def example(wind_class='I',sea_depth=0.0,with_new_nacelle=False,with_landbos=False,flexible_blade=False,with_3pt_drive=False, with_ecn_opex=False, ecn_file=None,with_openwind=False,ow_file=None,ow_wkbook=None):
"""
Inputs:
wind_class : str ('I', 'III', 'Offshore' - selected wind class for project)
sea_depth : float (sea depth if an offshore wind plant)
"""
# === Create LCOE SE assembly ========
lcoe_se = lcoe_se_assembly(with_new_nacelle,with_landbos,flexible_blade,with_3pt_drive,with_ecn_opex,ecn_file)
# === Set assembly variables and objects ===
lcoe_se.sea_depth = sea_depth # 0.0 for land-based turbine
lcoe_se.turbine_number = 100
lcoe_se.year = 2009
lcoe_se.month = 12
rotor = lcoe_se.rotor
nacelle = lcoe_se.nacelle
jacket = lcoe_se.jacket
tcc_a = lcoe_se.tcc_a
# bos_a = lcoe_se.bos_a
# opex_a = lcoe_se.opex_a
aep_a = lcoe_se.aep_a
fin_a = lcoe_se.fin_a
# Turbine ===========
from wisdem.reference_turbines.nrel5mw.nrel5mw_jacket import configure_nrel5mw_turbine_with_jacket
configure_nrel5mw_turbine_with_jacket(lcoe_se,wind_class,lcoe_se.sea_depth)
# TODO: these should be specified at the turbine level and connected to other system inputs
lcoe_se.tower_dt = 3.87 # (Array, m): diameters along tower # float for jacket
lcoe_se.generator_speed = 1173.7 # (Float, rpm) # generator speed
# extra variable constant for now
#lcoe_se.nacelle.bedplate.rotor_bending_moment_y = -2.3250E+06 # shouldnt be needed anymore
# tcc ====
lcoe_se.advanced_blade = True
lcoe_se.offshore = False
lcoe_se.assemblyCostMultiplier = 0.30
lcoe_se.profitMultiplier = 0.20
lcoe_se.overheadCostMultiplier = 0.0
lcoe_se.transportMultiplier = 0.0
# for new landBOS
''' # === new landBOS ===
lcoe_se.voltage = 137
lcoe_se.distInter = 5
lcoe_se.terrain = 'FLAT_TO_ROLLING'
lcoe_se.layout = 'SIMPLE'
lcoe_se.soil = 'STANDARD' '''
# aep ====
if not with_openwind:
lcoe_se.array_losses = 0.059
lcoe_se.other_losses = 0.0
if not with_ecn_opex:
lcoe_se.availability = 0.94
# fin ===
lcoe_se.fixed_charge_rate = 0.095
lcoe_se.construction_finance_rate = 0.0
lcoe_se.tax_rate = 0.4
lcoe_se.discount_rate = 0.07
lcoe_se.construction_time = 1.0
lcoe_se.project_lifetime = 20.0
# Set plant level inputs ===
shearExp = 0.2 #TODO : should be an input to lcoe
rotor.cdf_reference_height_wind_speed = 90.0
if not with_openwind:
lcoe_se.array_losses = 0.1
lcoe_se.other_losses = 0.0
if not with_ecn_opex:
lcoe_se.availability = 0.98
rotor.turbulence_class = 'B'
lcoe_se.multiplier = 2.23
if wind_class == 'Offshore':
# rotor.cdf_reference_mean_wind_speed = 8.4 # TODO - aep from its own module
# rotor.cdf_reference_height_wind_speed = 50.0
# rotor.weibull_shape = 2.1
shearExp = 0.14 # TODO : should be an input to lcoe
lcoe_se.array_losses = 0.15
if not with_ecn_opex:
lcoe_se.availability = 0.96
lcoe_se.offshore = True
lcoe_se.multiplier = 2.33
lcoe_se.fixed_charge_rate = 0.118
rotor.shearExp = shearExp
#tower.wind1.shearExp = shearExp # not needed for jacket
#tower.wind2.shearExp = shearExp
# ====
from rotorse.precomp import Profile, Orthotropic2DMaterial, CompositeSection # TODO: can just pass file names and do this initialization inside of rotor
#from commonse.environment import PowerWind, TowerSoil
#from wisdem.reference_turbines.nrel5mw.nrel5mw_jacket import configure_nrel5mw_turbine_with_jacket
from commonse.utilities import print_vars
#configure_nrel5mw_turbine_with_jacket(turbine)
# print_vars(turbine, list_type='inputs', prefix='turbine')
rotor = lcoe_se.rotor
nacelle = lcoe_se.nacelle
jacket = lcoe_se.jacket
# =================
# === Turbine Configuration ===
# --- atmosphere ---
lcoe_se.rho = 1.225 # (Float, kg/m**3): density of air
lcoe_se.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air
lcoe_se.shear_exponent = 0.2 # (Float): shear exponent
lcoe_se.hub_height = 90.0 # (Float, m): hub height
lcoe_se.turbine_class = 'I' # (Enum): IEC turbine class
lcoe_se.turbulence_class = 'B' # (Enum): IEC turbulence class class
lcoe_se.cdf_reference_height_wind_speed = 90.0 # (Float): reference hub height for IEC wind speed (used in CDF calculation)
lcoe_se.g = 9.81 # (Float, m/s**2): acceleration of gravity
lcoe_se.downwind = False # (Bool): flag if rotor is downwind
lcoe_se.generator_speed = 1173.7 # (Float, rpm) # generator speed
lcoe_se.tower_dt = 3.87
# ----------------------
# ============================
# === rotor ===
# --- blade grid ---
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
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
rotor.idx_cylinder_aero = 3 # (Int): first idx in r_aero_unit of non-cylindrical section, constant twist inboard of here
rotor.idx_cylinder_str = 14 # (Int): first idx in r_str_unit of non-cylindrical section
rotor.hubFraction = 0.025 # (Float): hub location as fraction of radius
# ------------------
# --- blade geometry ---
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
rotor.r_max_chord = 0.23577 # (Float): location of max chord on unit radius
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
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
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)
rotor.delta_precurve_sub = [0.0, 0.0, 0.0] # (Array, m): adjustment to precurve to account for curvature from loading
rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398] # (Array, m): spar cap thickness parameters
rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569] # (Array, m): trailing-edge thickness parameters
rotor.bladeLength = 61.5 # (Float, m): blade length (if not precurved or swept) otherwise length of blade before curvature
rotor.delta_bladeLength = 0.0 # (Float, m): adjustment to blade length to account for curvature from loading
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 ---
import rotorse
basepath = os.path.join(os.path.dirname(rotorse.__file__), '5MW_AFFiles')
# 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
# ----------------------
# --- control ---
rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed
rotor.control.Vout = 25.0 # (Float, m/s): cut-out wind speed
#rotor.control.ratedPower = 5e6 # (Float, W): rated power
lcoe_se.machine_rating = 5e3 # (Float, kW): rated power
rotor.control.minOmega = 0.0 # (Float, rpm): minimum allowed rotor rotation speed
rotor.control.maxOmega = 12.0 # (Float, rpm): maximum allowed rotor rotation speed
rotor.control.tsr = 7.55 # (Float): tip-speed ratio in Region 2 (should be optimized externally)
rotor.control.pitch = 0.0 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines)
rotor.pitch_extreme = 0.0 # (Float, deg): worst-case pitch at survival wind condition
rotor.azimuth_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition
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 ---
rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power
rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at
rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve
rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.)
rotor.drivetrainType = 'geared' # (Enum)
rotor.nF = 5 # (Int): number of natural frequencies to compute
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(os.path.dirname(rotorse.__file__), '5MW_PreCompFiles')
# 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
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
rotor.sector_idx_strain_spar = [2]*ncomp # (Array): index of sector for spar (PreComp definition of sector)
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])
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'))
rotor.materials = materials # (List): list of all Orthotropic2DMaterial objects used in defining the geometry
rotor.upperCS = upper # (List): list of CompositeSection objections defining the properties for upper surface
rotor.lowerCS = lower # (List): list of CompositeSection objections defining the properties for lower surface
rotor.websCS = webs # (List): list of CompositeSection objections defining the properties for shear webs
rotor.profile = profile # (List): airfoil shape at each radial position
# --------------------------------------
# --- fatigue ---
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
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
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
rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap
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.
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
rotor.N_damage = 365*24*3600*20.0 # (Float): number of cycles used in fatigue analysis TODO: make function of rotation speed
# ----------------
# =================
# === nacelle ======
nacelle.L_ms = 1.0 # (Float, m): main shaft length downwind of main bearing in low-speed shaft
nacelle.L_mb = 2.5 # (Float, m): main shaft length in low-speed shaft
nacelle.h0_front = 1.7 # (Float, m): height of Ibeam in bedplate front
nacelle.h0_rear = 1.35 # (Float, m): height of Ibeam in bedplate rear
# TODO: sync with rotor drivetrainType variable
nacelle.drivetrain_design = 'geared'
nacelle.crane = True # (Bool): flag for presence of crane
nacelle.bevel = 0 # (Int): Flag for the presence of a bevel stage - 1 if present, 0 if not
nacelle.gear_configuration = 'eep' # (Str): tring that represents the configuration of the gearbox (stage number and types)
nacelle.Np = [3, 3, 1] # (Array): number of planets in each stage
nacelle.ratio_type = 'optimal' # (Str): optimal or empirical stage ratios
nacelle.shaft_type = 'normal' # (Str): normal or short shaft length
#nacelle.shaft_angle = 5.0 # (Float, deg): Angle of the LSS inclindation with respect to the horizontal
nacelle.shaft_ratio = 0.10 # (Float): Ratio of inner diameter to outer diameter. Leave zero for solid LSS
#nacelle.shrink_disc_mass = 1000.0 # (Float, kg): Mass of the shrink disc
nacelle.mb1Type = 'CARB' # (Str): Main bearing type: CARB, TRB or SRB
nacelle.mb2Type = 'SRB' # (Str): Second bearing type: CARB, TRB or SRB
nacelle.yaw_motors_number = 8.0 # (Float): number of yaw motors
nacelle.uptower_transformer = True
nacelle.flange_length = 0.5 #m
nacelle.gearbox_cm = 0.1
nacelle.hss_length = 1.5
nacelle.overhang = 5.0 #TODO - should come from turbine configuration level
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)
nacelle.DrivetrainEfficiency = 0.95
nacelle.rotor_bending_moment_x = 330770.0# Nm
nacelle.rotor_bending_moment_y = -16665000.0 # Nm
nacelle.rotor_bending_moment_z = 2896300.0 # Nm
nacelle.rotor_force_x = 599610.0 # N
nacelle.rotor_force_y = 186780.0 # N
nacelle.rotor_force_z = -842710.0 # N
#nacelle.h0_rear = 1.35 # only used in drive smooth
#nacelle.h0_front = 1.7
# =================
# === jacket ===
#--- Set Jacket Input Parameters ---#
Jcktins=JcktGeoInputs()
Jcktins.nlegs =4
Jcktins.nbays =5
Jcktins.batter=12.
Jcktins.dck_botz =16.
Jcktins.dck_width=2*6.
Jcktins.weld2D =0.5
Jcktins.VPFlag = True #vertical pile T/F; to enable piles in frame3DD set pileinputs.ndiv>0
Jcktins.clamped= False #whether or not the bottom of the structure is rigidly connected. Use False when equivalent spring constants are being used.
Jcktins.AFflag = False #whether or not to use apparent fixity piles
Jcktins.PreBuildTPLvl = 5 #if >0, the TP is prebuilt according to rules per PreBuildTP
#Soil inputs
Soilinputs=SoilGeoInputs()
Soilinputs.zbots =-np.array([3.,5.,7.,15.,30.,50.])
Soilinputs.gammas =np.array([10000.,10000.,10000.,10000.,10000.,10000.])
Soilinputs.cus =np.array([60000.,60000.,60000.,60000.,60000.,60000.])
Soilinputs.phis =np.array([26.,26.,26.,26.,26.,26])#np.array([36.,33.,26.,37.,35.,37.5])#np.array([36.,33.,26.,37.,35.,37.5])
Soilinputs.delta =25.
Soilinputs.sndflg =True
Soilinputs.PenderSwtch =False #True
Soilinputs.SoilSF =1.
Soilinputs2=copy.copy(Soilinputs) #Parked case. We assume same stiffness although this may not be the case under a different load
#Water and wind inputs
Waterinputs=WaterInputs()
Waterinputs.wdepth =30.
Waterinputs.wlevel =30. #Distance from bottom of structure to surface THIS, I believe is no longer needed as piles may be negative in z, to check and remove in case
Waterinputs.T=12. #Wave Period
Waterinputs.HW=10. #Wave Height
Waterinputs.Cd=3. #Drag Coefficient, enhanced to account for marine growth and other members not calculated
Waterinputs.Cm=8.#2. #ADded mass Coefficient
Waterinputs2=copy.copy(Waterinputs) #PARKED CONDITIONS - still max wave here
Waterinputs.T=8. #Wave Period
Waterinputs.HW=4. #Wave Height
Windinputs=WindInputs()
Windinputs.Cdj=4. #Drag Coefficient for jacket members, enhanced to account for TP drag not calculated otherwise
Windinputs.Cdt=2 #Drag Coefficient for tower, enhanced to account for TP drag not calculated otherwise
Windinputs.HH=100. #CHECK HOW THIS COMPLIES....
Windinputs.U50HH=30. #assumed gust speed
## if turbine_jacket
##Windinputs.HH=90. #CHECK HOW THIS COMPLIES....
##Windinputs.U50HH=11.7373200354 # using rated loads
##Windinputs.rho = 1.225
##Windinputs.mu = 1.81206e-05
Windinputs2=copy.copy(Windinputs)
Windinputs2.U50HH=70. #assumed gust speed
#Pile data
Pilematin=MatInputs()
Pilematin.matname=np.array(['steel'])
Pilematin.E=np.array([ 25.e9])
Dpile=2.5#0.75 # 2.0
tpile=0.01
Lp=20. #45
Pileinputs=PileGeoInputs()
Pileinputs.Pilematins=Pilematin
Pileinputs.ndiv=0 #3
Pileinputs.Dpile=Dpile
Pileinputs.tpile=tpile
Pileinputs.Lp=Lp #[m] Embedment length
#Legs data
legmatin=MatInputs()
legmatin.matname=(['heavysteel','heavysteel','heavysteel','heavysteel'])
#legmatin.E=np.array([2.0e11])
Dleg=np.array([1.5,1.5,1.5,1.5,1.5,1.5])
tleg=1.5*np.array([0.0254]).repeat(Dleg.size)
leginputs=LegGeoInputs()
leginputs.legZbot = 1.0
leginputs.ndiv=1
leginputs.legmatins=legmatin
leginputs.Dleg0=Dleg[0]
leginputs.tleg0=tleg[0]
legbot_stmphin =1.5 #Distance from bottom of leg to second joint along z; must be>0
#Xbrc data
Xbrcmatin=MatInputs()
Xbrcmatin.matname=np.array(['heavysteel']).repeat(Jcktins.nbays)
#Xbrcmatin.E=np.array([ 2.2e11, 2.0e11,2.0e11,2.0e11,2.0e11])
Dbrc=np.array([1.,1.,1.0,1.0,1.0])
tbrc=np.array([1.,1.,1.0,1.0,1.0])*0.0254
Xbrcinputs=XBrcGeoInputs()
Xbrcinputs.Dbrc0=Dbrc[0]
Xbrcinputs.tbrc0=tbrc[0]
Xbrcinputs.ndiv=2#2
Xbrcinputs.Xbrcmatins=Xbrcmatin
Xbrcinputs.precalc=False #True #This can be set to true if we want Xbraces to be precalculated in D and t, in which case the above set Dbrc and tbrc would be overwritten
#Mbrc data
Mbrcmatin=MatInputs()
Mbrcmatin.matname=np.array(['heavysteel'])
#Mbrcmatin.E=np.array([ 2.5e11])
Dbrc_mud=1.5
Mbrcinputs=MudBrcGeoInputs()
Mbrcinputs.Dbrc_mud=Dbrc_mud
Mbrcinputs.ndiv=2
Mbrcinputs.Mbrcmatins=Mbrcmatin
Mbrcinputs.precalc=False #True #This can be set to true if we want Mudbrace to be precalculated in D and t, in which case the above set Dbrc_mud and tbrc_mud would be overwritten
#Hbrc data
Hbrcmatin=MatInputs()
Hbrcmatin.matname=np.array(['heavysteel'])
Hbrcmatin.E=np.array([ 2.5e11])
Dbrc_hbrc=1.1
Hbrcinputs=HBrcGeoInputs()
Hbrcinputs.Dbrch=Dbrc_hbrc
Hbrcinputs.ndiv=0#2
Hbrcinputs.Hbrcmatins=Hbrcmatin
Hbrcinputs.precalc=True #This can be set to true if we want Hbrace to be set=Xbrace top D and t, in which case the above set Dbrch and tbrch would be overwritten
#TP data
TPlumpinputs=TPlumpMass()
TPlumpinputs.mass=200.e3 #[kg]
TPstmpsmatin=MatInputs()
TPbrcmatin=MatInputs()
TPstemmatin=MatInputs()
TPbrcmatin.matname=np.array(['heavysteel'])
#TPbrcmatin.E=np.array([ 2.5e11])
TPstemmatin.matname=np.array(['heavysteel']).repeat(2)
#TPstemmatin.E=np.array([ 2.1e11]).repeat(2)
TPinputs=TPGeoInputs()
TPinputs.TPbrcmatins=TPbrcmatin
TPinputs.TPstemmatins=TPstemmatin
TPinputs.TPstmpmatins=TPstmpsmatin
TPinputs.Dstrut=leginputs.Dleg[-1]
TPinputs.tstrut=leginputs.tleg[-1]
TPinputs.Dgir=Dbrc_hbrc
TPinputs.tgir=0.0254
TPinputs.Dbrc=1.1
TPinputs.Dbrc=TPinputs.Dgir
TPinputs.tbrc=TPinputs.tgir
TPinputs.hstump=1.0#1.0
TPinputs.Dstump=1.25#1.0
TPinputs.stumpndiv=1#2
TPinputs.brcndiv=1#2
TPinputs.girndiv=1#2
TPinputs.strutndiv=1#2
TPinputs.stemndiv=1#2
TPinputs.nstems=3
TPinputs.Dstem=np.array([6.]).repeat(TPinputs.nstems)
TPinputs.tstem=np.array([0.1,0.11,0.11])
TPinputs.hstem=np.array([6./TPinputs.nstems]).repeat(TPinputs.nstems)
#Tower data
Twrmatin=MatInputs()
Twrmatin.matname=np.array(['heavysteel'])
#Twrmatin.E=np.array([ 2.77e11])
Twrinputs=TwrGeoInputs()
Twrinputs.Twrmatins=Twrmatin
#Twrinputs.Htwr=70. #Trumped by HH
Twrinputs.Htwr2frac=0.2 #fraction of tower height with constant x-section
Twrinputs.ndiv=np.array([6,12]) #ndiv for uniform and tapered section
Twrinputs.DeltaZmax= 6. #[m], maximum FE element length allowed in the tower members (i.e. the uniform and the tapered members)
Twrinputs.Db=5.6
Twrinputs.DTRb=130.
Twrinputs.DTRt=150.
Twrinputs.Dt=0.55*Twrinputs.Db
## if turbine_jacket
##Twrinputs.Dt = 3.87
TwrRigidTop=True #False #False=Account for RNA via math rather than a physical rigidmember
#RNA data
RNAins=RNAprops()
RNAins.mass=3*350.e3
RNAins.I[0]=86.579E+6
RNAins.I[1]=53.530E+6
RNAins.I[2]=58.112E+6
RNAins.CMoff[2]=2.34
RNAins.yawangle=45. #angle with respect to global X, CCW looking from above, wind from left
RNAins.rna_weightM=True
## if turbine_jacket
##RNAins.mass=285598.806453
##RNAins.I = np.array([1.14930678e8, 2.20354030e7, 1.87597425e7, 0.0, 5.03710467e5, 0.0])
##RNAins.CMoff = np.array([-1.13197635, 0.0, 0.50875268])
##RNAins.yawangle=0.0 #angle with respect to global X, CCW looking from above, wind from left
#RNAins.rna_weightM=True
RNAins2=copy.copy(RNAins) #PARKED CASE, for now assume the same
#RNA loads Fx-z, Mxx-zz
RNA_F=np.array([1000.e3,0.,0.,0.,0.,0.]) #operational
RNA_F2=np.array([500.e3,0.,0.,0.,0.,0.]) #Parked
## if turbine_jacket
##RNA_F=np.array([1284744.19620519,0.,-2914124.84400512,3963732.76208099,-2275104.79420872,-346781.68192839])
#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
## if turbine_jacket
##FrameAuxIns.gvector=np.array([0.,0.,-9.81]) #GRAVITY
#Decide whether or not to consider DLC 6.1 as well
twodlcs=False
#-----Launch the assembly-----#
#turbine.jacket=JacketSE(Jcktins.clamped,Jcktins.AFflag,twodlcs=twodlcs)
#turbine.jacket=set_as_top(JacketSE(Jcktins.clamped,Jcktins.AFflag,twodlcs=twodlcs)) ##(Jcktins.PreBuildTPLvl>0),
#Pass all inputs to assembly
lcoe_se.jacket.JcktGeoIn=Jcktins
lcoe_se.jacket.Soilinputs=Soilinputs
lcoe_se.jacket.Soilinputs2=Soilinputs2 #Parked conditions
lcoe_se.jacket.Waterinputs=Waterinputs
lcoe_se.jacket.Windinputs=Windinputs
lcoe_se.jacket.RNA_F=RNA_F
lcoe_se.jacket.Waterinputs2=Waterinputs2 #Parked conditions
lcoe_se.jacket.Windinputs2=Windinputs2 #Parked conditions
lcoe_se.jacket.RNA_F2=RNA_F2 #Parked conditions
lcoe_se.jacket.Pileinputs=Pileinputs
lcoe_se.jacket.leginputs=leginputs
#lcoe_se.jacket.legbot_stmphin =legbot_stmphin
lcoe_se.jacket.Xbrcinputs=Xbrcinputs
lcoe_se.jacket.Mbrcinputs=Mbrcinputs
lcoe_se.jacket.Hbrcinputs=Hbrcinputs
lcoe_se.jacket.TPlumpinputs=TPlumpinputs
lcoe_se.jacket.TPinputs=TPinputs
lcoe_se.jacket.RNAinputs=RNAins
lcoe_se.jacket.RNAinputs2=RNAins2
lcoe_se.jacket.Twrinputs=Twrinputs
lcoe_se.jacket.TwrRigidTop=TwrRigidTop
lcoe_se.jacket.FrameAuxIns=FrameAuxIns
# === Run default assembly and print results
lcoe_se.run()
# ====
# === Print ===
print "Key Turbine Outputs for NREL 5 MW Reference Turbine"
print 'mass rotor blades:{0:.2f} (kg) '.format(lcoe_se.rotor.mass_all_blades)
print 'mass hub system: {0:.2f} (kg) '.format(lcoe_se.hub.hub_system_mass)
print 'mass nacelle: {0:.2f} (kg) '.format(lcoe_se.nacelle.nacelle_mass)
print 'mass tower: {0:.2f} (kg) '.format(lcoe_se.jacket.Tower.Twrouts.mass)
print 'maximum tip deflection: {0:.2f} (m) '.format(lcoe_se.maxdeflection.max_tip_deflection)
print 'ground clearance: {0:.2f} (m) '.format(lcoe_se.maxdeflection.ground_clearance)
print
print "Key Plant Outputs for wind plant with NREL 5 MW Turbine"
#print "LCOE: ${0:.4f} USD/kWh".format(lcoe_se.lcoe) # not in base output set (add to assembly output if desired)
print "COE: ${0:.4f} USD/kWh".format(lcoe_se.coe)
print
print "AEP per turbine: {0:.1f} kWh/turbine".format(lcoe_se.net_aep / lcoe_se.turbine_number)
print "Turbine Cost: ${0:.2f} USD".format(lcoe_se.turbine_cost)
print "BOS costs per turbine: ${0:.2f} USD/turbine".format(lcoe_se.bos_costs / lcoe_se.turbine_number)
print "OPEX per turbine: ${0:.2f} USD/turbine".format(lcoe_se.avg_annual_opex / lcoe_se.turbine_number)
Pileinputs.tpile = tpile
Pileinputs.Lp = Lp #[m] Embedment length
#Legs data
legmatin = MatInputs()
legmatin.matname = ([
'heavysteel', 'heavysteel', 'heavysteel', 'heavysteel'
])
#legmatin.E=np.array([2.0e11])
Dleg = np.array([1.5, 1.5, 1.5, 1.5, 1.5, 1.5])
tleg = 1.5 * np.array([0.0254]).repeat(Dleg.size)
leginputs = LegGeoInputs()
leginputs.legZbot = 1.0
leginputs.ndiv = 1
leginputs.legmatins = legmatin
leginputs.Dleg0 = Dleg[0]
leginputs.tleg0 = tleg[0]
legbot_stmphin = 1.5 #Distance from bottom of leg to second joint along z; must be>0
#Xbrc data
Xbrcmatin = MatInputs()
Xbrcmatin.matname = np.array(['heavysteel']).repeat(Jcktins.nbays)
#Xbrcmatin.E=np.array([ 2.2e11, 2.0e11,2.0e11,2.0e11,2.0e11])
Dbrc = np.array([1., 1., 1.0, 1.0, 1.0])
tbrc = np.array([1., 1., 1.0, 1.0, 1.0]) * 0.0254
Xbrcinputs = XBrcGeoInputs()
Xbrcinputs.Dbrc0 = Dbrc[0]
Xbrcinputs.tbrc0 = tbrc[0]
Xbrcinputs.ndiv = 2 #2
Pileinputs.ndiv=0 #3
Pileinputs.Dpile=Dpile
Pileinputs.tpile=tpile
Pileinputs.Lp=Lp #[m] Embedment length
#Legs data
legmatin=MatInputs()
legmatin.matname=(['heavysteel','heavysteel','heavysteel','heavysteel'])
#legmatin.E=np.array([2.0e11])
Dleg=np.array([1.5,1.5,1.5,1.5,1.5,1.5])
tleg=1.5*np.array([0.0254]).repeat(Dleg.size)
leginputs=LegGeoInputs()
leginputs.legZbot = 1.0
leginputs.ndiv=1
leginputs.legmatins=legmatin
leginputs.Dleg0=Dleg[0]
leginputs.tleg0=tleg[0]
legbot_stmphin =1.5 #Distance from bottom of leg to second joint along z; must be>0
#Xbrc data
Xbrcmatin=MatInputs()
Xbrcmatin.matname=np.array(['heavysteel']).repeat(Jcktins.nbays)
#Xbrcmatin.E=np.array([ 2.2e11, 2.0e11,2.0e11,2.0e11,2.0e11])
Dbrc=np.array([1.,1.,1.0,1.0,1.0])
tbrc=np.array([1.,1.,1.0,1.0,1.0])*0.0254
Xbrcinputs=XBrcGeoInputs()
Xbrcinputs.Dbrc0=Dbrc[0]
Xbrcinputs.tbrc0=tbrc[0]
Xbrcinputs.ndiv=2#2