# (Array): initial structural grid on unit radius rotor.initial_str_grid = np.array([0.0, 0.00492790457512, 0.00652942887106, 0.00813095316699, 0.00983257273154, 0.0114340970275, 0.0130356213234, 0.02222276, 0.024446481932, 0.026048006228, 0.06666667, 0.089508406455, 0.11111057, 0.146462614229, 0.16666667, 0.195309105255, 0.23333333, 0.276686558545, 0.3, 0.333640766319,0.36666667, 0.400404310407, 0.43333333, 0.5, 0.520818918408, 0.56666667, 0.602196371696, 0.63333333, 0.667358391486, 0.683573824984, 0.7, 0.73242031601, 0.76666667, 0.83333333, 0.88888943, 0.93333333, 0.97777724, 1.0]) # (Int): first idx in r_aero_unit of non-cylindrical section, # constant twist inboard of here rotor.idx_cylinder_aero = 3 # (Int): first idx in r_str_unit of non-cylindrical section rotor.idx_cylinder_str = 14 # (Float): hub location as fraction of radius rotor.hubFraction = 0.025 # ------------------ # === blade geometry === # (Array): new aerodynamic grid on unit radius rotor.r_aero = np.array([0.02222276, 0.06666667, 0.11111057, 0.2, 0.23333333, 0.3, 0.36666667, 0.43333333, 0.5, 0.56666667, 0.63333333, 0.64, 0.7, 0.83333333, 0.88888943, 0.93333333, 0.97777724]) # (Float): location of max chord on unit radius rotor.r_max_chord = 0.23577 # (Array, m): chord at control points. defined at hub, then at linearly spaced
def EvaluateLCOE(BladeLength, HubHeight, MaximumRotSpeed,Verbose=False): ############################################################################ # Define baseline paremeters used for scaling ReferenceBladeLength = 35; ReferenceTowerHeight = 95 WindReferenceHeight = 50 WindReferenceMeanVelocity = 3 WeibullShapeFactor = 2.0 ShearFactor = 0.25 RatedPower = 1.5e6 # Years used for analysis Years = 25 DiscountRate = 0.08 ############################################################################ ############################################################################ ### 1. Aerodynamic and structural performance using RotorSE rotor = RotorSE() # ------------------- # === blade grid === # (Array): initial aerodynamic grid on unit radius rotor.initial_aero_grid = np.array([0.02222276, 0.06666667, 0.11111057, \ 0.16666667, 0.23333333, 0.3, 0.36666667, 0.43333333, 0.5, 0.56666667, \ 0.63333333, 0.7, 0.76666667, 0.83333333, 0.88888943, 0.93333333, \ 0.97777724]) # (Array): initial structural grid on unit radius rotor.initial_str_grid = np.array([0.0, 0.00492790457512, 0.00652942887106, 0.00813095316699, 0.00983257273154, 0.0114340970275, 0.0130356213234, 0.02222276, 0.024446481932, 0.026048006228, 0.06666667, 0.089508406455, 0.11111057, 0.146462614229, 0.16666667, 0.195309105255, 0.23333333, 0.276686558545, 0.3, 0.333640766319,0.36666667, 0.400404310407, 0.43333333, 0.5, 0.520818918408, 0.56666667, 0.602196371696, 0.63333333, 0.667358391486, 0.683573824984, 0.7, 0.73242031601, 0.76666667, 0.83333333, 0.88888943, 0.93333333, 0.97777724, 1.0]) # (Int): first idx in r_aero_unit of non-cylindrical section, # constant twist inboard of here rotor.idx_cylinder_aero = 3 # (Int): first idx in r_str_unit of non-cylindrical section rotor.idx_cylinder_str = 14 # (Float): hub location as fraction of radius rotor.hubFraction = 0.025 # ------------------ # === blade geometry === # (Array): new aerodynamic grid on unit radius rotor.r_aero = np.array([0.02222276, 0.06666667, 0.11111057, 0.2, 0.23333333, 0.3, 0.36666667, 0.43333333, 0.5, 0.56666667, 0.63333333, 0.64, 0.7, 0.83333333, 0.88888943, 0.93333333, 0.97777724]) # (Float): location of max chord on unit radius rotor.r_max_chord = 0.23577 # (Array, m): chord at control points. defined at hub, then at linearly spaced # locations from r_max_chord to tip ReferenceChord = [3.2612, 4.5709, 3.3178, 1.4621] rotor.chord_sub = [x * np.true_divide(BladeLength,ReferenceBladeLength) \ for x in ReferenceChord] # (Array, deg): twist at control points. defined at linearly spaced locations # from r[idx_cylinder] to tip rotor.theta_sub = [13.2783, 7.46036, 2.89317, -0.0878099] # (Array, m): precurve at control points. defined at same locations at chord, # starting at 2nd control point (root must be zero precurve) rotor.precurve_sub = [0.0, 0.0, 0.0] # (Array, m): adjustment to precurve to account for curvature from loading rotor.delta_precurve_sub = [0.0, 0.0, 0.0] # (Array, m): spar cap thickness parameters rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398] # (Array, m): trailing-edge thickness parameters rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569] # (Float, m): blade length (if not precurved or swept) # otherwise length of blade before curvature rotor.bladeLength = BladeLength # (Float, m): adjustment to blade length to account for curvature from # loading rotor.delta_bladeLength = 0.0 rotor.precone = 2.5 # (Float, deg): precone angle rotor.tilt = 5.0 # (Float, deg): shaft tilt rotor.yaw = 0.0 # (Float, deg): yaw error rotor.nBlades = 3 # (Int): number of blades # ------------------ # === airfoil files === basepath = os.path.join(os.path.dirname(\ os.path.realpath(__file__)), '5MW_AFFiles') # load all airfoils airfoil_types = [0]*8 airfoil_types[0] = os.path.join(basepath, 'Cylinder1.dat') airfoil_types[1] = os.path.join(basepath, 'Cylinder2.dat') airfoil_types[2] = os.path.join(basepath, 'DU40_A17.dat') airfoil_types[3] = os.path.join(basepath, 'DU35_A17.dat') airfoil_types[4] = os.path.join(basepath, 'DU30_A17.dat') airfoil_types[5] = os.path.join(basepath, 'DU25_A17.dat') airfoil_types[6] = os.path.join(basepath, 'DU21_A17.dat') airfoil_types[7] = os.path.join(basepath, 'NACA64_A17.dat') # place at appropriate radial stations af_idx = [0, 0, 1, 2, 3, 3, 4, 5, 5, 6, 6, 7, 7, 7, 7, 7, 7] n = len(af_idx) af = [0]*n for i in range(n): af[i] = airfoil_types[af_idx[i]] rotor.airfoil_files = af # (List): names of airfoil file # ---------------------- # === atmosphere === rotor.rho = 1.225 # (Float, kg/m**3): density of air rotor.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air rotor.shearExp = 0.25 # (Float): shear exponent rotor.hubHt = HubHeight # (Float, m): hub height rotor.turbine_class = 'I' # (Enum): IEC turbine class rotor.turbulence_class = 'B' # (Enum): IEC turbulence class class rotor.cdf_reference_height_wind_speed = 30.0 rotor.g = 9.81 # (Float, m/s**2): acceleration of gravity # ---------------------- # === control === rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed rotor.control.Vout = 26.0 # (Float, m/s): cut-out wind speed rotor.control.ratedPower = RatedPower # (Float, W): rated power # (Float, rpm): minimum allowed rotor rotation speed # (Float, rpm): maximum allowed rotor rotation speed rotor.control.minOmega = 0.0 rotor.control.maxOmega = MaximumRotSpeed # (Float): tip-speed ratio in Region 2 (should be optimized externally) rotor.control.tsr = 7 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines) rotor.control.pitch = 0.0 # (Float, deg): worst-case pitch at survival wind condition rotor.pitch_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition rotor.azimuth_extreme = 0.0 # (Float): fraction of rated speed at which the deflection is assumed to # representative throughout the power curve calculation rotor.VfactorPC = 0.7 # ---------------------- # === aero and structural analysis options === # (Int): number of sectors to divide rotor face into in computing thrust and power rotor.nSector = 4 # (Int): number of points to evaluate aero analysis at rotor.npts_coarse_power_curve = 20 # (Int): number of points to use in fitting spline to power curve rotor.npts_spline_power_curve = 200 # (Float): availability and other losses (soiling, array, etc.) rotor.AEP_loss_factor = 1.0 rotor.drivetrainType = 'geared' # (Enum) # (Int): number of natural frequencies to compute rotor.nF = 5 # (Float): a dynamic amplification factor to adjust the static deflection # calculation rotor.dynamic_amplication_tip_deflection = 1.35 # ---------------------- # === materials and composite layup === basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), \ '5MW_PrecompFiles') materials = Orthotropic2DMaterial.listFromPreCompFile(os.path.join(basepath,\ 'materials.inp')) ncomp = len(rotor.initial_str_grid) upper = [0]*ncomp lower = [0]*ncomp webs = [0]*ncomp profile = [0]*ncomp # (Array): array of leading-edge positions from a reference blade axis # (usually blade pitch axis). locations are normalized by the local chord # length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference # axis. positive in -x direction for airfoil-aligned coordinate system rotor.leLoc = np.array([0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.498, 0.497, 0.465, 0.447, 0.43, 0.411, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4]) # (Array): index of sector for spar (PreComp definition of sector) rotor.sector_idx_strain_spar = [2]*ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector) rotor.sector_idx_strain_te = [3]*ncomp web1 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.4114, 0.4102, 0.4094, 0.3876, 0.3755, 0.3639, 0.345, 0.3342, 0.3313, 0.3274, 0.323, 0.3206, 0.3172, 0.3138, 0.3104, 0.307, 0.3003, 0.2982, 0.2935, 0.2899, 0.2867, 0.2833, 0.2817, 0.2799, 0.2767, 0.2731, 0.2664, 0.2607, 0.2562, 0.1886, -1.0]) web2 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.5886, 0.5868, 0.5854, 0.5508, 0.5315, 0.5131, 0.4831, 0.4658, 0.4687, 0.4726, 0.477, 0.4794, 0.4828, 0.4862, 0.4896, 0.493, 0.4997, 0.5018, 0.5065, 0.5101, 0.5133, 0.5167, 0.5183, 0.5201, 0.5233, 0.5269, 0.5336, 0.5393, 0.5438, 0.6114, -1.0]) web3 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0]) # (Array, m): chord distribution for reference section, thickness of structural # layup scaled with reference thickness (fixed t/c for this case) rotor.chord_str_ref = np.array([3.2612, 3.3100915356, 3.32587052924, 3.34159388653, 3.35823798667, 3.37384375335, 3.38939112914, 3.4774055542, 3.49839685, 3.51343645709, 3.87017220335, 4.04645623801, 4.19408216643, 4.47641008477, 4.55844487985, 4.57383098262, 4.57285771934, 4.51914315648, 4.47677655262, 4.40075650022, 4.31069949379, 4.20483735936, 4.08985563932, 3.82931757126, 3.74220276467, 3.54415796922, 3.38732428502, 3.24931446473, 3.23421422609, 3.22701537997, 3.21972125648, 3.08979310611, 2.95152261813, 2.330753331, 2.05553464181, 1.82577817774, 1.5860853279, 1.4621])* \ np.true_divide(BladeLength,ReferenceBladeLength) for i in range(ncomp): webLoc = [] if web1[i] != -1: webLoc.append(web1[i]) if web2[i] != -1: webLoc.append(web2[i]) if web3[i] != -1: webLoc.append(web3[i]) upper[i], lower[i], webs[i] = CompositeSection.initFromPreCompLayupFile\ (os.path.join(basepath, 'layup_' + str(i+1) + '.inp'), webLoc, materials) profile[i] = Profile.initFromPreCompFile(os.path.join(basepath, 'shape_' \ + str(i+1) + '.inp')) # (List): list of all Orthotropic2DMaterial objects used in # defining the geometry rotor.materials = materials # (List): list of CompositeSection objections defining the properties for # upper surface rotor.upperCS = upper # (List): list of CompositeSection objections defining the properties for # lower surface rotor.lowerCS = lower # (List): list of CompositeSection objections defining the properties for # shear webs rotor.websCS = webs # (List): airfoil shape at each radial position rotor.profile = profile # -------------------------------------- # === fatigue === # (Array): nondimensional radial locations of damage equivalent moments rotor.rstar_damage = np.array([0.000, 0.022, 0.067, 0.111, 0.167, 0.233, 0.300, 0.367, 0.433, 0.500, 0.567, 0.633, 0.700, 0.767, 0.833, 0.889, 0.933, 0.978]) # (Array, N*m): damage equivalent moments about blade c.s. x-direction rotor.Mxb_damage = 1e3*np.array([2.3743E+003, 2.0834E+003, 1.8108E+003, 1.5705E+003, 1.3104E+003, 1.0488E+003, 8.2367E+002, 6.3407E+002, 4.7727E+002, 3.4804E+002, 2.4458E+002, 1.6339E+002, 1.0252E+002, 5.7842E+001, 2.7349E+001, 1.1262E+001, 3.8549E+000, 4.4738E-001]) # (Array, N*m): damage equivalent moments about blade c.s. y-direction rotor.Myb_damage = 1e3*np.array([2.7732E+003, 2.8155E+003, 2.6004E+003, 2.3933E+003, 2.1371E+003, 1.8459E+003, 1.5582E+003, 1.2896E+003, 1.0427E+003, 8.2015E+002, 6.2449E+002, 4.5229E+002, 3.0658E+002, 1.8746E+002, 9.6475E+001, 4.2677E+001, 1.5409E+001, 1.8426E+000]) rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap # (Float): uptimate strain in trailing-edge panels, note that I am putting a # factor of two for the damage part only. rotor.strain_ult_te = 2500*1e-6 * 2 rotor.eta_damage = 1.35*1.3*1.0 # (Float): safety factor for fatigue rotor.m_damage = 10.0 # (Float): slope of S-N curve for fatigue analysis # (Float): number of cycles used in fatigue analysis rotor.N_damage = 365*24*3600*20.0 # ---------------- # from myutilities import plt # === run and outputs === rotor.run() # Evaluate AEP Using Lewis' Functions # Weibull Wind Parameters WindReferenceHeight = 50 WindReferenceMeanVelocity = 7.5 WeibullShapeFactor = 2.0 ShearFactor = 0.25 PowerCurve = rotor.P/1e6 PowerCurveVelocity = rotor.V HubHeight = rotor.hubHt AEP,WeibullScale = CalculateAEPWeibull(PowerCurve,PowerCurveVelocity, HubHeight, \ BladeLength,WeibullShapeFactor, WindReferenceHeight, \ WindReferenceMeanVelocity, ShearFactor) NamePlateCapacity = EstimateCapacity(PowerCurve,PowerCurveVelocity, \ rotor.ratedConditions.V) # AEP At Constant 7.5m/s Wind used for benchmarking... #AEP = CalculateAEPConstantWind(PowerCurve, PowerCurveVelocity, 7.5) if (Verbose ==True): print '################### ROTORSE ######################' print 'AEP = %d MWH' %(AEP) print 'NamePlateCapacity = %fMW' %(NamePlateCapacity) print 'diameter =', rotor.diameter print 'ratedConditions.V =', rotor.ratedConditions.V print 'ratedConditions.Omega =', rotor.ratedConditions.Omega print 'ratedConditions.pitch =', rotor.ratedConditions.pitch print 'mass_one_blade =', rotor.mass_one_blade print 'mass_all_blades =', rotor.mass_all_blades print 'I_all_blades =', rotor.I_all_blades print 'freq =', rotor.freq print 'tip_deflection =', rotor.tip_deflection print 'root_bending_moment =', rotor.root_bending_moment print '#########################################################' ############################################################################# ### 2. Hub Sizing # Specify hub parameters based off rotor # Load default hub model hubS = HubSE() hubS.rotor_diameter = rotor.Rtip*2 # m hubS.blade_number = rotor.nBlades hubS.blade_root_diameter = rotor.chord_sub[0]*1.25 hubS.L_rb = rotor.hubFraction*rotor.diameter hubS.MB1_location = np.array([-0.5, 0.0, 0.0]) hubS.machine_rating = rotor.control.ratedPower hubS.blade_mass = rotor.mass_one_blade hubS.rotor_bending_moment = rotor.root_bending_moment hubS.run() RotorTotalWeight = rotor.mass_all_blades + hubS.spinner.mass + \ hubS.hub.mass + hubS.pitchSystem.mass if (Verbose==True): print '##################### Hub SE ############################' print "Estimate of Hub Component Sizes:" print "Hub Components" print ' Hub: {0:8.1f} kg'.format(hubS.hub.mass) print ' Pitch system: {0:8.1f} kg'.format(hubS.pitchSystem.mass) print ' Nose cone: {0:8.1f} kg'.format(hubS.spinner.mass) print 'Rotor Total Weight = %d kg' %RotorTotalWeight print '#########################################################' ############################################################################ ### 3. Drive train + Nacelle Mass estimation nace = Drive4pt() nace.rotor_diameter = rotor.Rtip *2 # m nace.rotor_speed = rotor.ratedConditions.Omega # #rpm m/s nace.machine_rating = hubS.machine_rating/1000 nace.DrivetrainEfficiency = 0.95 # 6.35e6 #4365248.74 # Nm nace.rotor_torque = rotor.ratedConditions.Q nace.rotor_thrust = rotor.ratedConditions.T # N nace.rotor_mass = 0.0 #accounted for in F_z # kg nace.rotor_bending_moment_x = rotor.Mxyz_0[0] nace.rotor_bending_moment_y = rotor.Mxyz_0[1] nace.rotor_bending_moment_z = rotor.Mxyz_0[2] nace.rotor_force_x = rotor.Fxyz_0[0] # N nace.rotor_force_y = rotor.Fxyz_0[1] nace.rotor_force_z = rotor.Fxyz_0[2] # N # geared 3-stage Gearbox with induction generator machine nace.drivetrain_design = 'geared' nace.gear_ratio = 96.76 # 97:1 as listed in the 5 MW reference document nace.gear_configuration = 'eep' # epicyclic-epicyclic-parallel nace.crane = True # onboard crane present nace.shaft_angle = 5.0 #deg nace.shaft_ratio = 0.10 nace.Np = [3,3,1] nace.ratio_type = 'optimal' nace.shaft_type = 'normal' nace.uptower_transformer=False nace.shrink_disc_mass = 333.3*nace.machine_rating/1000.0 # estimated nace.mb1Type = 'CARB' nace.mb2Type = 'SRB' nace.flange_length = 0.5 #m nace.overhang = 5.0 nace.gearbox_cm = 0.1 nace.hss_length = 1.5 #0 if no fatigue check, 1 if parameterized fatigue check, #2 if known loads inputs nace.check_fatigue = 0 nace.blade_number=rotor.nBlades nace.cut_in=rotor.control.Vin #cut-in m/s nace.cut_out=rotor.control.Vout #cut-out m/s nace.Vrated=rotor.ratedConditions.V #rated windspeed m/s nace.weibull_k = WeibullShapeFactor # windepeed distribution shape parameter # windspeed distribution scale parameter nace.weibull_A = WeibullScale nace.T_life=20. #design life in years nace.IEC_Class_Letter = 'B' # length from hub center to main bearing, leave zero if unknown nace.L_rb = hubS.L_rb # NREL 5 MW Tower Variables nace.tower_top_diameter = 3.78 # m nace.run() if (Verbose==True): print '##################### Drive SE ############################' print "Estimate of Nacelle Component Sizes" print 'Low speed shaft: {0:8.1f} kg'.format(nace.lowSpeedShaft.mass) print 'Main bearings: {0:8.1f} kg'.format(\ nace.mainBearing.mass + nace.secondBearing.mass) print 'Gearbox: {0:8.1f} kg'.format(nace.gearbox.mass) print 'High speed shaft & brakes: {0:8.1f} kg'.format\ (nace.highSpeedSide.mass) print 'Generator: {0:8.1f} kg'.format(nace.generator.mass) print 'Variable speed electronics: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.vs_electronics_mass) print 'Overall mainframe:{0:8.1f} kg'.format(\ nace.above_yaw_massAdder.mainframe_mass) print ' Bedplate: {0:8.1f} kg'.format(nace.bedplate.mass) print 'Electrical connections: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.electrical_mass) print 'HVAC system: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.hvac_mass ) print 'Nacelle cover: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.cover_mass) print 'Yaw system: {0:8.1f} kg'.format(nace.yawSystem.mass) print 'Overall nacelle: {0:8.1f} kg'.format(nace.nacelle_mass, \ nace.nacelle_cm[0], nace.nacelle_cm[1], nace.nacelle_cm[2], \ nace.nacelle_I[0], nace.nacelle_I[1], nace.nacelle_I[2]) print '#########################################################' ############################################################################ ### 4. Tower Mass # --- tower setup ------ from commonse.environment import PowerWind tower = set_as_top(TowerSE()) # ---- tower ------ tower.replace('wind1', PowerWind()) tower.replace('wind2', PowerWind()) # onshore (no waves) # --- geometry ---- tower.z_param = [0.0, HubHeight*0.5, HubHeight] TowerRatio = np.true_divide(HubHeight,ReferenceTowerHeight) tower.d_param = [6.0*TowerRatio, 4.935*TowerRatio, 3.87*TowerRatio] tower.t_param = [0.027*1.3*TowerRatio, 0.023*1.3*TowerRatio, \ 0.019*1.3*TowerRatio] n = 10 tower.z_full = np.linspace(0.0, HubHeight, n) tower.L_reinforced = 15.0*np.ones(n) # [m] buckling length tower.theta_stress = 0.0*np.ones(n) tower.yaw = 0.0 # --- material props --- tower.E = 210e9*np.ones(n) tower.G = 80.8e9*np.ones(n) tower.rho = 8500.0*np.ones(n) tower.sigma_y = 450.0e6*np.ones(n) # --- spring reaction data. Use float('inf') for rigid constraints. --- tower.kidx = [0] # applied at base tower.kx = [float('inf')] tower.ky = [float('inf')] tower.kz = [float('inf')] tower.ktx = [float('inf')] tower.kty = [float('inf')] tower.ktz = [float('inf')] # --- extra mass ---- tower.midx = [n-1] # RNA mass at top tower.m = [0.8] tower.mIxx = [1.14930678e+08] tower.mIyy = [2.20354030e+07] tower.mIzz = [1.87597425e+07] tower.mIxy = [0.00000000e+00] tower.mIxz = [5.03710467e+05] tower.mIyz = [0.00000000e+00] tower.mrhox = [-1.13197635] tower.mrhoy = [0.] tower.mrhoz = [0.50875268] tower.addGravityLoadForExtraMass = False # ----------- # --- wind --- tower.wind_zref = 90.0 tower.wind_z0 = 0.0 tower.wind1.shearExp = 0.14 tower.wind2.shearExp = 0.14 # --------------- # # --- loading case 1: max Thrust --- tower.wind_Uref1 = 11.73732 tower.plidx1 = [n-1] # at tower top tower.Fx1 = [0.19620519] tower.Fy1 = [0.] tower.Fz1 = [-2914124.84400512] tower.Mxx1 = [3963732.76208099] tower.Myy1 = [-2275104.79420872] tower.Mzz1 = [-346781.68192839] # # --------------- # # --- loading case 2: max wind speed --- tower.wind_Uref2 = 70.0 tower.plidx1 = [n-1] # at tower top tower.Fx1 = [930198.60063279] tower.Fy1 = [0.] tower.Fz1 = [-2883106.12368949] tower.Mxx1 = [-1683669.22411597] tower.Myy1 = [-2522475.34625363] tower.Mzz1 = [147301.97023764] # # --------------- # # --- run --- tower.run() if (Verbose==True): print '##################### Tower SE ##########################' print 'mass (kg) =', tower.mass print 'f1 (Hz) =', tower.f1 print 'f2 (Hz) =', tower.f2 print 'top_deflection1 (m) =', tower.top_deflection1 print 'top_deflection2 (m) =', tower.top_deflection2 print '#########################################################' ############################################################################ ## 5. Turbine captial costs analysis turbine = Turbine_CostsSE() # NREL 5 MW turbine component masses based on Sunderland model approach # Rotor # inline with the windpact estimates turbine.blade_mass = rotor.mass_one_blade turbine.hub_mass = hubS.hub.mass turbine.pitch_system_mass = hubS.pitchSystem.mass turbine.spinner_mass = hubS.spinner.mass # Drivetrain and Nacelle turbine.low_speed_shaft_mass = nace.lowSpeedShaft.mass turbine.main_bearing_mass=nace.mainBearing.mass turbine.second_bearing_mass = nace.secondBearing.mass turbine.gearbox_mass = nace.gearbox.mass turbine.high_speed_side_mass = nace.highSpeedSide.mass turbine.generator_mass = nace.generator.mass turbine.bedplate_mass = nace.bedplate.mass turbine.yaw_system_mass = nace.yawSystem.mass # Tower turbine.tower_mass = tower.mass*0.5 # Additional non-mass cost model input variables turbine.machine_rating = hubS.machine_rating/1000 turbine.advanced = False turbine.blade_number = rotor.nBlades turbine.drivetrain_design = 'geared' turbine.crane = False turbine.offshore = False # Target year for analysis results turbine.year = 2010 turbine.month = 12 turbine.run() if (Verbose==True): print '##################### TurbinePrice SE ####################' print "Overall rotor cost with 3 advanced blades is ${0:.2f} USD"\ .format(turbine.rotorCC.cost) print "Blade cost is ${0:.2f} USD".format(turbine.rotorCC.bladeCC.cost) print "Hub cost is ${0:.2f} USD".format(turbine.rotorCC.hubCC.cost) print "Pitch system cost is ${0:.2f} USD".format(turbine.rotorCC.pitchSysCC.cost) print "Spinner cost is ${0:.2f} USD".format(turbine.rotorCC.spinnerCC.cost) print print "Overall nacelle cost is ${0:.2f} USD".format(turbine.nacelleCC.cost) print "LSS cost is ${0:.2f} USD".format(turbine.nacelleCC.lssCC.cost) print "Main bearings cost is ${0:.2f} USD".format(turbine.nacelleCC.bearingsCC.cost) print "Gearbox cost is ${0:.2f} USD".format(turbine.nacelleCC.gearboxCC.cost) print "Hight speed side cost is ${0:.2f} USD".format(turbine.nacelleCC.hssCC.cost) print "Generator cost is ${0:.2f} USD".format(turbine.nacelleCC.generatorCC.cost) print "Bedplate cost is ${0:.2f} USD".format(turbine.nacelleCC.bedplateCC.cost) print "Yaw system cost is ${0:.2f} USD".format(turbine.nacelleCC.yawSysCC.cost) print print "Tower cost is ${0:.2f} USD".format(turbine.towerCC.cost) print print "The overall turbine cost is ${0:.2f} USD".format(turbine.turbine_cost) print '#########################################################' ############################################################################ ## 6. Operating Expenses # A simple test of nrel_csm_bos model bos = bos_csm_assembly() # Set input parameters bos = bos_csm_assembly() bos.machine_rating = hubS.machine_rating/1000 bos.rotor_diameter = rotor.diameter bos.turbine_cost = turbine.turbine_cost bos.hub_height = HubHeight bos.turbine_number = 1 bos.sea_depth = 0 bos.year = 2009 bos.month = 12 bos.multiplier = 1.0 bos.run() om = opex_csm_assembly() om.machine_rating = rotor.control.ratedPower/1000 # Need to manipulate input or underlying component will not execute om.net_aep = AEP*10e4 om.sea_depth = 0 om.year = 2009 om.month = 12 om.turbine_number = 100 om.run() if (Verbose==True): print '##################### Operating Costs ####################' print "BOS cost per turbine: ${0:.2f} USD".format(bos.bos_costs / \ bos.turbine_number) print "Average annual operational expenditures" print "OPEX on shore with 100 turbines ${:.2f}: USD".format(\ om.avg_annual_opex) print "Preventative OPEX by turbine: ${:.2f} USD".format(\ om.opex_breakdown.preventative_opex / om.turbine_number) print "Corrective OPEX by turbine: ${:.2f} USD".format(\ om.opex_breakdown.corrective_opex / om.turbine_number) print "Land Lease OPEX by turbine: ${:.2f} USD".format(\ om.opex_breakdown.lease_opex / om.turbine_number) print '#########################################################' CapitalCost = turbine.turbine_cost + bos.bos_costs / bos.turbine_number OperatingCost = om.opex_breakdown.preventative_opex / om.turbine_number + \ om.opex_breakdown.lease_opex / om.turbine_number + \ om.opex_breakdown.corrective_opex / om.turbine_number LCOE = ComputeLCOE(AEP, CapitalCost, OperatingCost, DiscountRate, Years) print '######################***********************###################' print "Levelized Cost of Energy over %d years \ is $%f/kWH" %(Years,LCOE/1000) print '######################***********************###################' return LCOE/1000
0.0, 0.00492790457512, 0.00652942887106, 0.00813095316699, 0.00983257273154, 0.0114340970275, 0.0130356213234, 0.02222276, 0.024446481932, 0.026048006228, 0.06666667, 0.089508406455, 0.11111057, 0.146462614229, 0.16666667, 0.195309105255, 0.23333333, 0.276686558545, 0.3, 0.333640766319, 0.36666667, 0.400404310407, 0.43333333, 0.5, 0.520818918408, 0.56666667, 0.602196371696, 0.63333333, 0.667358391486, 0.683573824984, 0.7, 0.73242031601, 0.76666667, 0.83333333, 0.88888943, 0.93333333, 0.97777724, 1.0 ]) # (Int): first idx in r_aero_unit of non-cylindrical section, # constant twist inboard of here rotor.idx_cylinder_aero = 3 # (Int): first idx in r_str_unit of non-cylindrical section rotor.idx_cylinder_str = 14 # (Float): hub location as fraction of radius rotor.hubFraction = 0.025 # ------------------ # === blade geometry === # (Array): new aerodynamic grid on unit radius rotor.r_aero = np.array([ 0.02222276, 0.06666667, 0.11111057, 0.2, 0.23333333, 0.3, 0.36666667, 0.43333333, 0.5, 0.56666667, 0.63333333, 0.64, 0.7, 0.83333333, 0.88888943, 0.93333333, 0.97777724 ]) # (Float): location of max chord on unit radius rotor.r_max_chord = 0.23577
def EvaluateLCOE(BladeLength, HubHeight, MaximumRotSpeed, Verbose=False): ############################################################################ # Define baseline paremeters used for scaling ReferenceBladeLength = 35 ReferenceTowerHeight = 95 WindReferenceHeight = 50 WindReferenceMeanVelocity = 3 WeibullShapeFactor = 2.0 ShearFactor = 0.25 RatedPower = 1.5e6 # Years used for analysis Years = 25 DiscountRate = 0.08 ############################################################################ ############################################################################ ### 1. Aerodynamic and structural performance using RotorSE rotor = RotorSE() # ------------------- # === blade grid === # (Array): initial aerodynamic grid on unit radius rotor.initial_aero_grid = np.array([0.02222276, 0.06666667, 0.11111057, \ 0.16666667, 0.23333333, 0.3, 0.36666667, 0.43333333, 0.5, 0.56666667, \ 0.63333333, 0.7, 0.76666667, 0.83333333, 0.88888943, 0.93333333, \ 0.97777724]) # (Array): initial structural grid on unit radius rotor.initial_str_grid = np.array([ 0.0, 0.00492790457512, 0.00652942887106, 0.00813095316699, 0.00983257273154, 0.0114340970275, 0.0130356213234, 0.02222276, 0.024446481932, 0.026048006228, 0.06666667, 0.089508406455, 0.11111057, 0.146462614229, 0.16666667, 0.195309105255, 0.23333333, 0.276686558545, 0.3, 0.333640766319, 0.36666667, 0.400404310407, 0.43333333, 0.5, 0.520818918408, 0.56666667, 0.602196371696, 0.63333333, 0.667358391486, 0.683573824984, 0.7, 0.73242031601, 0.76666667, 0.83333333, 0.88888943, 0.93333333, 0.97777724, 1.0 ]) # (Int): first idx in r_aero_unit of non-cylindrical section, # constant twist inboard of here rotor.idx_cylinder_aero = 3 # (Int): first idx in r_str_unit of non-cylindrical section rotor.idx_cylinder_str = 14 # (Float): hub location as fraction of radius rotor.hubFraction = 0.025 # ------------------ # === blade geometry === # (Array): new aerodynamic grid on unit radius rotor.r_aero = np.array([ 0.02222276, 0.06666667, 0.11111057, 0.2, 0.23333333, 0.3, 0.36666667, 0.43333333, 0.5, 0.56666667, 0.63333333, 0.64, 0.7, 0.83333333, 0.88888943, 0.93333333, 0.97777724 ]) # (Float): location of max chord on unit radius rotor.r_max_chord = 0.23577 # (Array, m): chord at control points. defined at hub, then at linearly spaced # locations from r_max_chord to tip ReferenceChord = [3.2612, 4.5709, 3.3178, 1.4621] rotor.chord_sub = [x * np.true_divide(BladeLength,ReferenceBladeLength) \ for x in ReferenceChord] # (Array, deg): twist at control points. defined at linearly spaced locations # from r[idx_cylinder] to tip rotor.theta_sub = [13.2783, 7.46036, 2.89317, -0.0878099] # (Array, m): precurve at control points. defined at same locations at chord, # starting at 2nd control point (root must be zero precurve) rotor.precurve_sub = [0.0, 0.0, 0.0] # (Array, m): adjustment to precurve to account for curvature from loading rotor.delta_precurve_sub = [0.0, 0.0, 0.0] # (Array, m): spar cap thickness parameters rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398] # (Array, m): trailing-edge thickness parameters rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569] # (Float, m): blade length (if not precurved or swept) # otherwise length of blade before curvature rotor.bladeLength = BladeLength # (Float, m): adjustment to blade length to account for curvature from # loading rotor.delta_bladeLength = 0.0 rotor.precone = 2.5 # (Float, deg): precone angle rotor.tilt = 5.0 # (Float, deg): shaft tilt rotor.yaw = 0.0 # (Float, deg): yaw error rotor.nBlades = 3 # (Int): number of blades # ------------------ # === airfoil files === basepath = os.path.join(os.path.dirname(\ os.path.realpath(__file__)), '5MW_AFFiles') # load all airfoils airfoil_types = [0] * 8 airfoil_types[0] = os.path.join(basepath, 'Cylinder1.dat') airfoil_types[1] = os.path.join(basepath, 'Cylinder2.dat') airfoil_types[2] = os.path.join(basepath, 'DU40_A17.dat') airfoil_types[3] = os.path.join(basepath, 'DU35_A17.dat') airfoil_types[4] = os.path.join(basepath, 'DU30_A17.dat') airfoil_types[5] = os.path.join(basepath, 'DU25_A17.dat') airfoil_types[6] = os.path.join(basepath, 'DU21_A17.dat') airfoil_types[7] = os.path.join(basepath, 'NACA64_A17.dat') # place at appropriate radial stations af_idx = [0, 0, 1, 2, 3, 3, 4, 5, 5, 6, 6, 7, 7, 7, 7, 7, 7] n = len(af_idx) af = [0] * n for i in range(n): af[i] = airfoil_types[af_idx[i]] rotor.airfoil_files = af # (List): names of airfoil file # ---------------------- # === atmosphere === rotor.rho = 1.225 # (Float, kg/m**3): density of air rotor.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air rotor.shearExp = 0.25 # (Float): shear exponent rotor.hubHt = HubHeight # (Float, m): hub height rotor.turbine_class = 'I' # (Enum): IEC turbine class rotor.turbulence_class = 'B' # (Enum): IEC turbulence class class rotor.cdf_reference_height_wind_speed = 30.0 rotor.g = 9.81 # (Float, m/s**2): acceleration of gravity # ---------------------- # === control === rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed rotor.control.Vout = 26.0 # (Float, m/s): cut-out wind speed rotor.control.ratedPower = RatedPower # (Float, W): rated power # (Float, rpm): minimum allowed rotor rotation speed # (Float, rpm): maximum allowed rotor rotation speed rotor.control.minOmega = 0.0 rotor.control.maxOmega = MaximumRotSpeed # (Float): tip-speed ratio in Region 2 (should be optimized externally) rotor.control.tsr = 7 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines) rotor.control.pitch = 0.0 # (Float, deg): worst-case pitch at survival wind condition rotor.pitch_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition rotor.azimuth_extreme = 0.0 # (Float): fraction of rated speed at which the deflection is assumed to # representative throughout the power curve calculation rotor.VfactorPC = 0.7 # ---------------------- # === aero and structural analysis options === # (Int): number of sectors to divide rotor face into in computing thrust and power rotor.nSector = 4 # (Int): number of points to evaluate aero analysis at rotor.npts_coarse_power_curve = 20 # (Int): number of points to use in fitting spline to power curve rotor.npts_spline_power_curve = 200 # (Float): availability and other losses (soiling, array, etc.) rotor.AEP_loss_factor = 1.0 rotor.drivetrainType = 'geared' # (Enum) # (Int): number of natural frequencies to compute rotor.nF = 5 # (Float): a dynamic amplification factor to adjust the static deflection # calculation rotor.dynamic_amplication_tip_deflection = 1.35 # ---------------------- # === materials and composite layup === basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), \ '5MW_PrecompFiles') materials = Orthotropic2DMaterial.listFromPreCompFile(os.path.join(basepath,\ 'materials.inp')) ncomp = len(rotor.initial_str_grid) upper = [0] * ncomp lower = [0] * ncomp webs = [0] * ncomp profile = [0] * ncomp # (Array): array of leading-edge positions from a reference blade axis # (usually blade pitch axis). locations are normalized by the local chord # length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference # axis. positive in -x direction for airfoil-aligned coordinate system rotor.leLoc = np.array([ 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.498, 0.497, 0.465, 0.447, 0.43, 0.411, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4 ]) # (Array): index of sector for spar (PreComp definition of sector) rotor.sector_idx_strain_spar = [2] * ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector) rotor.sector_idx_strain_te = [3] * ncomp web1 = np.array([ -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.4114, 0.4102, 0.4094, 0.3876, 0.3755, 0.3639, 0.345, 0.3342, 0.3313, 0.3274, 0.323, 0.3206, 0.3172, 0.3138, 0.3104, 0.307, 0.3003, 0.2982, 0.2935, 0.2899, 0.2867, 0.2833, 0.2817, 0.2799, 0.2767, 0.2731, 0.2664, 0.2607, 0.2562, 0.1886, -1.0 ]) web2 = np.array([ -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.5886, 0.5868, 0.5854, 0.5508, 0.5315, 0.5131, 0.4831, 0.4658, 0.4687, 0.4726, 0.477, 0.4794, 0.4828, 0.4862, 0.4896, 0.493, 0.4997, 0.5018, 0.5065, 0.5101, 0.5133, 0.5167, 0.5183, 0.5201, 0.5233, 0.5269, 0.5336, 0.5393, 0.5438, 0.6114, -1.0 ]) web3 = np.array([ -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0 ]) # (Array, m): chord distribution for reference section, thickness of structural # layup scaled with reference thickness (fixed t/c for this case) rotor.chord_str_ref = np.array([3.2612, 3.3100915356, 3.32587052924, 3.34159388653, 3.35823798667, 3.37384375335, 3.38939112914, 3.4774055542, 3.49839685, 3.51343645709, 3.87017220335, 4.04645623801, 4.19408216643, 4.47641008477, 4.55844487985, 4.57383098262, 4.57285771934, 4.51914315648, 4.47677655262, 4.40075650022, 4.31069949379, 4.20483735936, 4.08985563932, 3.82931757126, 3.74220276467, 3.54415796922, 3.38732428502, 3.24931446473, 3.23421422609, 3.22701537997, 3.21972125648, 3.08979310611, 2.95152261813, 2.330753331, 2.05553464181, 1.82577817774, 1.5860853279, 1.4621])* \ np.true_divide(BladeLength,ReferenceBladeLength) for i in range(ncomp): webLoc = [] if web1[i] != -1: webLoc.append(web1[i]) if web2[i] != -1: webLoc.append(web2[i]) if web3[i] != -1: webLoc.append(web3[i]) upper[i], lower[i], webs[i] = CompositeSection.initFromPreCompLayupFile\ (os.path.join(basepath, 'layup_' + str(i+1) + '.inp'), webLoc, materials) profile[i] = Profile.initFromPreCompFile(os.path.join(basepath, 'shape_' \ + str(i+1) + '.inp')) # (List): list of all Orthotropic2DMaterial objects used in # defining the geometry rotor.materials = materials # (List): list of CompositeSection objections defining the properties for # upper surface rotor.upperCS = upper # (List): list of CompositeSection objections defining the properties for # lower surface rotor.lowerCS = lower # (List): list of CompositeSection objections defining the properties for # shear webs rotor.websCS = webs # (List): airfoil shape at each radial position rotor.profile = profile # -------------------------------------- # === fatigue === # (Array): nondimensional radial locations of damage equivalent moments rotor.rstar_damage = np.array([ 0.000, 0.022, 0.067, 0.111, 0.167, 0.233, 0.300, 0.367, 0.433, 0.500, 0.567, 0.633, 0.700, 0.767, 0.833, 0.889, 0.933, 0.978 ]) # (Array, N*m): damage equivalent moments about blade c.s. x-direction rotor.Mxb_damage = 1e3 * np.array([ 2.3743E+003, 2.0834E+003, 1.8108E+003, 1.5705E+003, 1.3104E+003, 1.0488E+003, 8.2367E+002, 6.3407E+002, 4.7727E+002, 3.4804E+002, 2.4458E+002, 1.6339E+002, 1.0252E+002, 5.7842E+001, 2.7349E+001, 1.1262E+001, 3.8549E+000, 4.4738E-001 ]) # (Array, N*m): damage equivalent moments about blade c.s. y-direction rotor.Myb_damage = 1e3 * np.array([ 2.7732E+003, 2.8155E+003, 2.6004E+003, 2.3933E+003, 2.1371E+003, 1.8459E+003, 1.5582E+003, 1.2896E+003, 1.0427E+003, 8.2015E+002, 6.2449E+002, 4.5229E+002, 3.0658E+002, 1.8746E+002, 9.6475E+001, 4.2677E+001, 1.5409E+001, 1.8426E+000 ]) rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap # (Float): uptimate strain in trailing-edge panels, note that I am putting a # factor of two for the damage part only. rotor.strain_ult_te = 2500 * 1e-6 * 2 rotor.eta_damage = 1.35 * 1.3 * 1.0 # (Float): safety factor for fatigue rotor.m_damage = 10.0 # (Float): slope of S-N curve for fatigue analysis # (Float): number of cycles used in fatigue analysis rotor.N_damage = 365 * 24 * 3600 * 20.0 # ---------------- # from myutilities import plt # === run and outputs === rotor.run() # Evaluate AEP Using Lewis' Functions # Weibull Wind Parameters WindReferenceHeight = 50 WindReferenceMeanVelocity = 7.5 WeibullShapeFactor = 2.0 ShearFactor = 0.25 PowerCurve = rotor.P / 1e6 PowerCurveVelocity = rotor.V HubHeight = rotor.hubHt AEP,WeibullScale = CalculateAEPWeibull(PowerCurve,PowerCurveVelocity, HubHeight, \ BladeLength,WeibullShapeFactor, WindReferenceHeight, \ WindReferenceMeanVelocity, ShearFactor) NamePlateCapacity = EstimateCapacity(PowerCurve,PowerCurveVelocity, \ rotor.ratedConditions.V) # AEP At Constant 7.5m/s Wind used for benchmarking... #AEP = CalculateAEPConstantWind(PowerCurve, PowerCurveVelocity, 7.5) if (Verbose == True): print '################### ROTORSE ######################' print 'AEP = %d MWH' % (AEP) print 'NamePlateCapacity = %fMW' % (NamePlateCapacity) print 'diameter =', rotor.diameter print 'ratedConditions.V =', rotor.ratedConditions.V print 'ratedConditions.Omega =', rotor.ratedConditions.Omega print 'ratedConditions.pitch =', rotor.ratedConditions.pitch print 'mass_one_blade =', rotor.mass_one_blade print 'mass_all_blades =', rotor.mass_all_blades print 'I_all_blades =', rotor.I_all_blades print 'freq =', rotor.freq print 'tip_deflection =', rotor.tip_deflection print 'root_bending_moment =', rotor.root_bending_moment print '#########################################################' ############################################################################# ### 2. Hub Sizing # Specify hub parameters based off rotor # Load default hub model hubS = HubSE() hubS.rotor_diameter = rotor.Rtip * 2 # m hubS.blade_number = rotor.nBlades hubS.blade_root_diameter = rotor.chord_sub[0] * 1.25 hubS.L_rb = rotor.hubFraction * rotor.diameter hubS.MB1_location = np.array([-0.5, 0.0, 0.0]) hubS.machine_rating = rotor.control.ratedPower hubS.blade_mass = rotor.mass_one_blade hubS.rotor_bending_moment = rotor.root_bending_moment hubS.run() RotorTotalWeight = rotor.mass_all_blades + hubS.spinner.mass + \ hubS.hub.mass + hubS.pitchSystem.mass if (Verbose == True): print '##################### Hub SE ############################' print "Estimate of Hub Component Sizes:" print "Hub Components" print ' Hub: {0:8.1f} kg'.format(hubS.hub.mass) print ' Pitch system: {0:8.1f} kg'.format(hubS.pitchSystem.mass) print ' Nose cone: {0:8.1f} kg'.format(hubS.spinner.mass) print 'Rotor Total Weight = %d kg' % RotorTotalWeight print '#########################################################' ############################################################################ ### 3. Drive train + Nacelle Mass estimation nace = Drive4pt() nace.rotor_diameter = rotor.Rtip * 2 # m nace.rotor_speed = rotor.ratedConditions.Omega # #rpm m/s nace.machine_rating = hubS.machine_rating / 1000 nace.DrivetrainEfficiency = 0.95 # 6.35e6 #4365248.74 # Nm nace.rotor_torque = rotor.ratedConditions.Q nace.rotor_thrust = rotor.ratedConditions.T # N nace.rotor_mass = 0.0 #accounted for in F_z # kg nace.rotor_bending_moment_x = rotor.Mxyz_0[0] nace.rotor_bending_moment_y = rotor.Mxyz_0[1] nace.rotor_bending_moment_z = rotor.Mxyz_0[2] nace.rotor_force_x = rotor.Fxyz_0[0] # N nace.rotor_force_y = rotor.Fxyz_0[1] nace.rotor_force_z = rotor.Fxyz_0[2] # N # geared 3-stage Gearbox with induction generator machine nace.drivetrain_design = 'geared' nace.gear_ratio = 96.76 # 97:1 as listed in the 5 MW reference document nace.gear_configuration = 'eep' # epicyclic-epicyclic-parallel nace.crane = True # onboard crane present nace.shaft_angle = 5.0 #deg nace.shaft_ratio = 0.10 nace.Np = [3, 3, 1] nace.ratio_type = 'optimal' nace.shaft_type = 'normal' nace.uptower_transformer = False nace.shrink_disc_mass = 333.3 * nace.machine_rating / 1000.0 # estimated nace.mb1Type = 'CARB' nace.mb2Type = 'SRB' nace.flange_length = 0.5 #m nace.overhang = 5.0 nace.gearbox_cm = 0.1 nace.hss_length = 1.5 #0 if no fatigue check, 1 if parameterized fatigue check, #2 if known loads inputs nace.check_fatigue = 0 nace.blade_number = rotor.nBlades nace.cut_in = rotor.control.Vin #cut-in m/s nace.cut_out = rotor.control.Vout #cut-out m/s nace.Vrated = rotor.ratedConditions.V #rated windspeed m/s nace.weibull_k = WeibullShapeFactor # windepeed distribution shape parameter # windspeed distribution scale parameter nace.weibull_A = WeibullScale nace.T_life = 20. #design life in years nace.IEC_Class_Letter = 'B' # length from hub center to main bearing, leave zero if unknown nace.L_rb = hubS.L_rb # NREL 5 MW Tower Variables nace.tower_top_diameter = 3.78 # m nace.run() if (Verbose == True): print '##################### Drive SE ############################' print "Estimate of Nacelle Component Sizes" print 'Low speed shaft: {0:8.1f} kg'.format(nace.lowSpeedShaft.mass) print 'Main bearings: {0:8.1f} kg'.format(\ nace.mainBearing.mass + nace.secondBearing.mass) print 'Gearbox: {0:8.1f} kg'.format(nace.gearbox.mass) print 'High speed shaft & brakes: {0:8.1f} kg'.format\ (nace.highSpeedSide.mass) print 'Generator: {0:8.1f} kg'.format(nace.generator.mass) print 'Variable speed electronics: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.vs_electronics_mass) print 'Overall mainframe:{0:8.1f} kg'.format(\ nace.above_yaw_massAdder.mainframe_mass) print ' Bedplate: {0:8.1f} kg'.format(nace.bedplate.mass) print 'Electrical connections: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.electrical_mass) print 'HVAC system: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.hvac_mass ) print 'Nacelle cover: {0:8.1f} kg'.format(\ nace.above_yaw_massAdder.cover_mass) print 'Yaw system: {0:8.1f} kg'.format(nace.yawSystem.mass) print 'Overall nacelle: {0:8.1f} kg'.format(nace.nacelle_mass, \ nace.nacelle_cm[0], nace.nacelle_cm[1], nace.nacelle_cm[2], \ nace.nacelle_I[0], nace.nacelle_I[1], nace.nacelle_I[2]) print '#########################################################' ############################################################################ ### 4. Tower Mass # --- tower setup ------ from commonse.environment import PowerWind tower = set_as_top(TowerSE()) # ---- tower ------ tower.replace('wind1', PowerWind()) tower.replace('wind2', PowerWind()) # onshore (no waves) # --- geometry ---- tower.z_param = [0.0, HubHeight * 0.5, HubHeight] TowerRatio = np.true_divide(HubHeight, ReferenceTowerHeight) tower.d_param = [6.0 * TowerRatio, 4.935 * TowerRatio, 3.87 * TowerRatio] tower.t_param = [0.027*1.3*TowerRatio, 0.023*1.3*TowerRatio, \ 0.019*1.3*TowerRatio] n = 10 tower.z_full = np.linspace(0.0, HubHeight, n) tower.L_reinforced = 15.0 * np.ones(n) # [m] buckling length tower.theta_stress = 0.0 * np.ones(n) tower.yaw = 0.0 # --- material props --- tower.E = 210e9 * np.ones(n) tower.G = 80.8e9 * np.ones(n) tower.rho = 8500.0 * np.ones(n) tower.sigma_y = 450.0e6 * np.ones(n) # --- spring reaction data. Use float('inf') for rigid constraints. --- tower.kidx = [0] # applied at base tower.kx = [float('inf')] tower.ky = [float('inf')] tower.kz = [float('inf')] tower.ktx = [float('inf')] tower.kty = [float('inf')] tower.ktz = [float('inf')] # --- extra mass ---- tower.midx = [n - 1] # RNA mass at top tower.m = [0.8] tower.mIxx = [1.14930678e+08] tower.mIyy = [2.20354030e+07] tower.mIzz = [1.87597425e+07] tower.mIxy = [0.00000000e+00] tower.mIxz = [5.03710467e+05] tower.mIyz = [0.00000000e+00] tower.mrhox = [-1.13197635] tower.mrhoy = [0.] tower.mrhoz = [0.50875268] tower.addGravityLoadForExtraMass = False # ----------- # --- wind --- tower.wind_zref = 90.0 tower.wind_z0 = 0.0 tower.wind1.shearExp = 0.14 tower.wind2.shearExp = 0.14 # --------------- # # --- loading case 1: max Thrust --- tower.wind_Uref1 = 11.73732 tower.plidx1 = [n - 1] # at tower top tower.Fx1 = [0.19620519] tower.Fy1 = [0.] tower.Fz1 = [-2914124.84400512] tower.Mxx1 = [3963732.76208099] tower.Myy1 = [-2275104.79420872] tower.Mzz1 = [-346781.68192839] # # --------------- # # --- loading case 2: max wind speed --- tower.wind_Uref2 = 70.0 tower.plidx1 = [n - 1] # at tower top tower.Fx1 = [930198.60063279] tower.Fy1 = [0.] tower.Fz1 = [-2883106.12368949] tower.Mxx1 = [-1683669.22411597] tower.Myy1 = [-2522475.34625363] tower.Mzz1 = [147301.97023764] # # --------------- # # --- run --- tower.run() if (Verbose == True): print '##################### Tower SE ##########################' print 'mass (kg) =', tower.mass print 'f1 (Hz) =', tower.f1 print 'f2 (Hz) =', tower.f2 print 'top_deflection1 (m) =', tower.top_deflection1 print 'top_deflection2 (m) =', tower.top_deflection2 print '#########################################################' ############################################################################ ## 5. Turbine captial costs analysis turbine = Turbine_CostsSE() # NREL 5 MW turbine component masses based on Sunderland model approach # Rotor # inline with the windpact estimates turbine.blade_mass = rotor.mass_one_blade turbine.hub_mass = hubS.hub.mass turbine.pitch_system_mass = hubS.pitchSystem.mass turbine.spinner_mass = hubS.spinner.mass # Drivetrain and Nacelle turbine.low_speed_shaft_mass = nace.lowSpeedShaft.mass turbine.main_bearing_mass = nace.mainBearing.mass turbine.second_bearing_mass = nace.secondBearing.mass turbine.gearbox_mass = nace.gearbox.mass turbine.high_speed_side_mass = nace.highSpeedSide.mass turbine.generator_mass = nace.generator.mass turbine.bedplate_mass = nace.bedplate.mass turbine.yaw_system_mass = nace.yawSystem.mass # Tower turbine.tower_mass = tower.mass * 0.5 # Additional non-mass cost model input variables turbine.machine_rating = hubS.machine_rating / 1000 turbine.advanced = False turbine.blade_number = rotor.nBlades turbine.drivetrain_design = 'geared' turbine.crane = False turbine.offshore = False # Target year for analysis results turbine.year = 2010 turbine.month = 12 turbine.run() if (Verbose == True): print '##################### TurbinePrice SE ####################' print "Overall rotor cost with 3 advanced blades is ${0:.2f} USD"\ .format(turbine.rotorCC.cost) print "Blade cost is ${0:.2f} USD".format(turbine.rotorCC.bladeCC.cost) print "Hub cost is ${0:.2f} USD".format(turbine.rotorCC.hubCC.cost) print "Pitch system cost is ${0:.2f} USD".format( turbine.rotorCC.pitchSysCC.cost) print "Spinner cost is ${0:.2f} USD".format( turbine.rotorCC.spinnerCC.cost) print print "Overall nacelle cost is ${0:.2f} USD".format( turbine.nacelleCC.cost) print "LSS cost is ${0:.2f} USD".format(turbine.nacelleCC.lssCC.cost) print "Main bearings cost is ${0:.2f} USD".format( turbine.nacelleCC.bearingsCC.cost) print "Gearbox cost is ${0:.2f} USD".format( turbine.nacelleCC.gearboxCC.cost) print "Hight speed side cost is ${0:.2f} USD".format( turbine.nacelleCC.hssCC.cost) print "Generator cost is ${0:.2f} USD".format( turbine.nacelleCC.generatorCC.cost) print "Bedplate cost is ${0:.2f} USD".format( turbine.nacelleCC.bedplateCC.cost) print "Yaw system cost is ${0:.2f} USD".format( turbine.nacelleCC.yawSysCC.cost) print print "Tower cost is ${0:.2f} USD".format(turbine.towerCC.cost) print print "The overall turbine cost is ${0:.2f} USD".format( turbine.turbine_cost) print '#########################################################' ############################################################################ ## 6. Operating Expenses # A simple test of nrel_csm_bos model bos = bos_csm_assembly() # Set input parameters bos = bos_csm_assembly() bos.machine_rating = hubS.machine_rating / 1000 bos.rotor_diameter = rotor.diameter bos.turbine_cost = turbine.turbine_cost bos.hub_height = HubHeight bos.turbine_number = 1 bos.sea_depth = 0 bos.year = 2009 bos.month = 12 bos.multiplier = 1.0 bos.run() om = opex_csm_assembly() om.machine_rating = rotor.control.ratedPower / 1000 # Need to manipulate input or underlying component will not execute om.net_aep = AEP * 10e4 om.sea_depth = 0 om.year = 2009 om.month = 12 om.turbine_number = 100 om.run() if (Verbose == True): print '##################### Operating Costs ####################' print "BOS cost per turbine: ${0:.2f} USD".format(bos.bos_costs / \ bos.turbine_number) print "Average annual operational expenditures" print "OPEX on shore with 100 turbines ${:.2f}: USD".format(\ om.avg_annual_opex) print "Preventative OPEX by turbine: ${:.2f} USD".format(\ om.opex_breakdown.preventative_opex / om.turbine_number) print "Corrective OPEX by turbine: ${:.2f} USD".format(\ om.opex_breakdown.corrective_opex / om.turbine_number) print "Land Lease OPEX by turbine: ${:.2f} USD".format(\ om.opex_breakdown.lease_opex / om.turbine_number) print '#########################################################' CapitalCost = turbine.turbine_cost + bos.bos_costs / bos.turbine_number OperatingCost = om.opex_breakdown.preventative_opex / om.turbine_number + \ om.opex_breakdown.lease_opex / om.turbine_number + \ om.opex_breakdown.corrective_opex / om.turbine_number LCOE = ComputeLCOE(AEP, CapitalCost, OperatingCost, DiscountRate, Years) print '######################***********************###################' print "Levelized Cost of Energy over %d years \ is $%f/kWH" % (Years, LCOE / 1000) print '######################***********************###################' return LCOE / 1000