Hi everyone,

I am running some simulations where I compare the effect of the two available skewed-wake correction model in Aerodyn v15.03 (Uncoupled and Pitt and Peters model) . My case presents a wind turbine with no tilt neither blade pre-cone. I use an uniform wind speed without shear effect.

Equation 30 in the report " Development and Validation of a New Blade Element Momentum Skewed-Wake Model within Aerodyn" ( http://www.nrel.gov/docs/fy15osti/63217.pdf ) , models the Pitt and Peters correction as function of the induction factor for each section:

Being X[size=50]0[/size] the angle between the vector normal to the rotor plane, in my case the yaw angle. I expect to obtain same results when using Uncoupled and Pitt and Peters models for yaw angle 0 ( the tangent term becomes 0). However, the models differ and I really do not understand why. I.e. I plot thrust of the turbine for both models:

Any idea why? Am I missing something?

Thank you,

Dear Albert,

I have not tried to reproduce your results, but I quickly skimmed the AeroDyn BEMT algorithm and it is not obvious to me how changing input SkewMod between uncoupled (SkewMod=1) and Pitt and Peters (SkewMod=2) would have any influence on the results if the inflow-skew angle were in fact zero. Have you output the inflow-skew angle (AeroDyn output RtSkew) to verify that it is in fact zero? Have you also noticed the inflow angle (output BαNβPhi), angle of attack (output BαNβAlpha), or the axial and/or tangential induction factors (outputs BαNβAxInd and/or BαNβTnInd) changing for certain blade nodes between these cases?

Best regards,

Dear Jason,

Thank you for your fast reply.

In both simulations the inflow-skew angle is 0 in all the simulation (as expected) . I took a look into the aerodynamic parameters you mentioned in your post , for nodes close to the root both induction factors (B1N1AxInd , B1N1TnInd) are the same. Therefore , the inflow and attack angle (B1N1Alpha , B1N1Phi) present a really good agreement.

However, If I output other blade nodes , i.e. node 9 , the tangential induction factor value (B1N9TnInd) for the uncoupled option remains -1 all the simulation. On the other hand, the Pitt and Peters model is 0 the whole simulation. The axial induction factor (B1N9AxInd) has also discrepancies, the Uncoupled model predicts a value of +1 the complete simulation while the Pitt and Peters is 0 . This has an impact in inflow and attack angle since I’m considering the tangential induction factor in the calculation (TanInd = TRUE). This results in this discrepancies over time :

I do not understand why the induction factors are different if the module is only supposed to correct the yaw misalignment. I’m missing something probably.

Any idea?

P.S. : The first node “B1N1…” corresponds to the first node of the blade and “B1N9…” is the last node of the blade, defined in BlOutNd as 1,3,5,9,11,13,15,17,19.

Dear Albert,

OK, thanks for looking into this more.

I looked in the source code (specifically SUBROUTINE ApplySkewedWakeCorrection() in source file BEMTUncoupled.f90) and noticed that if the axial and tangential induction factors (a and ap) are set to 1 or -1, respectively, both are reset to zero. This was added to avoid numerical problems in the calculation of the inflow-angle (phi) later in the code. However, earlier in the code, a=1 and ap=-1 is set at the root and tip when the root and tip loss models are enabled to ensure that no loads are computed at this nodes. So, in essence, the skewed-wake correction is over-writing the tip and hub loss effects at the root and tip in your case. Obviously, there is a problem in the logic here that we must fix. I’ve noted this as an issue that will be fixed in a future version.

Thanks for your help in debugging.

Best regards,

Dear Dr. Jonkman,

For the Pitt and Peter’s skewed wake correction is the angle between the vector normal to the rotor plane and the wind vector calculated at every blade section? What I mean is, under turbulent wind every blade section will have a different wind vector while the normal vector to the rotor plane remains same. In this situation should I calculate the angle for every section separately and use that angle for the skewed wake correction?

I would really appreciate if you could help clear this confusion.

Thanks a million,

Saptarshi

Dear Saptarshi,

The skew angle in the Pitt and Peters skewed-wake correction is defined as the angle between the vector normal to the rotor plane and the vector of the wind averaged across the rotor. This angle is the same for all blades.

Best regards,

Dear Dr. Jonkman,

Thanks a lot for clarifying this.

Saptarshi

Dear Jason,

I introduce myself to this topic because my question is about skew correction.

In particular, I was wondering the formulation of Xo (angle between the vector normal to the rotor plane) in case of non-constant wind and all 6 active platform DOFs.

Could you bring me the equation or a document in which it is reported?

Thanks for your help,

Lorenzo.

Dear Lorenzo,

The equation for the skew angle is calculated as described, i.e. the angle between the vector normal to the rotor plane and the vector of the wind averaged across the rotor. In the source code, it is calculated as:

skew = ACOS( V_DiskAvg dot xhat_Disk / 2NORM ( V_DiskAvg ) )

where V_DiskAvg is a the relative velocity (wind minus structure) averaged over the rotor disk and xhat_Disk is a unit vector normal to the disk.

Best regards,

Dear Jason,

I’m not sure what you mean by “wind averaged across the rotor”. Tell me if I understood correctly:

By defining V_DiskAvg = [V0_x, V0_y, V0_z] the vector of the wind speeds relative to the structure (wind minus structure) in the node under analysis, to be clear the same used in the BEM theory to obtain Vx and Vy according to the formula reported in “Development and Validation of a New Blade Element Momentum Skewed-Wake Model within AeroDyn” article where Vinf=V0_x.

The formula becomes:

skew = acos (V0_x / (sqrt (V0_x ^ 2 + V0_y ^ 2 + V0_z ^ 2)))

Confirm?

Thanks for the help,

Lorenzo.

Dear Lorenzo,

Equation (28) from Ning et al’s paper is not implemented in FAST / AeroDyn, as this formula is only valid for a rigid wind turbine and uniform flow.

In AeroDyn, the V_DiskAvg is computed by spatially averaging the relative wind velocity at each aerodynamic analysis node across the rotor, i.e.:

V_DiskAvg = SUM( SUM( V_wind(j,k) - V_structural(j,k), j = 1, 2, …, NumBlNds ), k = 1, 2, …, NumBlades )/( NumBlades*NumBlNds )

I hope that helps.

Best regards,

Dear Jason,

So V_DiskAvg becomes a constant vector for each time step like: V_DiskAvg = [V_DiskAvg_x, V_DiskAvg_y, V_DiskAvg_z]

and it will be

skew = acos (V_DiskAvg / (sqrt (V_DiskAvg_x^2 + V_DiskAvg_y^2 + V_DiskAvg_z^2)))

It is right?

Best regards,

Lorenzo

Dear Lorenzo,

If xhat_Disk is directed along the x axis, then:

skew = acos (V_DiskAvg_x / (sqrt (V_DiskAvg_x^2 + V_DiskAvg_y^2 + V_DiskAvg_z^2)))

Best regards,

Dear Jason,

Yes, I meant that, sorry for the typo.

Best regards,

Lorenzo.