def setUp(self):
self.om = opex_csm_assembly()
self.om.machine_rating = 5000.0
self.om.net_aep = 1701626526.28
self.om.sea_depth = 20.0
self.om.year = 2009
self.om.month = 12
self.om.turbine_number = 100
def setUp(self):
self.om = opex_csm_assembly()
self.om.machine_rating = 5000.0
self.om.net_aep = 1701626526.28
self.om.sea_depth = 20.0
self.om.year = 2009
self.om.month = 12
self.om.turbine_number = 100
def configure_lcoe_with_csm_opex(assembly):
"""
opex inputs:
availability = Float()
"""
assembly.replace('opex_a', opex_csm_assembly())
# connections to opex
assembly.connect('machine_rating', 'opex_a.machine_rating')
assembly.connect('sea_depth', 'opex_a.sea_depth')
assembly.connect('year', 'opex_a.year')
assembly.connect('month', 'opex_a.month')
assembly.connect('turbine_number', 'opex_a.turbine_number')
assembly.connect('aep_a.net_aep', 'opex_a.net_aep')
def configure(self):
"""
tcc_a inputs:
advanced_blade = Bool
offshore = Bool
assemblyCostMultiplier = Float
overheadCostMultiplier = Float
profitMultiplier = Float
transportMultiplier = Float
aep inputs:
array_losses = Float
other_losses = Float
fin inputs:
fixed_charge_rate = Float
construction_finance_rate = Float
tax_rate = Float
discount_rate = Float
construction_time = Float
bos inputs:
bos_multiplier = Float
inputs:
sea_depth
year
month
project lifetime
if csm opex additional inputs:
availability = Float()
if openwind opex additional inputs:
power_curve
rpm
ct
if with_landbos additional inputs:
voltage
distInter
terrain
layout
soil
"""
# configure base assembly
configure_extended_financial_analysis(self)
# putting replace statements here for now; TODO - openmdao bug
# replace BOS with either CSM or landbos
if self.with_landbos:
self.replace('bos_a', NREL_Land_BOSSE())
else:
self.replace('bos_a', bos_csm_assembly())
self.replace('tcc_a', Turbine_CostsSE())
if self.with_ecn_opex:
self.replace('opex_a', opex_ecn_assembly(ecn_file))
else:
self.replace('opex_a', opex_csm_assembly())
self.replace('aep_a', aep_weibull_assembly())
self.replace('fin_a', fin_csm_assembly())
# add TurbineSE assembly
configure_turbine(self, self.with_new_nacelle, self.flexible_blade, self.with_3pt_drive)
# replace TCC with turbine_costs
configure_lcoe_with_turb_costs(self)
# replace BOS with either CSM or landbos
if self.with_landbos:
configure_lcoe_with_landbos(self)
else:
configure_lcoe_with_csm_bos(self)
# replace AEP with weibull AEP (TODO: option for basic aep)
configure_lcoe_with_weibull_aep(self)
# replace OPEX with CSM or ECN opex and add AEP
if self.with_ecn_opex:
configure_lcoe_with_ecn_opex(self,ecn_file)
self.connect('opex_a.availability','aep_a.availability') # connecting here due to aep / opex reversal depending on model
else:
configure_lcoe_with_csm_opex(self)
self.add('availability',Float(0.94, iotype='in', desc='average annual availbility of wind turbines at plant', group='Plant_AEP'))
self.connect('availability','aep_a.availability') # connecting here due to aep / opex reversal depending on model
# replace Finance with CSM Finance
configure_lcoe_with_csm_fin(self)
def configure(self):
"""
tcc_a inputs:
advanced_blade = Bool
offshore = Bool
assemblyCostMultiplier = Float
overheadCostMultiplier = Float
profitMultiplier = Float
transportMultiplier = Float
aep inputs:
array_losses = Float
other_losses = Float
fin inputs:
fixed_charge_rate = Float
construction_finance_rate = Float
tax_rate = Float
discount_rate = Float
construction_time = Float
bos inputs:
bos_multiplier = Float
inputs:
sea_depth
year
month
project lifetime
if csm opex additional inputs:
availability = Float()
if openwind opex additional inputs:
power_curve
rpm
ct
if with_landbos additional inputs:
voltage
distInter
terrain
layout
soil
"""
# configure base assembly
configure_extended_financial_analysis(self)
# putting replace statements here for now; TODO - openmdao bug
# replace BOS with either CSM or landbos
if self.with_landbos:
self.replace('bos_a', NREL_Land_BOSSE())
else:
self.replace('bos_a', bos_csm_assembly())
self.replace('tcc_a', Turbine_CostsSE())
if self.with_ecn_opex:
self.replace('opex_a', opex_ecn_assembly(ecn_file))
else:
self.replace('opex_a', opex_csm_assembly())
self.replace('aep_a', aep_weibull_assembly())
self.replace('fin_a', fin_csm_assembly())
# add TurbineSE assembly
configure_turbine(self, self.with_new_nacelle, self.flexible_blade,
self.with_3pt_drive)
# replace TCC with turbine_costs
configure_lcoe_with_turb_costs(self)
# replace BOS with either CSM or landbos
if self.with_landbos:
configure_lcoe_with_landbos(self)
else:
configure_lcoe_with_csm_bos(self)
# replace AEP with weibull AEP (TODO: option for basic aep)
configure_lcoe_with_weibull_aep(self)
# replace OPEX with CSM or ECN opex and add AEP
if self.with_ecn_opex:
configure_lcoe_with_ecn_opex(self, ecn_file)
self.connect(
'opex_a.availability', 'aep_a.availability'
) # connecting here due to aep / opex reversal depending on model
else:
configure_lcoe_with_csm_opex(self)
self.add(
'availability',
Float(
0.94,
iotype='in',
desc='average annual availbility of wind turbines at plant'
))
self.connect(
'availability', 'aep_a.availability'
) # connecting here due to aep / opex reversal depending on model
# replace Finance with CSM Finance
configure_lcoe_with_csm_fin(self)
bos.turbine_cost = 5229222.77
bos.run()
print "Balance of Station Costs for an land-based wind plant with 100 NREL 5 MW turbines"
print "BOS cost land-based: ${0:.2f} USD".format(bos.bos_costs)
print "BOS cost per turbine: ${0:.2f} USD".format(bos.bos_costs / bos.turbine_number)
print
# 5 ----------
# 6 ----------
# A simple test of nrel_csm_om model
from plant_costsse.nrel_csm_opex.nrel_csm_opex import opex_csm_assembly
om = opex_csm_assembly()
# 6 ----------
# 7 ----------
# Ste input parameters
om.machine_rating = 5000.0 # Need to manipulate input or underlying component will not execute
om.net_aep = 1701626526.28
om.sea_depth = 20.0
om.year = 2009
om.month = 12
om.turbine_number = 100
# 7 ----------
# 8 ----------
def configure(self):
configure_extended_financial_analysis(self)
self.replace('tcc_a', tcc_csm_assembly())
self.replace('bos_a', bos_csm_assembly())
self.replace('opex_a', opex_csm_assembly())
self.replace('aep_a', aep_csm_assembly())
self.replace('fin_a', fin_csm_assembly())
# connect i/o to component and assembly inputs
# turbine configuration
# rotor
self.connect('rotor_diameter', ['aep_a.rotor_diameter', 'tcc_a.rotor_diameter', 'bos_a.rotor_diameter'])
self.connect('max_tip_speed', ['aep_a.max_tip_speed'])
self.connect('opt_tsr','aep_a.opt_tsr')
self.connect('cut_in_wind_speed','aep_a.cut_in_wind_speed')
self.connect('cut_out_wind_speed','aep_a.cut_out_wind_speed')
self.connect('altitude','aep_a.altitude')
self.connect('shear_exponent','aep_a.shear_exponent')
self.connect('wind_speed_50m','aep_a.wind_speed_50m')
self.connect('weibull_k','aep_a.weibull_k')
self.connect('soiling_losses','aep_a.soiling_losses')
self.connect('array_losses','aep_a.array_losses')
self.connect('availability','aep_a.availability')
self.connect('thrust_coefficient','aep_a.thrust_coefficient')
self.connect('blade_number','tcc_a.blade_number')
self.connect('advanced_blade','tcc_a.advanced_blade')
# drivetrain
self.connect('machine_rating', ['aep_a.machine_rating', 'tcc_a.machine_rating', 'bos_a.machine_rating', 'opex_a.machine_rating'])
self.connect('drivetrain_design', ['aep_a.drivetrain_design', 'tcc_a.drivetrain_design'])
self.connect('crane','tcc_a.crane')
self.connect('advanced_bedplate','tcc_a.advanced_bedplate')
# tower
self.connect('hub_height', ['aep_a.hub_height', 'tcc_a.hub_height', 'bos_a.hub_height'])
self.connect('advanced_tower','tcc_a.advanced_tower')
# plant configuration
# climate
self.connect('sea_depth', ['bos_a.sea_depth', 'opex_a.sea_depth', 'fin_a.sea_depth'])
self.connect('offshore','tcc_a.offshore')
# plant operation
self.connect('turbine_number', ['aep_a.turbine_number', 'bos_a.turbine_number', 'opex_a.turbine_number'])
# financial
self.connect('year', ['tcc_a.year', 'bos_a.year', 'opex_a.year'])
self.connect('month', ['tcc_a.month', 'bos_a.month', 'opex_a.month'])
self.connect('fixed_charge_rate','fin_a.fixed_charge_rate')
self.connect('construction_finance_rate','fin_a.construction_finance_rate')
self.connect('tax_rate','fin_a.tax_rate')
self.connect('discount_rate','fin_a.discount_rate')
self.connect('construction_time','fin_a.construction_time')
self.connect('project_lifetime','fin_a.project_lifetime')
# connections
self.connect('aep_a.rotor_thrust','tcc_a.rotor_thrust')
self.connect('aep_a.rotor_torque','tcc_a.rotor_torque')
self.connect('aep_a.net_aep', ['opex_a.net_aep'])
self.connect('tcc_a.turbine_cost','bos_a.turbine_cost')
# create passthroughs for key output variables of interest
# aep_a
self.connect('aep_a.rated_rotor_speed','rated_rotor_speed')
self.connect('aep_a.rated_wind_speed','rated_wind_speed')
self.connect('aep_a.rotor_thrust','rotor_thrust')
self.connect('aep_a.rotor_torque','rotor_torque')
self.connect('aep_a.power_curve','power_curve')
self.connect('aep_a.max_efficiency','max_efficiency')
self.connect('aep_a.gross_aep','gross_aep')
# tcc_a
self.connect('tcc_a.turbine_mass','turbine_mass')
# fin_a
self.connect('fin_a.lcoe','lcoe')
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 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):
configure_extended_financial_analysis(self)
self.replace('tcc_a', tcc_csm_assembly())
self.replace('bos_a', bos_csm_assembly())
self.replace('opex_a', opex_csm_assembly())
self.replace('aep_a', aep_csm_assembly())
self.replace('fin_a', fin_csm_assembly())
# connect i/o to component and assembly inputs
# turbine configuration
# rotor
self.connect('rotor_diameter', ['aep_a.rotor_diameter', 'tcc_a.rotor_diameter', 'bos_a.rotor_diameter'])
self.connect('max_tip_speed', ['aep_a.max_tip_speed'])
self.connect('max_power_coefficient', 'aep_a.max_power_coefficient')
self.connect('opt_tsr','aep_a.opt_tsr')
self.connect('cut_in_wind_speed','aep_a.cut_in_wind_speed')
self.connect('cut_out_wind_speed','aep_a.cut_out_wind_speed')
self.connect('altitude','aep_a.altitude')
self.connect('shear_exponent','aep_a.shear_exponent')
self.connect('wind_speed_50m','aep_a.wind_speed_50m')
self.connect('weibull_k','aep_a.weibull_k')
self.connect('soiling_losses','aep_a.soiling_losses')
self.connect('array_losses','aep_a.array_losses')
self.connect('availability','aep_a.availability')
self.connect('thrust_coefficient','aep_a.thrust_coefficient')
self.connect('max_efficiency', 'aep_a.max_efficiency')
self.connect('blade_number','tcc_a.blade_number')
self.connect('advanced_blade','tcc_a.advanced_blade')
# drivetrain
self.connect('machine_rating', ['aep_a.machine_rating', 'tcc_a.machine_rating', 'bos_a.machine_rating', 'opex_a.machine_rating'])
self.connect('drivetrain_design', ['aep_a.drivetrain_design', 'tcc_a.drivetrain_design'])
self.connect('crane','tcc_a.crane')
self.connect('advanced_bedplate','tcc_a.advanced_bedplate')
# tower
self.connect('hub_height', ['aep_a.hub_height', 'tcc_a.hub_height', 'bos_a.hub_height'])
self.connect('advanced_tower','tcc_a.advanced_tower')
# plant configuration
# climate
self.connect('sea_depth', ['bos_a.sea_depth', 'opex_a.sea_depth', 'fin_a.sea_depth'])
self.connect('offshore','tcc_a.offshore')
# plant operation
self.connect('turbine_number', ['aep_a.turbine_number', 'bos_a.turbine_number', 'opex_a.turbine_number'])
# financial
self.connect('year', ['tcc_a.year', 'bos_a.year', 'opex_a.year'])
self.connect('month', ['tcc_a.month', 'bos_a.month', 'opex_a.month'])
self.connect('fixed_charge_rate','fin_a.fixed_charge_rate')
self.connect('construction_finance_rate','fin_a.construction_finance_rate')
self.connect('tax_rate','fin_a.tax_rate')
self.connect('discount_rate','fin_a.discount_rate')
self.connect('construction_time','fin_a.construction_time')
self.connect('project_lifetime','fin_a.project_lifetime')
# connections
self.connect('aep_a.rotor_thrust','tcc_a.rotor_thrust')
self.connect('aep_a.rotor_torque','tcc_a.rotor_torque')
self.connect('aep_a.net_aep', ['opex_a.net_aep'])
self.connect('tcc_a.turbine_cost','bos_a.turbine_cost')
# create passthroughs for key output variables of interest
# aep_a
self.connect('aep_a.rated_rotor_speed','rated_rotor_speed')
self.connect('aep_a.rated_wind_speed','rated_wind_speed')
self.connect('aep_a.rotor_thrust','rotor_thrust')
self.connect('aep_a.rotor_torque','rotor_torque')
self.connect('aep_a.power_curve','power_curve')
#self.connect('aep_a.max_efficiency','max_efficiency')
self.connect('aep_a.gross_aep','gross_aep')
self.connect('aep_a.capacity_factor','capacity_factor')
# tcc_a
self.connect('tcc_a.turbine_mass','turbine_mass')
# fin_a
self.connect('fin_a.lcoe','lcoe')
def configure(self):
configure_extended_financial_analysis(self)
self.replace("tcc_a", tcc_csm_assembly())
self.replace("bos_a", bos_csm_assembly())
self.replace("opex_a", opex_csm_assembly())
self.replace("aep_a", aep_csm_assembly())
self.replace("fin_a", fin_csm_assembly())
# connect i/o to component and assembly inputs
# turbine configuration
# rotor
self.connect("rotor_diameter", ["aep_a.rotor_diameter", "tcc_a.rotor_diameter", "bos_a.rotor_diameter"])
self.connect("max_tip_speed", ["aep_a.max_tip_speed"])
self.connect("max_power_coefficient", "aep_a.max_power_coefficient")
self.connect("opt_tsr", "aep_a.opt_tsr")
self.connect("cut_in_wind_speed", "aep_a.cut_in_wind_speed")
self.connect("cut_out_wind_speed", "aep_a.cut_out_wind_speed")
self.connect("altitude", "aep_a.altitude")
self.connect("shear_exponent", "aep_a.shear_exponent")
self.connect("wind_speed_50m", "aep_a.wind_speed_50m")
self.connect("weibull_k", "aep_a.weibull_k")
self.connect("soiling_losses", "aep_a.soiling_losses")
self.connect("array_losses", "aep_a.array_losses")
self.connect("availability", "aep_a.availability")
self.connect("thrust_coefficient", "aep_a.thrust_coefficient")
self.connect("max_efficiency", "aep_a.max_efficiency")
self.connect("blade_number", "tcc_a.blade_number")
self.connect("advanced_blade", "tcc_a.advanced_blade")
# drivetrain
self.connect(
"machine_rating",
["aep_a.machine_rating", "tcc_a.machine_rating", "bos_a.machine_rating", "opex_a.machine_rating"],
)
self.connect("drivetrain_design", ["aep_a.drivetrain_design", "tcc_a.drivetrain_design"])
self.connect("crane", "tcc_a.crane")
self.connect("advanced_bedplate", "tcc_a.advanced_bedplate")
# tower
self.connect("hub_height", ["aep_a.hub_height", "tcc_a.hub_height", "bos_a.hub_height"])
self.connect("advanced_tower", "tcc_a.advanced_tower")
# plant configuration
# climate
self.connect("sea_depth", ["bos_a.sea_depth", "opex_a.sea_depth", "fin_a.sea_depth"])
self.connect("offshore", "tcc_a.offshore")
# plant operation
self.connect("turbine_number", ["aep_a.turbine_number", "bos_a.turbine_number", "opex_a.turbine_number"])
# financial
self.connect("year", ["tcc_a.year", "bos_a.year", "opex_a.year"])
self.connect("month", ["tcc_a.month", "bos_a.month", "opex_a.month"])
self.connect("fixed_charge_rate", "fin_a.fixed_charge_rate")
self.connect("construction_finance_rate", "fin_a.construction_finance_rate")
self.connect("tax_rate", "fin_a.tax_rate")
self.connect("discount_rate", "fin_a.discount_rate")
self.connect("construction_time", "fin_a.construction_time")
self.connect("project_lifetime", "fin_a.project_lifetime")
# connections
self.connect("aep_a.rotor_thrust", "tcc_a.rotor_thrust")
self.connect("aep_a.rotor_torque", "tcc_a.rotor_torque")
self.connect("aep_a.net_aep", ["opex_a.net_aep"])
self.connect("tcc_a.turbine_cost", "bos_a.turbine_cost")
# create passthroughs for key output variables of interest
# aep_a
self.connect("aep_a.rated_rotor_speed", "rated_rotor_speed")
self.connect("aep_a.rated_wind_speed", "rated_wind_speed")
self.connect("aep_a.rotor_thrust", "rotor_thrust")
self.connect("aep_a.rotor_torque", "rotor_torque")
self.connect("aep_a.power_curve", "power_curve")
# self.connect('aep_a.max_efficiency','max_efficiency')
self.connect("aep_a.gross_aep", "gross_aep")
self.connect("aep_a.capacity_factor", "capacity_factor")
# tcc_a
self.connect("tcc_a.turbine_mass", "turbine_mass")
# fin_a
self.connect("fin_a.lcoe", "lcoe")
