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Final report for WP4.3: Enhancement of design methods ... - Upwind

Final report for WP4.3: Enhancement of design methods ... - Upwind

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UPWIND WP4: Offshore Support Structures and Foundations<br />

The computational grid used consists <strong>of</strong> the components blade, hub and background grid, leading to total number<br />

<strong>of</strong> about 10 million grid points. Refined grids around each blade (Figure 8.1, green grid) with a dimensionless<br />

grid distance y+-value between 0.1 and 2 are embedded in a cylindrical grid around the hub (Figure<br />

8.1, red grid), which is rotating within a coarser background grid (Figure 8.1, blue grid). Overall, the grid has the<br />

in-plane dimension <strong>of</strong> 3 rotor diameters in each direction, centred at the hub, and an out <strong>of</strong> plane dimension <strong>of</strong><br />

3.5 diameters upwind and downwind respectively. FLOWer features the Chimera technique [109], allowing <strong>for</strong><br />

arbitrary relative motion <strong>of</strong> aerodynamic bodies. Applying the Chimera technique, the previously described pitch<br />

motion was prescribed as a rigid body motion on the rotor and hub grids, which are moving within the background<br />

meshes. Chimera is also applied <strong>for</strong> modelling the rotor rotation. In this study, no elastic de<strong>for</strong>mation <strong>of</strong><br />

the blade is introduced, but fluid-structure coupled simulations are planned <strong>for</strong> next analyses. Further studies<br />

will also include the tower and nacelle, as already per<strong>for</strong>med by Meister et. al. with FLOWer <strong>for</strong> a 5MW onshore<br />

turbine without prescribed floating motions [110].<br />

The presented CFD results showed good numerical convergence, there<strong>for</strong>e it is assumed that the presented<br />

flowfield is realistically representing the actual aerodynamic conditions during such a motion. Nevertheless the<br />

presented results are only a preliminary study and need further validation from CFD and potential flow calculations,<br />

as well as, ultimately, experimental data.<br />

Figure 8.1: Prescribed rotor motion <strong>for</strong> CFD study and CFD mesh<br />

The pressure distribution over the blades is presented in Figure 8.2. Motion (1) corresponds to the first half <strong>of</strong><br />

the downwind swing (c.f. Figure 8.1), i.e. 4/3 rotor rotations, motion (2) corresponds to the 2 nd half <strong>of</strong> the downwind<br />

swing and the first half <strong>of</strong> the upwind swing, i.e. from 5/3 to 4 rotor rotations, and motion (3) finally represents<br />

the last half <strong>of</strong> the upwind swing, i.e. 13/3 to 5 rotor rotations. During motion (1), the pressure is decreasing<br />

due to the backward motion and the increased turbulence in the wake. When the turbine is pitching upwind<br />

again (2), the pressure on the blades is increasing until the rotor is back in vertical position and then slightly<br />

decreasing until the end <strong>of</strong> move (2). The pressure increase is due to the increased inflow velocity, and possibly<br />

also due to rotor wake interactions. In the last part <strong>of</strong> the period (3), the pressure again is decreasing, but to a<br />

lesser extent than in the first downwind motion (1).<br />

Figure 8.2: Pressure contours <strong>of</strong> rotor during prescribed motion<br />

92

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