Advanced Wind Turbine Program Next Generation Turbine ... - NREL

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Power Production [kW 1,500 1,000 500 0 Steady Winds 9% Turbulence 0 5 10 15 20 25 30 Wind Speed [m/s] Figure 37. Predicted Power Performance for the EMD1.5/77 Turbine 4.2 EMD1.5/77 Component Designs 4.2.1 EMD Gearbox Modification To maintain the rotor tip speed at the baseline value of 73.8 m/s when operating at rated power, the gear ratio was increased to 78.25:1 rpm. The gearbox supplier analyzed the gearbox and determined that the change could be effected by modifying the third stage only. The first stage gear can accommodate the increased ultimate loads. 4.2.2 EMD 37-m Rotor Blade Design and Testing Several approaches to designing the 37-m blades were considered, including adding material to either or both of the root and the tip of the GE34a blade. GE finally decided to choose the approach motivated by energy capture and add all of the 3.25 m of new blade to the tip. The contour is exactly the same as that of the GE34a blade out to the 30.95-m spanwise location. Details of the blade geometry are shown in Figure 38. The GE37a blade employs another innovative feature: blade curvature. During the concept studies (see Section 2.3) it was noted that one alternative to blade coning is the use of blade curvature, that is, gradually curving the blade out of the rotor plane. For the GE37a blade, such curvature is only employed at the tip of the blade in order to provide a small amount of additional tower clearance. This is needed because of the extra length of the blade. The blade still employs 1.3° of forward precone in the root. 65
Figure 38. EMD 37-m (GE37a) Blade 66
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National Renewable Energy Laborator
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NOTICE This report was prepared as
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Abstract This document reports the
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In addition to innovations resultin
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3.2.3 Mechanical Loads Testing of t
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List of Symbols and Abbreviations A
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The SOW also stipulates that GE see
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2.1 Electromechanical Systems Conce
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Table 1. Summary of the Key Drive T
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2.1.1 Conventional-Speed Generators
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other than the wound rotor inductio
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offer compelling advantages to COE.
Page 25 and 26: cluded that the same would likely b
Page 27 and 28: cannot be designed for unity power
Page 29 and 30: Figure 5. Fatigue Damage Equivalent
Page 31 and 32: 2.3 Rotor and Structural Design Con
Page 33 and 34: 2.3.1.1 Upwind Rotor Blade and Towe
Page 35 and 36: Percent Change in Load Percent Chan
Page 37 and 38: the other three combinations of rot
Page 39 and 40: Percent Reduction in Component of F
Page 41 and 42: Design rules were used to estimate
Page 43 and 44: formed using the baseline rotor des
Page 45 and 46: duce an average flapwise deflection
Page 47 and 48: would be to reduce the COE by reduc
Page 49 and 50: 2.3.5 Boundary Layer Control GE com
Page 51 and 52: Perhaps the most important outcome
Page 53 and 54: Table 3. Proof of Concepts Turbine
Page 55 and 56: Figure 16. Schematic of the Proof o
Page 57 and 58: • Measure thermal characteristics
Page 59 and 60: Figure 21. POC Drive Train on the N
Page 61 and 62: • The lift and drag characteristi
Page 63 and 64: Figure 24. NGT POC Airfoil Family F
Page 65 and 66: One of the prototype blades was ini
Page 67 and 68: least 20 years of equivalent loadin
Page 69 and 70: 3.2.1 Power Performance Testing of
Page 71 and 72: Maxi mum Ti p Speed (m/s) Sound Pow
Page 73 and 74: Table 6. Engineering & Manufacturin
Page 75: GE briefly considered the costs and
Page 79 and 80: Development of the concept required
Page 81 and 82: Bench tests verified PLC control mo
Page 83 and 84: 4.3.2 Mechanical Loads Testing of t
Page 85 and 86: 5 Commercialization of GE NGT Techn
Page 87: F1146-E(12/2004) REPORT DOCUMENTATI
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