def test3(self): pw = PowerWind() pw.Uref = 10.0 pw.zref = 100.0 pw.z0 = 0.0 pw.z = np.linspace(-10.0, 90.0, 20) pw.shearExp = 0.2 pw.betaWind = 5.0 names, errors = check_gradient(pw) tol = 1e-6 for name, err in zip(names, errors): try: self.assertLessEqual(err, tol) except AssertionError, e: print '*** error in:', name raise e
def setUp(self): z = np.linspace(0.0, 100.0, 20) nPoints = len(z) Uref = 10.0 zref = 100.0 z0 = 0.001 #Fails when z0 = 0, What to do here? shearExp = 0.2 betaWind = 0.0 prob = Problem() root = prob.root = Group() root.add('p1', IndepVarComp('z', z)) root.add('p2', IndepVarComp('zref', zref)) root.add('p3', IndepVarComp('Uref', Uref)) root.add('p', PowerWind(nPoints)) root.connect('p1.z', 'p.z') root.connect('p2.zref', 'p.zref') root.connect('p3.Uref', 'p.Uref') prob.driver.add_objective('p.U', scaler=1E-6) prob.driver.add_desvar('p1.z', lower=np.ones(nPoints), upper=np.ones(nPoints) * 1000, scaler=1E-6) prob.driver.add_desvar('p2.zref', lower=0, upper=1000, scaler=1E-6) prob.driver.add_desvar('p3.Uref', lower=0, upper=1000, scaler=1E-6) prob.setup() prob['p.z0'] = z0 prob['p.shearExp'] = shearExp prob['p.betaWind'] = betaWind prob.run() print prob['p.U'] self.J = prob.check_total_derivatives(out_stream=None)
def test1(self): pw = PowerWind() pw.Uref = 10.0 pw.zref = 100.0 pw.z0 = 0.0 pw.z = np.linspace(0.0, 100.0, 20) pw.shearExp = 0.2 pw.betaWind = 0.0 names, errors = check_gradient(pw) tol = 1e-6 for name, err in zip(names, errors): if name == 'd_U[0] / d_z[0]': continue # the derivative at z==0 is a discontinuity. this node must not move in the optimization try: self.assertLessEqual(err, tol) except AssertionError, e: print '*** error in:', name raise e
def test3(self): pw = PowerWind() pw.Uref = 10.0 pw.zref = 100.0 pw.z0 = 0.0 pw.z = np.linspace(-10.0, 90.0, 20) pw.shearExp = 0.2 pw.betaWind = 5.0 names, errors = check_gradient(pw) tol = 1e-6 for name, err in zip(names, errors): try: self.assertLessEqual(err, tol) except AssertionError, e: print "*** error in:", name raise e
def test1(self): pw = PowerWind() pw.Uref = 10.0 pw.zref = 100.0 pw.z0 = 0.0 pw.z = np.linspace(0.0, 100.0, 20) pw.shearExp = 0.2 pw.betaWind = 0.0 names, errors = check_gradient(pw) tol = 1e-6 for name, err in zip(names, errors): if name == "d_U[0] / d_z[0]": continue # the derivative at z==0 is a discontinuity. this node must not move in the optimization try: self.assertLessEqual(err, tol) except AssertionError, e: print "*** error in:", name raise e
self.connect('gc.manufacturability', 'manufacturability') if __name__ == '__main__': optimize = False # --- 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, 43.8, 87.6] tower.d_param = [6.0, 4.935, 3.87] tower.t_param = [0.027*1.3, 0.023*1.3, 0.019*1.3] n = 15 tower.z_full = np.linspace(0.0, 87.6, n) tower.L_reinforced = 30.0*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)
def configure_nrel5mw_turbine(turbine, wind_class='I', sea_depth=0.0): """ Inputs: rotor = RotorSE() nacelle = DriveSE() tower = TowerSE() wind_class : str ('I', 'III', 'Offshore' - selected wind class for project) sea_depth : float (sea depth if an offshore wind plant) """ # === Turbine === turbine.rho = 1.225 # (Float, kg/m**3): density of air turbine.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air turbine.shear_exponent = 0.2 # (Float): shear exponent turbine.hub_height = 90.0 # (Float, m): hub height turbine.turbine_class = 'I' # (Enum): IEC turbine class turbine.turbulence_class = 'B' # (Enum): IEC turbulence class class turbine.cdf_reference_height_wind_speed = 90.0 # (Float): reference hub height for IEC wind speed (used in CDF calculation) turbine.g = 9.81 # (Float, m/s**2): acceleration of gravity # ====================== # === rotor === # --- blade grid --- turbine.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 aerodynamic grid on unit radius turbine.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 ]) # (Array): initial structural grid on unit radius turbine.rotor.idx_cylinder_aero = 3 # (Int): first idx in r_aero_unit of non-cylindrical section, constant twist inboard of here turbine.rotor.idx_cylinder_str = 14 # (Int): first idx in r_str_unit of non-cylindrical section turbine.rotor.hubFraction = 0.025 # (Float): hub location as fraction of radius # ------------------ # --- blade geometry --- turbine.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 ]) # (Array): new aerodynamic grid on unit radius turbine.rotor.r_max_chord = 0.23577 # (Float): location of max chord on unit radius turbine.rotor.chord_sub = [ 3.2612, 4.5709, 3.3178, 1.4621 ] # (Array, m): chord at control points. defined at hub, then at linearly spaced locations from r_max_chord to tip turbine.rotor.theta_sub = [ 13.2783, 7.46036, 2.89317, -0.0878099 ] # (Array, deg): twist at control points. defined at linearly spaced locations from r[idx_cylinder] to tip turbine.rotor.precurve_sub = [ 0.0, 0.0, 0.0 ] # (Array, m): precurve at control points. defined at same locations at chord, starting at 2nd control point (root must be zero precurve) turbine.rotor.delta_precurve_sub = [ 0.0, 0.0, 0.0 ] # (Array, m): adjustment to precurve to account for curvature from loading turbine.rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398 ] # (Array, m): spar cap thickness parameters turbine.rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569 ] # (Array, m): trailing-edge thickness parameters turbine.rotor.bladeLength = 61.5 # (Float, m): blade length (if not precurved or swept) otherwise length of blade before curvature turbine.rotor.delta_bladeLength = 0.0 # (Float, m): adjustment to blade length to account for curvature from loading turbine.rotor.precone = 2.5 # (Float, deg): precone angle turbine.rotor.tilt = 5.0 # (Float, deg): shaft tilt turbine.rotor.yaw = 0.0 # (Float, deg): yaw error turbine.rotor.nBlades = 3 # (Int): number of blades # ------------------ # --- airfoil files --- import rotorse #basepath = os.path.join('5MW_files', '5MW_AFFiles') basepath = os.path.join('..', 'reference_turbines', 'nrel5mw', 'airfoils') # 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]] turbine.rotor.airfoil_files = af # (List): names of airfoil file # ---------------------- # --- control --- turbine.rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed turbine.rotor.control.Vout = 25.0 # (Float, m/s): cut-out wind speed turbine.rotor.control.ratedPower = 5e6 # (Float, W): rated power turbine.rotor.control.minOmega = 0.0 # (Float, rpm): minimum allowed rotor rotation speed turbine.rotor.control.maxOmega = 12.0 # (Float, rpm): maximum allowed rotor rotation speed turbine.rotor.control.tsr = 7.55 # (Float): tip-speed ratio in Region 2 (should be optimized externally) turbine.rotor.control.pitch = 0.0 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines) turbine.rotor.pitch_extreme = 0.0 # (Float, deg): worst-case pitch at survival wind condition turbine.rotor.azimuth_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition turbine.rotor.VfactorPC = 0.7 # (Float): fraction of rated speed at which the deflection is assumed to representative throughout the power curve calculation # ---------------------- # --- aero and structural analysis options --- turbine.rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power turbine.rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at turbine.rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve turbine.rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.) turbine.rotor.drivetrainType = 'geared' # (Enum) turbine.rotor.nF = 5 # (Int): number of natural frequencies to compute turbine.rotor.dynamic_amplication_tip_deflection = 1.35 # (Float): a dynamic amplification factor to adjust the static deflection calculation # ---------------------- # --- materials and composite layup --- #basepath = os.path.join('5MW_files', '5MW_PrecompFiles') basepath = os.path.join('..', 'reference_turbines', 'nrel5mw', 'blade') materials = Orthotropic2DMaterial.listFromPreCompFile( os.path.join(basepath, 'materials.inp')) ncomp = len(turbine.rotor.initial_str_grid) upper = [0] * ncomp lower = [0] * ncomp webs = [0] * ncomp profile = [0] * ncomp turbine.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): 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 turbine.rotor.sector_idx_strain_spar = [ 2 ] * ncomp # (Array): index of sector for spar (PreComp definition of sector) turbine.rotor.sector_idx_strain_te = [ 3 ] * ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector) 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 ]) turbine.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 ] ) # (Array, m): chord distribution for reference section, thickness of structural layup scaled with reference thickness (fixed t/c for this case) 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')) turbine.rotor.materials = materials # (List): list of all Orthotropic2DMaterial objects used in defining the geometry turbine.rotor.upperCS = upper # (List): list of CompositeSection objections defining the properties for upper surface turbine.rotor.lowerCS = lower # (List): list of CompositeSection objections defining the properties for lower surface turbine.rotor.websCS = webs # (List): list of CompositeSection objections defining the properties for shear webs turbine.rotor.profile = profile # (List): airfoil shape at each radial position # -------------------------------------- strain_ult_spar = 1.0e-2 strain_ult_te = 2500 * 1e-6 # --- fatigue --- turbine.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): nondimensional radial locations of damage equivalent moments turbine.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. x-direction turbine.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 ]) # (Array, N*m): damage equivalent moments about blade c.s. y-direction turbine.rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap turbine.rotor.strain_ult_te = 2500 * 1e-6 * 2 # (Float): uptimate strain in trailing-edge panels, note that I am putting a factor of two for the damage part only. turbine.rotor.eta_damage = 1.35 * 1.3 * 1.0 # (Float): safety factor for fatigue turbine.rotor.m_damage = 10.0 # (Float): slope of S-N curve for fatigue analysis turbine.rotor.N_damage = 365 * 24 * 3600 * 20.0 # (Float): number of cycles used in fatigue analysis TODO: make function of rotation speed # ---------------- # ================= # === nacelle ====== turbine.nacelle.L_ms = 1.0 # (Float, m): main shaft length downwind of main bearing in low-speed shaft turbine.nacelle.L_mb = 2.5 # (Float, m): main shaft length in low-speed shaft turbine.nacelle.h0_front = 1.7 # (Float, m): height of Ibeam in bedplate front turbine.nacelle.h0_rear = 1.35 # (Float, m): height of Ibeam in bedplate rear turbine.nacelle.drivetrain_design = 'geared' turbine.nacelle.crane = True # (Bool): flag for presence of crane turbine.nacelle.bevel = 0 # (Int): Flag for the presence of a bevel stage - 1 if present, 0 if not turbine.nacelle.gear_configuration = 'eep' # (Str): tring that represents the configuration of the gearbox (stage number and types) turbine.nacelle.Np = [3, 3, 1] # (Array): number of planets in each stage turbine.nacelle.ratio_type = 'optimal' # (Str): optimal or empirical stage ratios turbine.nacelle.shaft_type = 'normal' # (Str): normal or short shaft length #turbine.nacelle.shaft_angle = 5.0 # (Float, deg): Angle of the LSS inclindation with respect to the horizontal turbine.nacelle.shaft_ratio = 0.10 # (Float): Ratio of inner diameter to outer diameter. Leave zero for solid LSS turbine.nacelle.carrier_mass = 8000.0 # estimated for 5 MW turbine.nacelle.mb1Type = 'CARB' # (Str): Main bearing type: CARB, TRB or SRB turbine.nacelle.mb2Type = 'SRB' # (Str): Second bearing type: CARB, TRB or SRB turbine.nacelle.yaw_motors_number = 8.0 # (Float): number of yaw motors turbine.nacelle.uptower_transformer = True turbine.nacelle.flange_length = 0.5 #m turbine.nacelle.gearbox_cm = 0.1 turbine.nacelle.hss_length = 1.5 turbine.nacelle.overhang = 5.0 #TODO - should come from turbine configuration level turbine.nacelle.check_fatigue = 0 #0 if no fatigue check, 1 if parameterized fatigue check, 2 if known loads inputs # TODO: should come from rotor (these are FAST outputs) turbine.nacelle.DrivetrainEfficiency = 0.95 #turbine.nacelle.rotor_bending_moment_x = 330770.0# Nm #turbine.nacelle.rotor_bending_moment_y = -16665000.0 # Nm #turbine.nacelle.rotor_bending_moment_z = 2896300.0 # Nm #turbine.nacelle.rotor_force_x = 599610.0 # N #turbine.nacelle.rotor_force_y = 186780.0 # N #turbine.nacelle.rotor_force_z = -842710.0 # N''' #turbine.nacelle.h0_rear = 1.35 # only used in drive smooth #turbine.nacelle.h0_front = 1.7 # ================= # === tower === # ---- tower ------ turbine.tower.replace('wind1', PowerWind()) turbine.tower.replace('wind2', PowerWind()) # onshore (no waves) if turbine.sea_depth <> 0.0: turbine.tower.replace('wave1', LinearWaves()) turbine.tower.replace('wave2', LinearWaves()) turbine.tower.wave1.Uc = 0.0 turbine.tower.wave1.hs = 8.0 * 1.86 turbine.tower.wave1.T = 10.0 turbine.tower.wave1.z_surface = 0.0 turbine.tower.wave1.z_floor = -sea_depth turbine.tower.wave1.g = 9.81 turbine.tower.wave1.betaWave = 0.0 turbine.tower.wave2.Uc = 0.0 turbine.tower.wave2.hs = 8.0 * 1.86 turbine.tower.wave2.T = 10.0 turbine.tower.wave2.z_surface = 0.0 turbine.tower.wave2.z_floor = -sea_depth turbine.tower.wave2.g = 9.81 turbine.tower.wave2.betaWave = 0.0 if turbine.sea_depth == 0.0: # --- geometry ---- #np.insert(turbine.tower.z_param,0,87.9) #np.insert(turbine.tower.z_param,0,43.8) #np.insert(turbine.tower.z_param,0,0.0) turbine.tower.z_param = [0.0, 43.8, 87.9] turbine.tower_d = [6.0, 4.935, 3.87] turbine.tower.t_param = [0.027 * 1.3, 0.023 * 1.3, 0.019 * 1.3] n = 15 turbine.tower.z_full = np.linspace(0.0, 87.6, n) turbine.tower.L_reinforced = 30.0 * np.ones(n) # [m] buckling length turbine.tower.theta_stress = 0.0 * np.ones(n) turbine.tower.yaw = 0.0 # --- material props --- turbine.tower.E = 210e9 * np.ones(n) turbine.tower.G = 80.8e9 * np.ones(n) turbine.tower.rho = 8500.0 * np.ones(n) turbine.tower.sigma_y = 450.0e6 * np.ones(n) else: # --- geometry ---- #np.insert(turbine.tower.z_param,0,87.9) #np.insert(turbine.tower.z_param,0,43.8) #np.insert(turbine.tower.z_param,0,0.0) #np.insert(turbine.tower.z_param,0,-20.0) turbine.tower.z_param = [-20.0, 0.0, 43.8, 87.9] turbine.tower_d = [6.0, 6.0, 4.935, 3.87] turbine.tower.t_param = [0.06, 0.027 * 1.3, 0.023 * 1.3, 0.019 * 1.3] n = 20 turbine.tower.z_full = np.linspace(-20, 87.6, n) turbine.tower.L_reinforced = 30.0 * np.ones(n) # [m] buckling length turbine.tower.theta_stress = 0.0 * np.ones(n) turbine.tower.yaw = 0.0 # --- material props --- turbine.tower.E = 210e9 * np.ones(n) turbine.tower.G = 80.8e9 * np.ones(n) turbine.tower.rho = 8500.0 * np.ones(n) turbine.tower.sigma_y = 450.0e6 * np.ones(n) # --- spring reaction data. Use float('inf') for rigid constraints. --- turbine.tower.kidx = [0] # applied at base turbine.tower.kx = [float('inf')] turbine.tower.ky = [float('inf')] turbine.tower.kz = [float('inf')] turbine.tower.ktx = [float('inf')] turbine.tower.kty = [float('inf')] turbine.tower.ktz = [float('inf')] # --- extra mass ---- turbine.tower.midx = [n - 1] # RNA mass at top turbine.tower.m = [285598.8] turbine.tower.mIxx = [1.14930678e+08] turbine.tower.mIyy = [2.20354030e+07] turbine.tower.mIzz = [1.87597425e+07] turbine.tower.mIxy = [0.00000000e+00] turbine.tower.mIxz = [5.03710467e+05] turbine.tower.mIyz = [0.00000000e+00] turbine.tower.mrhox = [-1.13197635] turbine.tower.mrhoy = [0.] turbine.tower.mrhoz = [0.50875268] turbine.tower.addGravityLoadForExtraMass = True # ----------- # --- wind --- #turbine.tower.wind_zref = 90.0 turbine.tower.wind_z0 = 0.0 turbine.tower.wind1.shearExp = 0.2 turbine.tower.wind2.shearExp = 0.2 # --------------- # if addGravityLoadForExtraMass=True be sure not to double count by adding those force here also # # --- loading case 1: max Thrust --- #turbine.tower.wind_Uref1 = 11.73732 turbine.tower.plidx1 = [n - 1] # at tower top turbine.tower.Fx1 = [1284744.19620519] turbine.tower.Fy1 = [0.] turbine.tower.Fz1 = [-2914124.84400512] turbine.tower.Mxx1 = [3963732.76208099] turbine.tower.Myy1 = [-2275104.79420872] turbine.tower.Mzz1 = [-346781.68192839] # # --------------- # # --- loading case 2: max wind speed --- #turbine.tower.wind_Uref2 = 70.0 turbine.tower.plidx2 = [n - 1] # at tower top turbine.tower.Fx2 = [930198.60063279] turbine.tower.Fy2 = [0.] turbine.tower.Fz2 = [-2883106.12368949] turbine.tower.Mxx2 = [-1683669.22411597] turbine.tower.Myy2 = [-2522475.34625363] turbine.tower.Mzz2 = [147301.97023764] # # --------------- # --- safety factors --- turbine.tower.gamma_f = 1.35 turbine.tower.gamma_m = 1.3 turbine.tower.gamma_n = 1.0 turbine.tower.gamma_b = 1.1 # --------------- # --- fatigue --- turbine.tower.z_DEL = np.array([ 0.000, 1.327, 3.982, 6.636, 9.291, 11.945, 14.600, 17.255, 19.909, 22.564, 25.218, 27.873, 30.527, 33.182, 35.836, 38.491, 41.145, 43.800, 46.455, 49.109, 51.764, 54.418, 57.073, 59.727, 62.382, 65.036, 67.691, 70.345, 73.000, 75.655, 78.309, 80.964, 83.618, 86.273, 87.600 ]) turbine.tower.M_DEL = 1e3 * np.array([ 8.2940E+003, 8.1518E+003, 7.8831E+003, 7.6099E+003, 7.3359E+003, 7.0577E+003, 6.7821E+003, 6.5119E+003, 6.2391E+003, 5.9707E+003, 5.7070E+003, 5.4500E+003, 5.2015E+003, 4.9588E+003, 4.7202E+003, 4.4884E+003, 4.2577E+003, 4.0246E+003, 3.7942E+003, 3.5664E+003, 3.3406E+003, 3.1184E+003, 2.8977E+003, 2.6811E+003, 2.4719E+003, 2.2663E+003, 2.0673E+003, 1.8769E+003, 1.7017E+003, 1.5479E+003, 1.4207E+003, 1.3304E+003, 1.2780E+003, 1.2673E+003, 1.2761E+003 ]) turbine.tower.gamma_fatigue = 1.35 * 1.3 * 1.0 turbine.tower.life = 20.0 turbine.tower.m_SN = 4 # --------------- # --- constraints --- turbine.tower.min_d_to_t = 120.0 turbine.tower.min_taper = 0.4 # --------------- # ==== Other options if wind_class == 'I': turbine.rotor.turbine_class = 'I' elif wind_class == 'III': turbine.rotor.turbine_class = 'III' # for fatigue based analysis of class III wind turbine turbine.tower.M_DEL = 1.028713178 * 1e3 * np.array([ 7.8792E+003, 7.7507E+003, 7.4918E+003, 7.2389E+003, 6.9815E+003, 6.7262E+003, 6.4730E+003, 6.2174E+003, 5.9615E+003, 5.7073E+003, 5.4591E+003, 5.2141E+003, 4.9741E+003, 4.7399E+003, 4.5117E+003, 4.2840E+003, 4.0606E+003, 3.8360E+003, 3.6118E+003, 3.3911E+003, 3.1723E+003, 2.9568E+003, 2.7391E+003, 2.5294E+003, 2.3229E+003, 2.1246E+003, 1.9321E+003, 1.7475E+003, 1.5790E+003, 1.4286E+003, 1.3101E+003, 1.2257E+003, 1.1787E+003, 1.1727E+003, 1.1821E+003 ]) turbine.rotor.Mxb_damage = 1e3 * np.array([ 2.3617E+003, 2.0751E+003, 1.8051E+003, 1.5631E+003, 1.2994E+003, 1.0388E+003, 8.1384E+002, 6.2492E+002, 4.6916E+002, 3.4078E+002, 2.3916E+002, 1.5916E+002, 9.9752E+001, 5.6139E+001, 2.6492E+001, 1.0886E+001, 3.7210E+000, 4.3206E-001 ]) turbine.rotor.Myb_damage = 1e3 * np.array([ 2.5492E+003, 2.6261E+003, 2.4265E+003, 2.2308E+003, 1.9882E+003, 1.7184E+003, 1.4438E+003, 1.1925E+003, 9.6251E+002, 7.5564E+002, 5.7332E+002, 4.1435E+002, 2.8036E+002, 1.7106E+002, 8.7732E+001, 3.8678E+001, 1.3942E+001, 1.6600E+000 ]) elif wind_class == 'Offshore': turbine.rotor.turbine_class = 'I' # TODO: these should be specified at the turbine level and connected to other system inputs if turbine.sea_depth == 0.0: turbine.tower_d = [6.0, 4.935, 3.87] # (Array, m): diameters along tower else: turbine.tower_d = [6.0, 6.0, 4.935, 3.87] turbine.generator_speed = 1173.7 # (Float, rpm) # generator speed
def __init__(self, nSection, nFull): super(Column, self).__init__() nRefine = (nFull - 1) / nSection self.add('cyl_geom', CylinderDiscretization(nSection + 1, nRefine), promotes=[ 'section_height', 'diameter', 'wall_thickness', 'd_full', 't_full' ]) self.add('cyl_mass', CylinderMass(nFull), promotes=['d_full', 't_full', 'material_density']) self.add('col_geom', ColumnGeometry(nSection, nFull), promotes=[ 'water_depth', 'freeboard', 'fairlead', 'z_full', 'z_param', 'z_section', 'draft', 'draft_depth_ratio', 'fairlead_draft_ratio' ]) self.add('gc', GeometricConstraints(nSection + 1, diamFlag=True), promotes=[ 'min_taper', 'min_d_to_t', 'manufacturability', 'weldability' ]) self.add('bulk', BulkheadMass(nSection, nFull), promotes=[ 'z_full', 'z_param', 'd_full', 't_full', 'rho', 'bulkhead_mass_factor', 'bulkhead_thickness', 'bulkhead_mass', 'bulkhead_I_keel' ]) self.add('stiff', StiffenerMass(nSection, nFull), promotes=[ 'd_full', 't_full', 'z_full', 'z_param', 'rho', 'ring_mass_factor', 'stiffener_mass', 'stiffener_I_keel', 'stiffener_web_height', 'stiffener_web_thickness', 'stiffener_flange_width', 'stiffener_flange_thickness', 'stiffener_spacing', 'flange_spacing_ratio', 'stiffener_radius_ratio' ]) self.add( 'col', ColumnProperties(nFull), promotes=[ 'water_density', 'd_full', 't_full', 'z_full', 'z_section', 'permanent_ballast_density', 'permanent_ballast_height', 'bulkhead_mass', 'stiffener_mass', 'column_mass_factor', 'outfitting_mass_fraction', 'bulkhead_I_keel', 'stiffener_I_keel', 'ballast_cost_rate', 'tapered_col_cost_rate', 'outfitting_cost_rate', 'variable_ballast_interp_mass', 'variable_ballast_interp_zpts', 'z_center_of_mass', 'z_center_of_buoyancy', 'Awater', 'Iwater', 'I_column', 'displaced_volume', 'added_mass', 'total_mass', 'total_cost', 'ballast_mass', 'ballast_I_keel', 'ballast_z_cg' ]) self.add('wind', PowerWind(nFull), promotes=['Uref', 'zref', 'shearExp', 'z0']) self.add('wave', LinearWaves(nFull), promotes=['Uc', 'hmax', 'T']) self.add('windLoads', CylinderWindDrag(nFull), promotes=['cd_usr', 'beta']) self.add('waveLoads', CylinderWaveDrag(nFull), promotes=['cm', 'cd_usr']) self.add('distLoads', AeroHydroLoads(nFull), promotes=['Px', 'Py', 'Pz', 'qdyn', 'yaw']) self.add('buck', ColumnBuckling(nSection, nFull), promotes=[ 'd_full', 't_full', 'z_full', 'z_section', 'z_param', 'E', 'nu', 'yield_stress', 'loading', 'stack_mass_in', 'stiffener_web_height', 'stiffener_web_thickness', 'stiffener_flange_width', 'stiffener_flange_thickness', 'stiffener_spacing', 'flange_compactness', 'web_compactness', 'axial_local_unity', 'axial_general_unity', 'external_local_unity', 'external_general_unity' ]) self.connect('diameter', 'gc.d') self.connect('wall_thickness', 'gc.t') self.connect('cyl_geom.z_param', 'col_geom.z_param_in') self.connect('cyl_geom.z_full', ['cyl_mass.z_full', 'col_geom.z_full_in']) self.connect('cyl_mass.section_center_of_mass', 'col_geom.section_center_of_mass') self.connect('cyl_mass.mass', 'col.shell_mass') self.connect('cyl_mass.I_base', 'col.shell_I_keel') self.connect('material_density', 'rho') self.connect('total_mass', 'buck.section_mass') self.connect('water_depth', 'wave.z_floor') self.connect( 'z_full', ['wind.z', 'wave.z', 'windLoads.z', 'waveLoads.z', 'distLoads.z']) self.connect('d_full', ['windLoads.d', 'waveLoads.d']) self.connect('beta', 'waveLoads.beta') self.connect('z0', 'wave.z_surface') self.connect('wind.U', 'windLoads.U') self.connect('water_density', ['wave.rho', 'waveLoads.rho']) self.connect('wave.U', 'waveLoads.U') self.connect('wave.A', 'waveLoads.A') self.connect('wave.p', 'waveLoads.p') # connections to distLoads1 self.connect('windLoads.windLoads:Px', 'distLoads.windLoads:Px') self.connect('windLoads.windLoads:Py', 'distLoads.windLoads:Py') self.connect('windLoads.windLoads:Pz', 'distLoads.windLoads:Pz') self.connect('windLoads.windLoads:qdyn', 'distLoads.windLoads:qdyn') self.connect('windLoads.windLoads:beta', 'distLoads.windLoads:beta') self.connect('windLoads.windLoads:z', 'distLoads.windLoads:z') self.connect('windLoads.windLoads:d', 'distLoads.windLoads:d') self.connect('waveLoads.waveLoads:Px', 'distLoads.waveLoads:Px') self.connect('waveLoads.waveLoads:Py', 'distLoads.waveLoads:Py') self.connect('waveLoads.waveLoads:Pz', 'distLoads.waveLoads:Pz') self.connect('waveLoads.waveLoads:pt', 'distLoads.waveLoads:qdyn') self.connect('waveLoads.waveLoads:beta', 'distLoads.waveLoads:beta') self.connect('waveLoads.waveLoads:z', 'distLoads.waveLoads:z') self.connect('waveLoads.waveLoads:d', 'distLoads.waveLoads:d') self.connect('qdyn', 'buck.pressure')
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
def configure(self): self.add('pre', JcktLoadPre()) self.add('windj', PowerWind()) self.add('windt', PowerWind()) self.add('wavej', LinearWaves()) self.add('wavet', LinearWaves()) self.add('windLoadsj', TowerWindDrag()) self.add('windLoadst', TowerWindDrag()) self.add('waveLoadsj', TowerWaveDrag()) self.add('waveLoadst', TowerWaveDrag()) self.add('post', JcktLoadPost()) self.driver.workflow.add([ 'pre', 'windj', 'windt', 'wavej', 'wavet', 'windLoadsj', 'windLoadst', 'waveLoadsj', 'waveLoadst', 'post' ]) # connections to pre self.connect('nlegs', 'pre.nlegs') self.connect('nodes', 'pre.nodes') self.connect('pillegDs', 'pre.pillegDs') self.connect('twrDs', 'pre.twrDs') #self.connect('twrTs', 'pre.twrTs') self.connect('Twrmems', 'pre.Twrmems') self.connect('Legmems', 'pre.Legmems') self.connect('Pilemems', 'pre.Pilemems') # connections to windj/t self.connect('windIns.U50HH', ['windj.Uref', 'windt.Uref']) self.connect('windIns.HH + waterIns.wdepth + waterIns.z_floor', ['windj.zref', 'windt.zref']) self.connect('pre.pillegZs_out', 'windj.z') self.connect('pre.twrZs_out', 'windt.z') self.connect('waterIns.wdepth + waterIns.z_floor', ['windj.z0', 'windt.z0']) self.connect('windIns.psi', ['windj.betaWind', 'windt.betaWind']) self.connect('windIns.al_shear', ['windj.shearExp', 'windt.shearExp']) # connections to wavej/t self.connect('waterIns.Uc', ['wavej.Uc', 'wavet.Uc']) self.connect('waterIns.wdepth + waterIns.z_floor', ['wavej.z_surface', 'wavet.z_surface']) self.connect('waterIns.HW', ['wavej.hmax', 'wavet.hmax']) self.connect('waterIns.wdepth', ['wavej.wdepth', 'wavet.wdepth']) #CJB+ # self.connect('waterIns.T', ['wavej.T', 'wavet.T']) self.connect('waterIns.T', 'wavej.T') self.connect('waterIns.T', 'wavet.T') self.connect('waterIns.z_floor', ['wavej.z_floor', 'wavet.z_floor']) self.connect('gravity', ['wavej.g', 'wavet.g']) self.connect('waterIns.psi', ['wavej.betaWave', 'wavet.betaWave']) self.connect('pre.pillegZs_out', 'wavej.z') self.connect('pre.twrZs_out', 'wavet.z') # connections to windLoadsj self.connect('windj.U', 'windLoadsj.U') self.connect('windj.beta', 'windLoadsj.beta') self.connect('windIns.rho', 'windLoadsj.rho') self.connect('windIns.mu', 'windLoadsj.mu') self.connect('windIns.Cdj', 'windLoadsj.cd_usr') self.connect('pre.pillegZs_out', 'windLoadsj.z') self.connect('pre.pillegDs_out', 'windLoadsj.d') # connections to windLoadst self.connect('windt.U', 'windLoadst.U') self.connect('windt.beta', 'windLoadst.beta') self.connect('windIns.rho', 'windLoadst.rho') self.connect('windIns.mu', 'windLoadst.mu') self.connect('windIns.Cdt', 'windLoadst.cd_usr') self.connect('pre.twrZs_out', 'windLoadst.z') self.connect('pre.twrDs_out', 'windLoadst.d') # connections to waveLoadsj self.connect('wavej.U', 'waveLoadsj.U') self.connect('wavej.A', 'waveLoadsj.A') self.connect('wavej.beta', 'waveLoadsj.beta') self.connect('wavej.U0', 'waveLoadsj.U0') self.connect('wavej.A0', 'waveLoadsj.A0') self.connect('wavej.beta0', 'waveLoadsj.beta0') self.connect('waterIns.rho', 'waveLoadsj.rho') self.connect('waterIns.mu', 'waveLoadsj.mu') self.connect('waterIns.Cm', 'waveLoadsj.cm') self.connect('waterIns.Cd', 'waveLoadsj.cd_usr') self.connect('waterIns.wlevel', 'waveLoadsj.wlevel') self.connect('pre.pillegZs_out', 'waveLoadsj.z') self.connect('pre.pillegDs_out', 'waveLoadsj.d') # connections to waveLoadst self.connect('wavet.U', 'waveLoadst.U') self.connect('wavet.A', 'waveLoadst.A') self.connect('wavet.beta', 'waveLoadst.beta') self.connect('wavet.U0', 'waveLoadst.U0') self.connect('wavet.A0', 'waveLoadst.A0') self.connect('wavet.beta0', 'waveLoadst.beta0') self.connect('waterIns.rho', 'waveLoadst.rho') self.connect('waterIns.mu', 'waveLoadst.mu') self.connect('waterIns.Cm', 'waveLoadst.cm') self.connect('waterIns.Cd', 'waveLoadst.cd_usr') self.connect('waterIns.wlevel', 'waveLoadst.wlevel') self.connect('pre.twrZs_out', 'waveLoadst.z') self.connect('pre.twrDs_out', 'waveLoadst.d') # connections to post self.connect('windLoadst.windLoads', 'post.towerWindLoads') self.connect('waveLoadst.waveLoads', 'post.towerWaveLoads') self.connect('windLoadsj.windLoads', 'post.pileLegWindLoads') self.connect('waveLoadsj.waveLoads', 'post.pileLegWaveLoads') self.connect('pre.pilendIDs', 'post.pilendIDs') self.connect('pre.legndIDs', 'post.legndIDs') self.connect('pre.twrndIDs', 'post.twrndIDs') self.connect('nlegs', 'post.nlegs') self.connect('TwrRigidTop', 'post.TwrRigidTop') self.connect('RNAinputs', 'post.RNAinputs') self.connect('RNA_F', 'post.RNA_F') self.connect('al_bat3D', 'post.al_bat3D') self.connect('VPFlag', 'post.VPFlag') self.connect('waterIns.wdepth', 'post.wdepth') # connections to outputs self.connect('post.Loadouts', 'Loadouts') #self.connect('windLoadst.windLoads','twrWindLoads') #self.connect('waveLoadst.waveLoads','twrWaveLoads') self.create_passthrough('windLoadst.windLoads') self.create_passthrough('waveLoadst.waveLoads')
def __init__(self, RefBlade, npts_coarse_power_curve=20, npts_spline_power_curve=200, regulation_reg_II5 = True, regulation_reg_III=True): super(RotorAeroPower, self).__init__() self.add('rho', IndepVarComp('rho', val=1.225), promotes=['*']) self.add('mu', IndepVarComp('mu', val=1.81e-5), promotes=['*']) self.add('shearExp', IndepVarComp('shearExp', val=0.2), promotes=['*']) self.add('cdf_reference_height_wind_speed', IndepVarComp('cdf_reference_height_wind_speed', val=0.0, units='m', desc='reference hub height for IEC wind speed (used in CDF calculation)'), promotes=['*']) self.add('tiploss', IndepVarComp('tiploss', True, pass_by_obj=True), promotes=['*']) self.add('hubloss', IndepVarComp('hubloss', True, pass_by_obj=True), promotes=['*']) self.add('wakerotation', IndepVarComp('wakerotation', True, pass_by_obj=True), promotes=['*']) self.add('usecd', IndepVarComp('usecd', True, pass_by_obj=True), promotes=['*']) #self.add('airfoil_files', IndepVarComp('airfoil_files', AirfoilProperties.airfoil_files, pass_by_obj=True), promotes=['*']) # --- control --- self.add('c_Vin', IndepVarComp('control_Vin', val=0.0, units='m/s', desc='cut-in wind speed'), promotes=['*']) self.add('c_Vout', IndepVarComp('control_Vout', val=0.0, units='m/s', desc='cut-out wind speed'), promotes=['*']) self.add('c_ratedPower', IndepVarComp('control_ratedPower', val=0.0, units='W', desc='rated power'), promotes=['*']) self.add('c_minOmega', IndepVarComp('control_minOmega', val=0.0, units='rpm', desc='minimum allowed rotor rotation speed'), promotes=['*']) self.add('c_maxOmega', IndepVarComp('control_maxOmega', val=0.0, units='rpm', desc='maximum allowed rotor rotation speed'), promotes=['*']) self.add('c_maxTS', IndepVarComp('control_maxTS', val=0.0, units='m/s', desc='maximum allowed blade tip speed'), promotes=['*']) self.add('c_tsr', IndepVarComp('control_tsr', val=0.0, desc='tip-speed ratio in Region 2 (should be optimized externally)'), promotes=['*']) self.add('c_pitch', IndepVarComp('control_pitch', val=0.0, units='deg', desc='pitch angle in region 2 (and region 3 for fixed pitch machines)'), promotes=['*']) # --- drivetrain efficiency --- self.add('drivetrainType', IndepVarComp('drivetrainType', val=DRIVETRAIN_TYPE['GEARED'], pass_by_obj=True), promotes=['*']) # --- options --- self.add('nSector', IndepVarComp('nSector', val=4, iotype='in', desc='number of sectors to divide rotor face into in computing thrust and power', pass_by_obj=True), promotes=['*']) self.add('AEP_loss_factor', IndepVarComp('AEP_loss_factor', val=1.0, desc='availability and other losses (soiling, array, etc.)'), promotes=['*']) self.add('shape_parameter', IndepVarComp('shape_parameter', val=0.0), promotes=['*']) # --- Rotor Aero & Power --- self.add('rotorGeom', RotorGeometry(RefBlade), promotes=['*']) # self.add('tipspeed', MaxTipSpeed()) self.add('powercurve', RegulatedPowerCurve(RefBlade.npts, npts_coarse_power_curve, npts_spline_power_curve, regulation_reg_II5, regulation_reg_III)) self.add('wind', PowerWind(1)) # self.add('cdf', WeibullWithMeanCDF(npts_coarse_power_curve)) self.add('cdf', RayleighCDF(npts_spline_power_curve)) self.add('aep', AEP(npts_spline_power_curve)) self.add('outputs_aero', OutputsAero(npts_coarse_power_curve), promotes=['*']) # connections to analysis self.connect('r_pts', 'powercurve.r') self.connect('chord', 'powercurve.chord') self.connect('theta', 'powercurve.theta') self.connect('precurve', 'powercurve.precurve') self.connect('precurve_tip', 'powercurve.precurveTip') self.connect('Rhub', 'powercurve.Rhub') self.connect('Rtip', 'powercurve.Rtip') self.connect('hub_height', 'powercurve.hubHt') self.connect('precone', 'powercurve.precone') self.connect('tilt', 'powercurve.tilt') self.connect('yaw', 'powercurve.yaw') self.connect('airfoils', 'powercurve.airfoils') self.connect('nBlades', 'powercurve.B') self.connect('rho', 'powercurve.rho') self.connect('mu', 'powercurve.mu') self.connect('shearExp', 'powercurve.shearExp') self.connect('nSector', 'powercurve.nSector') self.connect('tiploss', 'powercurve.tiploss') self.connect('hubloss', 'powercurve.hubloss') self.connect('wakerotation', 'powercurve.wakerotation') self.connect('usecd', 'powercurve.usecd') # connections to powercurve self.connect('drivetrainType', 'powercurve.drivetrainType') self.connect('control_Vin', 'powercurve.control_Vin') self.connect('control_Vout', 'powercurve.control_Vout') self.connect('control_maxTS', 'powercurve.control_maxTS') self.connect('control_maxOmega', 'powercurve.control_maxOmega') self.connect('control_minOmega', 'powercurve.control_minOmega') self.connect('control_pitch', 'powercurve.control_pitch') self.connect('control_ratedPower', 'powercurve.control_ratedPower') self.connect('control_tsr', 'powercurve.control_tsr') # connections to wind # self.connect('cdf_reference_mean_wind_speed', 'wind.Uref') self.connect('turbineclass.V_mean', 'wind.Uref') self.connect('cdf_reference_height_wind_speed', 'wind.zref') self.connect('wind_zvec', 'wind.z') self.connect('shearExp', 'wind.shearExp') # connections to cdf self.connect('powercurve.V_spline', 'cdf.x') self.connect('wind.U', 'cdf.xbar', src_indices=[0]) self.connect('shape_parameter', 'cdf.k') # connections to aep self.connect('cdf.F', 'aep.CDF_V') self.connect('powercurve.P_spline', 'aep.P') self.connect('AEP_loss_factor', 'aep.lossFactor') # connect to outputs self.connect('geom.diameter', 'diameter_in') self.connect('turbineclass.V_extreme50', 'V_extreme_in') self.connect('precurve_tip', 'precurveTip_in') self.connect('presweep_tip', 'presweepTip_in') self.connect('powercurve.V', 'V_in') self.connect('powercurve.P', 'P_in') self.connect('aep.AEP', 'AEP_in') self.connect('powercurve.rated_V', 'rated_V_in') self.connect('powercurve.rated_Omega', 'rated_Omega_in') self.connect('powercurve.rated_pitch', 'rated_pitch_in') self.connect('powercurve.rated_T', 'rated_T_in') self.connect('powercurve.rated_Q', 'rated_Q_in') self.deriv_options['type'] = 'fd' self.deriv_options['form'] = 'central' self.deriv_options['step_calc'] = 'relative'
def main(): #\ """Function to Instantiate a TowerSE Assembly: \n INPUTS \n All hardwired, so edit the quantities below all the way to the line "#________________ DO NOT MODIFY THE FOLLOWING ________________#" \n -See TowerSEOpt_Py&MDAOopt.py for more information. \n OUTPUTS \n mytwr -tower assembly instance \n\n Optimization parameters: \n\n f0 -float, target frequency [Hz] f0epsilon -float, f0*(1+f0epsilon) will not be exceeded \n guesses -Float(n), guesses for all design variables check out DesVar class. \n bounds -Float(n,2), bounds for all design variables check out DesVar class. \n\n SAMPLE CALLS: \n 1.OPTIMIZATION: python towerOpt_ExtCobyla.py C:\RRD\PYTHON\WISDEM\towerSE\src\towerse\MyTowerInputs.py \n 2.OPTIMIZATION: python TowerSEOpt_Py&MDAOopt.py C:\RRD\PYTHON\WISDEM\towerSE\src\towerse\MytowerInputs.py True \n 3.BUILD Tower: python >>> mytwr=C:\RRD\PYTHON\WISDEM\TowerSE\src\towerse\MyTowerInputs.py \n """ # I need to put this at the top as it is not set up nicely as jacket: do not modify next line and go to inputs below mytwr = set_as_top(TowerMonopileSE()) # __________Frame3DD or PBeam___________# mytwr.replace('tower1', TowerWithpBEAM()) mytwr.replace('tower2', TowerWithpBEAM()) #mytwr.replace('tower1', TowerWithFrame3DD()) #mytwr.replace('tower2', TowerWithFrame3DD()) # __________Material___________# mytwr.material = Material(matname='heavysteel', E=2.1e11, G=8.08e10, rho=8500.) # __________Geometry/Positioning___________# mytwr.sea_depth = 20.0 mytwr.tower_length = 87.60 mytwr.tower_to_shaft = 2.0 mytwr.deck_height = 15.0 mytwr.monopile_extension = 5.0 mytwr.d_monopile = 6.0 # positioning for several variables now depends on monopile diameter mytwr.t_monopile = 0.06 mytwr.t_jacket = 0.05 mytwr.d_tower_base = 6.0 mytwr.d_tower_top = 3.87 mytwr.t_tower_base = 1.3 * 0.027 mytwr.t_tower_top = 1.3 * 0.019 mytwr.yaw = 0.0 mytwr.tilt = 5.0 # full geometry now specified by positioning component for monopile application # __________Environment___________# mytwr.replace('wind1', PowerWind()) mytwr.replace('wind2', PowerWind()) # wind mytwr.wind1.shearExp = 0.2 mytwr.wind2.shearExp = 0.2 # waves mytwr.replace('wave1', LinearWaves()) mytwr.replace('wave2', LinearWaves()) mytwr.wave1.Uc = 0.0 mytwr.wave1.hs = 8.0 * 1.86 mytwr.wave1.T = 10.0 mytwr.wave1.g = 9.81 mytwr.wave1.betaWave = 0.0 mytwr.wave2.Uc = 0.0 mytwr.wave2.hs = 8.0 * 1.86 mytwr.wave2.T = 10.0 mytwr.wave2.g = 9.81 mytwr.wave2.betaWave = 0.0 # __________Soil___________# mytwr.replace('soil', TowerSoil()) mytwr.soil.rigid = 6 * [True] #________RNA mass Properties_________# mytwr.top_m = 350000. #Float(iotype='in', units='m', desc='RNA (tower top) mass') mytwr.top_I = np.array( [114930678.00, 22035403.00, 18759742.50, 0.00, 503710.47, 0.00] ) #Array(iotype='in', units='kg*m**2', desc='mass moments of inertia. order: (xx, yy, zz, xy, xz, yz)') mytwr.top_cm = np.array( [-1.13, 0.00, 0.51]) #Array(iotype='in', units='m', desc='RNA center of mass') #_______________Loads________________# # max Thrust case mytwr.wind_Uref1 = 11.73732 mytwr.top1_F = np.array([ 1284744.196, 0.0, -112400.5527 ]) #Array(iotype='in', units='N', desc='Aerodynamic forces') mytwr.top1_M = np.array([ 3963732.762, 896380.8464, -346781.6819 ]) #Array(iotype='in', units='N*m', desc='Aerodynamic moments') # max wind speed case mytwr.wind_Uref2 = 70.0 mytwr.top2_F = np.array( [188038.8045, 0, -16451.2637] ) #Array(iotype='in', units='N', desc='Aerodynamic forces') # with all blades feathered mytwr.top2_M = np.array( [0.0, 131196.8431, 0.0]) #Array(iotype='in', units='N*m', desc='Aerodynamic moments') # fatigue mytwr.z_DEL = np.array( [0.000] ) #, 1.327, 3.982, 6.636, 9.291, 11.945, 14.600, 17.255, 19.909, 22.564, 25.218, 27.873, 30.527, 33.182, 35.836, 38.491, 41.145, 43.800, 46.455, 49.109, 51.764, 54.418, 57.073, 59.727, 62.382, 65.036, 67.691, 70.345, 73.000, 75.655, 78.309, 80.964, 83.618, 86.273, 87.600]) mytwr.M_DEL = 1e3 * np.array( [1.0] ) #8.2940E+003, 8.1518E+003, 7.8831E+003, 7.6099E+003, 7.3359E+003, 7.0577E+003, 6.7821E+003, 6.5119E+003, 6.2391E+003, 5.9707E+003, 5.7070E+003, 5.4500E+003, 5.2015E+003, 4.9588E+003, 4.7202E+003, 4.4884E+003, 4.2577E+003, 4.0246E+003, 3.7942E+003, 3.5664E+003, 3.3406E+003, 3.1184E+003, 2.8977E+003, 2.6811E+003, 2.4719E+003, 2.2663E+003, 2.0673E+003, 1.8769E+003, 1.7017E+003, 1.5479E+003, 1.4207E+003, 1.3304E+003, 1.2780E+003, 1.2673E+003, 1.2761E+003]) mytwr.gamma_fatigue = 1.35 * 1.3 * 1.0 mytwr.life = 20.0 mytwr.m_SN = 4 # Frame3DD parameters FrameAuxIns = Frame3DDaux() FrameAuxIns.sh_fg = 1 #shear flag-->Timoshenko FrameAuxIns.deltaz = 5. FrameAuxIns.geo_fg = 0 FrameAuxIns.nModes = 6 # number of desired dynamic modes of vibration FrameAuxIns.Mmethod = 1 # 1: subspace Jacobi 2: Stodola FrameAuxIns.lump = 0 # 0: consistent mass ... 1: lumped mass matrix FrameAuxIns.tol = 1e-9 # mode shape tolerance FrameAuxIns.shift = 0.0 # shift value ... for unrestrained structures FrameAuxIns.gvector = np.array([0., 0., -9.8065]) #GRAVITY #_____ Safety Factors______# mytwr.gamma_f = 1.35 mytwr.gamma_m = 1.3 mytwr.gamma_n = 1.0 mytwr.gamma_b = 1.1 #______________________________________________# #______________________________________________# # OTHER AUXILIARY CONSTRAINTS AND TARGETS FOR OPTIMIZATION # !!! NOT USED IN THIS FILE! #______________________________________________# #______________________________________________# # _______Geometric constraints__________# mytwr.min_taper = 0.4 DTRsdiff = True #Set whether or not DTRt=DTRb #______Set target frequency [Hz] and f0epsilon, i.e. fmax=(1+f0eps)*f0_________# f0 = 0.28 f0epsilon = 0.1 #________Set Optimization Bounds and guesses for the various variables_________# # x= [ Db, DTRb Dt, DTRt Htwr2fac ] MnCnst = np.array([5., 120., 3., 120., 0.05]) MxCnst = np.array([7., 200., 4., 200., 0.25]) guesses = np.array([6., 140., 3.5, 150., 0.2]) #_____________________________________________________________# #________________ DO NOT MODIFY THE FOLLOWING ________________# #_____________________________________________________________# mytwr.min_d_to_t = np.min(MnCnst[[1, 3]]) bounds = np.vstack((MnCnst, MxCnst)) desvarmeans = np.mean(bounds, 1) mytwr.FrameAuxIns = FrameAuxIns return mytwr, f0, f0epsilon, DTRsdiff, guesses, bounds.T
def __init__(self, nPoints, nFull, nK, nMass, nPL, nDEL, wind=''): super(TowerSE, self).__init__() self.fd_options['force_fd'] = True self.add('geometry', TowerDiscretization(nPoints, nFull), promotes=['*']) # two load cases. TODO: use a case iterator if wind == 'PowerWind': self.add('wind1', PowerWind(nFull), promotes=['zref', 'z0']) self.add('wind2', PowerWind(nFull), promotes=['zref', 'z0']) elif wind == 'LogWind': self.add('wind1', LogWind(nFull), promotes=['zref', 'z0']) self.add('wind2', LogWind(nFull), promotes=['zref', 'z0']) self.add('wave1', WaveBase(nFull)) self.add('wave2', WaveBase(nFull)) self.add('windLoads1', TowerWindDrag(nFull)) self.add('windLoads2', TowerWindDrag(nFull)) self.add('waveLoads1', TowerWaveDrag(nFull)) self.add('waveLoads2', TowerWaveDrag(nFull)) self.add('distLoads1', AeroHydroLoads(nFull), promotes=['yaw']) self.add('distLoads2', AeroHydroLoads(nFull), promotes=['yaw']) self.add('props', CylindricalShellProperties(nFull), promotes=['Az', 'Asx', 'Asy', 'Jz', 'Ixx', 'Iyy']) self.add('tower1', TowerFrame3DD(nFull, nK, nMass, nPL, nDEL), promotes=[ 'E', 'G', 'sigma_y', 'L_reinforced', 'kidx', 'kx', 'ky', 'kz', 'ktx', 'kty', 'ktz', 'midx', 'm', 'mIxx', 'mIyy', 'mIzz', 'mIxy', 'mIxz', 'mIyz', 'mrhox', 'mrhoy', 'mrhoz', 'addGravityLoadForExtraMass', 'g', 'gamma_f', 'gamma_m', 'gamma_n', 'gamma_b', 'life', 'm_SN', 'DC', 'z_DEL', 'M_DEL', 'gamma_fatigue', 'shear', 'geom', 'dx', 'nM', 'Mmethod', 'lump', 'tol', 'shift', 'Az', 'Asx', 'Asy', 'Jz', 'Ixx', 'Iyy' ]) self.add('tower2', TowerFrame3DD(nFull, nK, nMass, nPL, nDEL), promotes=[ 'E', 'G', 'sigma_y', 'L_reinforced', 'kidx', 'kx', 'ky', 'kz', 'ktx', 'kty', 'ktz', 'midx', 'm', 'mIxx', 'mIyy', 'mIzz', 'mIxy', 'mIxz', 'mIyz', 'mrhox', 'mrhoy', 'mrhoz', 'addGravityLoadForExtraMass', 'g', 'gamma_f', 'gamma_m', 'gamma_n', 'gamma_b', 'life', 'm_SN', 'DC', 'z_DEL', 'M_DEL', 'gamma_fatigue', 'shear', 'geom', 'dx', 'nM', 'Mmethod', 'lump', 'tol', 'shift', 'Az', 'Asx', 'Asy', 'Jz', 'Ixx', 'Iyy' ]) self.add('gc', GeometricConstraints(nPoints)) self.connect('distLoads2.Px', 'tower2.Px') self.connect('distLoads2.Py', 'tower2.Py') self.connect('distLoads2.Pz', 'tower2.Pz') self.connect('distLoads2.qdyn', 'tower2.qdyn') #self.connect('distLoads2.outloads', 'tower2.WWloads') # connect tower1 and tower2 self.connect('tower1.rho', 'tower2.rho') # connections to gc self.connect('d_param', 'gc.d') self.connect('t_param', 'gc.t') # connections to wind1 self.connect('z_full', 'wind1.z') # connections to wind2 self.connect('z_full', 'wind2.z') # connections to wave1 and wave2 self.connect('z_full', 'wave1.z') self.connect('z_full', 'wave2.z') # connections to windLoads1 self.connect('wind1.U', 'windLoads1.U') self.connect('z_full', 'windLoads1.z') self.connect('d_full', 'windLoads1.d') self.connect('wind1.beta', 'windLoads1.beta') # connections to windLoads2 self.connect('wind2.U', 'windLoads2.U') self.connect('z_full', 'windLoads2.z') self.connect('d_full', 'windLoads2.d') self.connect('wind2.beta', 'windLoads2.beta') # connect windLoads self.connect('windLoads1.rho', 'windLoads2.rho') self.connect('windLoads1.mu', 'windLoads2.mu') self.connect('windLoads1.cd_usr', 'windLoads2.cd_usr') # connections to waveLoads1 self.connect('wave1.U', 'waveLoads1.U') self.connect('wave1.A', 'waveLoads1.A') self.connect('z_full', 'waveLoads1.z') self.connect('d_full', 'waveLoads1.d') self.connect('wave1.beta', 'waveLoads1.beta') # connections to waveLoads2 self.connect('wave2.U', 'waveLoads2.U') self.connect('wave2.A', 'waveLoads2.A') self.connect('z_full', 'waveLoads2.z') self.connect('d_full', 'waveLoads2.d') self.connect('wave2.beta', 'waveLoads2.beta') # connect waveLoads self.connect('waveLoads1.rho', 'waveLoads2.rho') self.connect('waveLoads1.mu', 'waveLoads2.mu') self.connect('waveLoads1.cm', 'waveLoads2.cm') self.connect('waveLoads1.cd_usr', 'waveLoads2.cd_usr') # connections to distLoads1 self.connect('z_full', 'distLoads1.z') # connections to distLoads2 self.connect('z_full', 'distLoads2.z') # connections to props self.connect('d_full', 'props.d') self.connect('t_full', 'props.t') # connect to tower1 self.connect('z_full', 'tower1.z') self.connect('d_full', 'tower1.d') self.connect('t_full', 'tower1.t') self.connect('distLoads1.Px', 'tower1.Px') self.connect('distLoads1.Py', 'tower1.Py') self.connect('distLoads1.Pz', 'tower1.Pz') self.connect('distLoads1.qdyn', 'tower1.qdyn') #self.connect('distLoads1.outloads', 'tower1.WWloads') # connect to tower2 self.connect('z_full', 'tower2.z') self.connect('d_full', 'tower2.d') self.connect('t_full', 'tower2.t') self.connect('windLoads1.windLoads:Px', 'distLoads1.windLoads:Px') self.connect('windLoads1.windLoads:Py', 'distLoads1.windLoads:Py') self.connect('windLoads1.windLoads:Pz', 'distLoads1.windLoads:Pz') self.connect('windLoads1.windLoads:qdyn', 'distLoads1.windLoads:qdyn') self.connect('windLoads1.windLoads:beta', 'distLoads1.windLoads:beta') self.connect('windLoads1.windLoads:Px0', 'distLoads1.windLoads:Px0') self.connect('windLoads1.windLoads:Py0', 'distLoads1.windLoads:Py0') self.connect('windLoads1.windLoads:Pz0', 'distLoads1.windLoads:Pz0') self.connect('windLoads1.windLoads:qdyn0', 'distLoads1.windLoads:qdyn0') self.connect('windLoads1.windLoads:beta0', 'distLoads1.windLoads:beta0') self.connect('windLoads1.windLoads:z', 'distLoads1.windLoads:z') self.connect('windLoads1.windLoads:d', 'distLoads1.windLoads:d') self.connect('windLoads2.windLoads:Px', 'distLoads2.windLoads:Px') self.connect('windLoads2.windLoads:Py', 'distLoads2.windLoads:Py') self.connect('windLoads2.windLoads:Pz', 'distLoads2.windLoads:Pz') self.connect('windLoads2.windLoads:qdyn', 'distLoads2.windLoads:qdyn') self.connect('windLoads2.windLoads:beta', 'distLoads2.windLoads:beta') self.connect('windLoads2.windLoads:Px0', 'distLoads2.windLoads:Px0') self.connect('windLoads2.windLoads:Py0', 'distLoads2.windLoads:Py0') self.connect('windLoads2.windLoads:Pz0', 'distLoads2.windLoads:Pz0') self.connect('windLoads2.windLoads:qdyn0', 'distLoads2.windLoads:qdyn0') self.connect('windLoads2.windLoads:beta0', 'distLoads2.windLoads:beta0') self.connect('windLoads2.windLoads:z', 'distLoads2.windLoads:z') self.connect('windLoads2.windLoads:d', 'distLoads2.windLoads:d') self.connect('waveLoads1.waveLoads:Px', 'distLoads1.waveLoads:Px') self.connect('waveLoads1.waveLoads:Py', 'distLoads1.waveLoads:Py') self.connect('waveLoads1.waveLoads:Pz', 'distLoads1.waveLoads:Pz') self.connect('waveLoads1.waveLoads:qdyn', 'distLoads1.waveLoads:qdyn') self.connect('waveLoads1.waveLoads:beta', 'distLoads1.waveLoads:beta') self.connect('waveLoads1.waveLoads:Px0', 'distLoads1.waveLoads:Px0') self.connect('waveLoads1.waveLoads:Py0', 'distLoads1.waveLoads:Py0') self.connect('waveLoads1.waveLoads:Pz0', 'distLoads1.waveLoads:Pz0') self.connect('waveLoads1.waveLoads:qdyn0', 'distLoads1.waveLoads:qdyn0') self.connect('waveLoads1.waveLoads:beta0', 'distLoads1.waveLoads:beta0') self.connect('waveLoads1.waveLoads:z', 'distLoads1.waveLoads:z') self.connect('waveLoads1.waveLoads:d', 'distLoads1.waveLoads:d') self.connect('waveLoads2.waveLoads:Px', 'distLoads2.waveLoads:Px') self.connect('waveLoads2.waveLoads:Py', 'distLoads2.waveLoads:Py') self.connect('waveLoads2.waveLoads:Pz', 'distLoads2.waveLoads:Pz') self.connect('waveLoads2.waveLoads:qdyn', 'distLoads2.waveLoads:qdyn') self.connect('waveLoads2.waveLoads:beta', 'distLoads2.waveLoads:beta') self.connect('waveLoads2.waveLoads:Px0', 'distLoads2.waveLoads:Px0') self.connect('waveLoads2.waveLoads:Py0', 'distLoads2.waveLoads:Py0') self.connect('waveLoads2.waveLoads:Pz0', 'distLoads2.waveLoads:Pz0') self.connect('waveLoads2.waveLoads:qdyn0', 'distLoads2.waveLoads:qdyn0') self.connect('waveLoads2.waveLoads:beta0', 'distLoads2.waveLoads:beta0') self.connect('waveLoads2.waveLoads:z', 'distLoads2.waveLoads:z') self.connect('waveLoads2.waveLoads:d', 'distLoads2.waveLoads:d') # outputs TODO """