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Introduction

The MEXICO project: The Database and Results of Data Processing and Interpretation Herman Snel, Gerard Schepers (ECN), Arn é Siccama (NRG). Introduction. MEXICO project = M odel EX periments I n Co ntrolled Conditions (European Union project, Framework Programme 5)

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Introduction

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  1. The MEXICO project: The Database and Results of Data Processing and Interpretation Herman Snel, Gerard Schepers (ECN), Arné Siccama (NRG)

  2. Introduction • MEXICO project = Model EXperimentsIn Controlled Conditions • (European Union project, Framework Programme 5) • Main objective: create a database of detailed aerodynamic measurements on a realistic wind turbine model, in a large high quality wind tunnel. Complementary to the NREL NASA Ames measurements • The database is to be used for aerodynamic model evaluation, validation and improvement, from BEM to CFD • The programme ran from 2001 to the end of 2006: • Dec 2006: a six day measurement campaign in the LLF of DNW (9.5 x 9.5 m2) with a 3 bladed model of 4.5 m diameter, leading to 100 GB of very useful data.

  3. Overview • Participants • Model and instrumentation • Flow field measurements, PIV • The measurement matrix and the data base • PIV quantitative flow field analyses • Comparison with CFD (Fluent) • Conclusions

  4. Participants and main tasks • ECN (NL): coordinator, model design and experiment coordination • Delft University of Technology (NL): 2D profile measurements, model data acquisition • NLR, NL: tunnel data acquisition and experiment coordination • RISOE National Laboratories: CFD and experimental matrix • Technical University if Denmark, DTU: CFD, tunnel effects • CRES (GR) CFD, tunnel effects • NTUA (GR) CFD, tunnel effects • FOI/FFA (S) flow visualization • Israel Institute of Technology Technion: model construction • National Renewable Energy Laboratories NREL (USA): invited participant • Subcontractor: DNW, wind tunnel facilities

  5. The model and the instrumentation • Three bladed rotor (NREL was 2 bladed) with a diameter of 4.5 m and a design tip speed ratio of 6.7. Tip speed for most of the measurements 100 m/s for a higher Re number (7.07 Hz) • Profiles: DU91-W2-250, RISOE A1-21 and NACA 64 418 • Total of 148 Kulite pressure sensors distributed over 5 sections, at 25, 35, 60, 85 and 95% radial position, in the three blades. • Two strain gauge bridges at the root of each of the blades. • Total forces and moments at the six component balance of DNW • Speed and pitch variable • Model data effective sampling frequency 5.5 kHz • Balance and tunnel data averaged over run (5 seconds, 35 revolutions)

  6. Blade layout DU 91 W2 250 Risø A1-21 2.25 m Kulite instrumented sections: 25% and 35 % DU 91 W2 250 60% Riso A1-21 82% and 92% NACA 64 418 NACA 64-418 -

  7. Zero rotor azimuth: blade 1 vertically upward Y PIV planes at 270 degrees azimuth PIV traverse tower with two cameras, aimed at horizontal PIV sheet of 35*42 cm2 in horizontal symmetry plane of the rotor Seeding (tiny soap bubbles) injected in settling chamber. Sheet is illuminated by laser flashes at 200 nanosecond interval and photographed. Sheet is subdivided into ‘interrogation windows’ (79*93, 4.3*4.3mm2). Velocity vector is the vector giving maximum correlation between these two shots. Flow field measurements, stereo PIV Photo: Gerard Schepers

  8. The measurement matrix. A) pressures and loads • Tip speed ratios varying from 3.3 to 10, at many tip angles • Yaw angles 0, ±15, ±30 and ±45 degrees • Rotor parked condition with blade angles varying from -5.3 to 90 degrees. • ‘Data points’ taken during 5 sec = 35 revolutions • Additionally: • Pitch angles ramps from -2.3° to 5° and back • Rotational speed ramps from tip speed of 100 m/s to 76 m/s and back

  9. The measurement matrix B) PIV • Particle Image Velocimetry (PIV) was carried out simultaneously with (repeated) pressure and load measurement, showing good repeatability. Tip speed ratios of 4.17, 6.7 and 10 • Three types: • In rotor plane, at 6 different azimuth angles between blades (flow between blades !) • Inflow and wake traverses at 2 radial stations (61% and 82%) • Tip vortex tracking • 30 to 100 ‘takes’ at 2.4 Hz (phase locked) • Both for axi-symmetric and yawed flow (plus and minus 30°)

  10. Results of inflow and wake traverses All data shown for tip speed of 100 m/s and -2.3° tip angle, zero yaw Tunnel speeds of 10 m/s, 15 m/s and 24 m/s l = 4.17 l = 6.7 Cylindrical vortex wake model l = 10

  11. The moment of truth The first intelligible pressure distribution appears in the quick look system, during the measurements

  12. Attached and stalled flow, PIV images just behind rotor, at 82% span. Flow direction To blade tip Attached flow l = 6.7: Thin viscous wake, left by passing blade Stalled flow l = 4.17: Much thicker blade wake and ‘trailing vortex’ at location of large jump in bound vorticity, explains chaotic behaviour in velocity decay

  13. Blade tip position at 2.25 m Axial velocity in radial traverse in rotor plane, for 0 and 120 azimuth Shows good repeatability and coherence between different PIV sheets

  14. Up-flow and down-flow effect of blades, yaw = 0 Measured Inflow for blade just below and just above PIV sheet. PIV sheet always at 270 ° azimuth position Blade tip position az = 40° az = 20 ° az = 40° az = 20 ° Difference of approximately 5 m/s, 1/3 of free tunnel speed !

  15. Trajectories for 3 tip speed ratios Tip vortex trajectories, axial flow l = 10 l =6.67 l = 4.17 l = 4.17 l = 6.67 l = 10 Vortex position against time: transportation speed constant!

  16. Vwake Y tunnel axis c Vw Rotor plane Wake skew angle c Vortex trajectories for 30 degrees yaw Flow direction Rotor plane position, seen from above

  17. PIV images of tip vortex trajectories for 30 degrees yaw

  18. Example of tip vortex in yawed flow Vortex roll up inward of tip position Blade tip position Flow direction

  19. Comparison with Fluent calculations for tip speed ratio of 6.7, tip angle of -2.3° and zero yaw(Design conditions)

  20. tunnel model Some grid details, tunnel environment included! blade 1/3 of the region covered, with symmetry boundary conditions 5.3 M cells, including tunnel environment

  21. Velocity components compared for axial traverse

  22. Comparison of wake expansion and radial traverse Calculated expansion much lower than measured !!?? Radial traverse at 30 cm behind rotor qualitatively good.

  23. Absolute pressure distributions at 5 radial stations compared

  24. Computed surface streamlines 3D stall is observed in computations, most likely not present in tip area

  25. A very large amount of very valuable data is available, to validate • Axi symmetric and yawed flow models, including turbulent wake state • Free vortex wake models • Dynamic stall models (in yaw) • General inflow modelling • CFD blade flow and near wake flow • Many years of work ahead, first ideas give hints towards improvements of BEM methods • An IEA Annex (has been / is being) set-up to coordinate this work (Gerard Schepers) • Acknowledgements • Financial support by EC 5th Framework program and by National Agencies Conclusions

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