use adaptive trailing edge geometry

But why at the trailing edge? Potential thin-airfoil theory: #2: Low loads at TE… Both steady and unsteady. #1: Maximize bang for bucks

..And why not just a rigid flap? Surface discontinuity triggers stall  Noise issues Bad L/D leading to loss in power production Flap losing it’s potential load reduction effect  Go for the continuously deforming one! For everything shown here a 10% flap with limits: -5  >  >5  was used

2D: The tools Aerodynamics: Unsteady thin airfoil theory (potential flow) developed Modal expansion of the airfoil deflections Unsteady terms associated with wake modelled by the computationally efficient indicial method Model capable of predicting integral as well as local aerodynamic forces Good agreement with attached flow CFD

2D: The tools Structural model: Solid body + forces from TE deformation Control: Simple PID control using flapwise deflection as input 2D animation.avi

2D: Main results Huge potential fatigue load reduction (~80% reduction of std(N)) Low time lag essential Fast actuation velocity essential Trade-off to pitch DOF: Higher fatigue load in torsional direction.

3D model STRUCTURAL Slender cantilever beam theory Blade length 33m Known structural data Mode shapes and eigenfreq. 1f,2f,3f,4f,1e,2e,1Θ,2Θ AERODYNAMIC Turbulent wind series (Veers) Induced velocity (Bramwell) Dynamic inflow model (TUDk) Tip-loss factor (Prandtl) Known static lift and drag Dynamic flow (Gaunaa) CONTROL Local PID’s on flapwise deflection Parameters determined using optimization. min(eq. flapw. root mom.)

3D Results (1)

3D results (2)

3D results (3)

Wind Tunnel Testing The Actuator (piezo-electric) The Airfoil (Risø B1-18) video from the wind tunnel.wmv

Preliminary result (steady) Flap side-effect: Very high max lift!

Preliminary result (step flap)

Preliminary result (pitch + flap)

Conclusions Big (huge?) load reduction potential Time-delays in the system should be avoided at all costs Fast actuation velocity important Preliminary wind tunnel results look very promising: TE could cancel out lift variations from +-1  pitch motion

Future (and present) work Sensoring technique (how to determine the state of the wing dynamically) Combined pitch and flap control Model aerodynamic dynamic stall effects Implement into HAWC2 What are the implications of this stuff on dynamic stability More wind tunnel testing More realistic situations (whole span same flap control etc.)