class Test_HubSE(unittest.TestCase):
def setUp(self):
self.hub = HubSE()
self.hub = HubSE()
self.hub.rotor_diameter = 126.0 # m
self.hub.blade_number = 3
self.hub.blade_root_diameter = 3.542
self.hub.machine_rating = 5000.0
self.hub.blade_mass = 17740.0 # kg
AirDensity= 1.225 # kg/(m^3)
Solidity = 0.0517
RatedWindSpeed = 11.05 # m/s
self.hub.rotor_bending_moment = (3.06 * pi / 8) * AirDensity * (RatedWindSpeed ** 2) * (Solidity * (self.hub.rotor_diameter ** 3)) / self.hub.blade_number
self.hub.gamma = 5.0
self.hub.MB1_location = np.array([-3.2, 0.0, 1.0])
def test_functionality(self):
self.hub.run()
self.assertEqual(round(self.hub.hub_system_mass,1), 45025.7)
def setUp(self):
self.hub = HubSE()
self.hub = HubSE()
self.hub.rotor_diameter = 126.0 # m
self.hub.blade_number = 3
self.hub.blade_root_diameter = 3.542
self.hub.machine_rating = 5000.0
self.hub.blade_mass = 17740.0 # kg
AirDensity= 1.225 # kg/(m^3)
Solidity = 0.0517
RatedWindSpeed = 11.05 # m/s
self.hub.rotor_bending_moment = (3.06 * pi / 8) * AirDensity * (RatedWindSpeed ** 2) * (Solidity * (self.hub.rotor_diameter ** 3)) / self.hub.blade_number
self.hub.gamma = 5.0
self.hub.MB1_location = np.array([-3.2, 0.0, 1.0])
def configure_turbine_with_jacket(assembly,
with_new_nacelle=False,
flexible_blade=False,
with_3pt_drive=False):
"""a stand-alone configure method to allow for flatter assemblies
Parameters
----------
assembly : Assembly
an openmdao assembly to be configured
with_new_nacelle : bool
False uses the default implementation, True uses an experimental implementation designed
to smooth out discontinities making in amenable for gradient-based optimization
flexible_blade : bool
if True, internally solves the coupled aero/structural deflection using fixed point iteration.
Note that the coupling is currently only in the flapwise deflection, and is primarily
only important for highly flexible blades. If False, the aero loads are passed
to the structure but there is no further iteration.
"""
# --- general turbine configuration inputs---
assembly.add(
'rho',
Float(1.225,
iotype='in',
units='kg/m**3',
desc='density of air',
deriv_ignore=True))
assembly.add(
'mu',
Float(1.81206e-5,
iotype='in',
units='kg/m/s',
desc='dynamic viscosity of air',
deriv_ignore=True))
assembly.add(
'shear_exponent',
Float(0.2, iotype='in', desc='shear exponent', deriv_ignore=True))
assembly.add('hub_height',
Float(90.0, iotype='in', units='m', desc='hub height'))
assembly.add(
'turbine_class',
Enum('I', ('I', 'II', 'III'), iotype='in', desc='IEC turbine class'))
assembly.add(
'turbulence_class',
Enum('B', ('A', 'B', 'C'),
iotype='in',
desc='IEC turbulence class class'))
assembly.add(
'g',
Float(9.81,
iotype='in',
units='m/s**2',
desc='acceleration of gravity',
deriv_ignore=True))
assembly.add(
'cdf_reference_height_wind_speed',
Float(
90.0,
iotype='in',
desc=
'reference hub height for IEC wind speed (used in CDF calculation)'
))
assembly.add('downwind',
Bool(False, iotype='in', desc='flag if rotor is downwind'))
assembly.add('tower_dt',
Float(iotype='in', units='m',
desc='tower top diameter')) # update for jacket
assembly.add('generator_speed',
Float(iotype='in', units='rpm', desc='generator speed'))
assembly.add(
'machine_rating',
Float(5000.0, units='kW', iotype='in', desc='machine rated power'))
assembly.add(
'rna_weightM',
Bool(True,
iotype='in',
desc='flag to consider or not the RNA weight effect on Moment'))
assembly.add('rotor', RotorSE())
if with_new_nacelle:
assembly.add('hub', HubSE())
if with_3pt_drive:
assembly.add('nacelle', Drive3pt())
else:
assembly.add('nacelle', Drive4pt())
else:
assembly.add('nacelle', DriveWPACT())
assembly.add('hub', HubWPACT())
assembly.add('rna', RNAMass())
assembly.add('rotorloads1', RotorLoads())
assembly.add('rotorloads2', RotorLoads())
assembly.add('jacket', JacketSE())
assembly.add('maxdeflection', MaxTipDeflection())
if flexible_blade:
assembly.add('fpi', FixedPointIterator())
assembly.fpi.workflow.add(['rotor'])
assembly.fpi.add_parameter('rotor.delta_precurve_sub',
low=-1.e99,
high=1.e99)
assembly.fpi.add_parameter('rotor.delta_bladeLength',
low=-1.e99,
high=1.e99)
assembly.fpi.add_constraint(
'rotor.delta_precurve_sub = rotor.delta_precurve_sub_out')
assembly.fpi.add_constraint(
'rotor.delta_bladeLength = rotor.delta_bladeLength_out')
assembly.fpi.max_iteration = 20
assembly.fpi.tolerance = 1e-8
assembly.driver.workflow.add(['fpi'])
else:
assembly.driver.workflow.add(['rotor'])
assembly.driver.workflow.add([
'hub', 'nacelle', 'jacket', 'maxdeflection', 'rna', 'rotorloads1',
'rotorloads2'
])
# TODO: rotor drivetrain design should be connected to nacelle drivetrain design
# connections to rotor
assembly.connect('machine_rating', 'rotor.control.ratedPower')
assembly.connect('rho', 'rotor.rho')
assembly.connect('mu', 'rotor.mu')
assembly.connect('shear_exponent', 'rotor.shearExp')
assembly.connect('hub_height', 'rotor.hubHt')
assembly.connect('turbine_class', 'rotor.turbine_class')
assembly.connect('turbulence_class', 'rotor.turbulence_class')
assembly.connect('g', 'rotor.g')
assembly.connect('cdf_reference_height_wind_speed',
'rotor.cdf_reference_height_wind_speed')
# connections to hub
assembly.connect('rotor.mass_one_blade', 'hub.blade_mass')
assembly.connect('rotor.root_bending_moment', 'hub.rotor_bending_moment')
assembly.connect('rotor.diameter', 'hub.rotor_diameter')
assembly.connect('rotor.hub_diameter', 'hub.blade_root_diameter')
assembly.connect('rotor.nBlades', 'hub.blade_number')
if with_new_nacelle:
assembly.connect('nacelle.MB1_location', 'hub.MB1_location')
assembly.connect('rotor.tilt', 'hub.gamma')
assembly.connect('nacelle.L_rb', 'hub.L_rb')
# connections to nacelle #TODO: fatigue option variables
assembly.connect('rotor.diameter', 'nacelle.rotor_diameter')
if not with_new_nacelle:
assembly.connect(
'rotor.mass_all_blades + hub.hub_system_mass', 'nacelle.rotor_mass'
) #DODO: circular dependency if using DriveSE (nacelle csm --> hub, hub mass --> nacelle)
if with_new_nacelle:
assembly.connect('rotor.nBlades', 'nacelle.blade_number')
assembly.connect('rotor.tilt', 'nacelle.shaft_angle')
assembly.connect('333.3 * machine_rating / 1000.0',
'nacelle.shrink_disc_mass')
assembly.connect('1.5 * rotor.ratedConditions.Q', 'nacelle.rotor_torque')
assembly.connect('rotor.ratedConditions.T', 'nacelle.rotor_thrust')
assembly.connect('rotor.ratedConditions.Omega', 'nacelle.rotor_speed')
assembly.connect('machine_rating', 'nacelle.machine_rating')
assembly.connect('rotor.root_bending_moment',
'nacelle.rotor_bending_moment')
assembly.connect('generator_speed/rotor.ratedConditions.Omega',
'nacelle.gear_ratio')
'''if with_new_nacelle:
assembly.connect('rotor.g', 'nacelle.g')''' # Only drive smooth taking g from rotor; TODO: update when drive_smooth is updated
assembly.connect(
'tower_dt', 'nacelle.tower_top_diameter'
) # OpenMDAO circular dependency issue # update for jacket input
# connections to rna
assembly.connect('rotor.mass_all_blades', 'rna.blades_mass')
assembly.connect('rotor.I_all_blades', 'rna.blades_I')
assembly.connect('hub.hub_system_mass', 'rna.hub_mass')
assembly.connect('hub.hub_system_cm', 'rna.hub_cm')
assembly.connect('hub.hub_system_I', 'rna.hub_I')
assembly.connect('nacelle.nacelle_mass', 'rna.nac_mass')
assembly.connect('nacelle.nacelle_cm', 'rna.nac_cm')
assembly.connect('nacelle.nacelle_I', 'rna.nac_I')
# connections to rotorloads1
assembly.connect('downwind', 'rotorloads1.downwind')
assembly.connect('rna_weightM', 'rotorloads1.rna_weightM')
assembly.connect('1.8 * rotor.ratedConditions.T', 'rotorloads1.F[0]')
assembly.connect('rotor.ratedConditions.Q', 'rotorloads1.M[0]')
assembly.connect('hub.hub_system_cm', 'rotorloads1.r_hub')
assembly.connect('rna.rna_cm', 'rotorloads1.rna_cm')
assembly.connect('rotor.tilt', 'rotorloads1.tilt')
assembly.connect('g', 'rotorloads1.g')
assembly.connect('rna.rna_mass', 'rotorloads1.m_RNA')
# connections to rotorloads2
assembly.connect('downwind', 'rotorloads2.downwind')
assembly.connect('rna_weightM', 'rotorloads2.rna_weightM')
assembly.connect('rotor.T_extreme', 'rotorloads2.F[0]')
assembly.connect('rotor.Q_extreme', 'rotorloads2.M[0]')
assembly.connect('hub.hub_system_cm', 'rotorloads2.r_hub')
assembly.connect('rna.rna_cm', 'rotorloads2.rna_cm')
assembly.connect('rotor.tilt', 'rotorloads2.tilt')
assembly.connect('g', 'rotorloads2.g')
assembly.connect('rna.rna_mass', 'rotorloads2.m_RNA')
# connections to jacket
assembly.connect('rho', 'jacket.Windinputs.rho') # jacket input
assembly.connect('mu', 'jacket.Windinputs.mu') # jacket input
assembly.connect('-g', 'jacket.FrameAuxIns.gvector[2]') # jacket input
assembly.connect('hub_height', 'jacket.Windinputs.HH') # jacket input
assembly.connect('tower_dt', 'jacket.Twrinputs.Dt') # jacket input
assembly.connect('rotor.yaw', 'jacket.RNAinputs.yawangle') # jacket input
#assembly.connect('hub_height - nacelle.nacelle_cm[2]', 'jacket.Twrinputs.Htwr') # jacket input; TODO: probably irrelevant for this purpose, tower length is now determined in jacket
assembly.connect('rna.rna_mass', 'jacket.RNAinputs.mass') # jacket input
assembly.connect('rna.rna_cm', 'jacket.RNAinputs.CMoff') # jacket input
assembly.connect('rna.rna_I_TT', 'jacket.RNAinputs.I') # jacket input
# Rated rotor loads (Option 1)
assembly.connect('rotor.ratedConditions.V',
'jacket.Windinputs.U50HH') # jacket input
assembly.connect('rotorloads1.top_F', 'jacket.RNA_F[0:3]') # jacket input
assembly.connect('rotorloads1.top_M', 'jacket.RNA_F[3:6]') # jacket input
# Survival rotor loads (Option 2)
#assembly.connect('rotor.V_extreme', 'tower.Windinputs.U50HH') # jacket input
#assembly.connect('rotorloads2.top_F', 'jacket.RNA_F') # jacket input
#assembly.connect('rotorloads2.top_M', 'jacket.RNA_M') # jacket input
# connections to maxdeflection
assembly.connect('rotor.Rtip', 'maxdeflection.Rtip')
assembly.connect('rotor.precurveTip', 'maxdeflection.precurveTip')
assembly.connect('rotor.presweepTip', 'maxdeflection.presweepTip')
assembly.connect('rotor.precone', 'maxdeflection.precone')
assembly.connect('rotor.tilt', 'maxdeflection.tilt')
assembly.connect('hub.hub_system_cm', 'maxdeflection.hub_tt')
assembly.connect(
'jacket.Twrouts.nodes[2,:]', 'maxdeflection.tower_z'
) # jacket input, had to make array dimensions explicit on instantiation for this connect to work ---THIS is the z at CMzoff, not necessarily the top flange
assembly.connect('jacket.Twrouts', 'maxdeflection.Twrouts'
) # TODO: jacket input - doesnt recognize logobj
assembly.connect('jacket.Twrouts.Htwr',
'maxdeflection.towerHt') # jacket input
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()
print "Estimate of Hub Component Sizes for the Baseline 5 MW Reference Turbine"
print "Hub Components"
print ' Hub: {0:8.1f} kg'.format(hubS.hub.mass) # 31644.47
print ' Pitch system: {0:8.1f} kg'.format(hubS.pitchSystem.mass) # 17003.98
print ' Nose cone: {0:8.1f} kg'.format(hubS.spinner.mass) # 1810.50
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()
print "Estimate of Hub Component Sizes for the Baseline 5 MW Reference Turbine"
print "Hub Components"
print ' Hub: {0:8.1f} kg'.format(hubS.hub.mass) # 31644.47
print ' Pitch system: {0:8.1f} kg'.format(hubS.pitchSystem.mass) # 17003.98
print ' Nose cone: {0:8.1f} kg'.format(hubS.spinner.mass) # 1810.50
print 'ratedConditions.T =', rotor.ratedConditions.T
print 'ratedConditions.Q =', rotor.ratedConditions.Q
print 'Rated Power =', rotor.control.ratedPower/1000
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
################################################################################
### 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.B
hubS.blade_root_diameter = 3.542
hubS.blade_root_diameter = 2.5
hubS.L_rb = rotor.Rhub
hubS.MB1_location = np.array([-0.5, 0.0, 0.0])
hubS.machine_rating = rotor.control.ratedPower/1000
hubS.run()
print "Estimate of Hub Component Sizes for the Baseline 5 MW Reference Turbine"
print "Hub Components"
print ' Hub: {0:8.1f} kg'.format(hubS.hub.mass) # 31644.47
print ' Pitch system: {0:8.1f} kg'.format(hubS.pitchSystem.mass) # 17003.98
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_turbine(assembly,
with_new_nacelle=True,
flexible_blade=False,
with_3pt_drive=False):
"""a stand-alone configure method to allow for flatter assemblies
Parameters
----------
assembly : Assembly
an openmdao assembly to be configured
with_new_nacelle : bool
False uses the default implementation, True uses an experimental implementation designed
to smooth out discontinities making in amenable for gradient-based optimization
flexible_blade : bool
if True, internally solves the coupled aero/structural deflection using fixed point iteration.
Note that the coupling is currently only in the flapwise deflection, and is primarily
only important for highly flexible blades. If False, the aero loads are passed
to the structure but there is no further iteration.
"""
#SEAM variables ----------------------------------
#d2e = Float(0.73, iotype='in', desc='Dollars to Euro ratio'
assembly.add(
'rated_power',
Float(3000.,
iotype='in',
units='kW',
desc='Turbine rated power',
group='Global'))
assembly.add(
'hub_height',
Float(100., iotype='in', units='m', desc='Hub height', group='Global'))
assembly.add(
'rotor_diameter',
Float(110.,
iotype='in',
units='m',
desc='Rotor diameter',
group='Global'))
# assembly.add('site_type',Enum('onshore', values=('onshore', 'offshore'), iotype='in', desc='Site type', group='Global'))
assembly.add(
'tower_bottom_diameter',
Float(4., iotype='in', desc='Tower bottom diameter', group='Global'))
assembly.add(
'tower_top_diameter',
Float(2., iotype='in', desc='Tower top diameter', group='Global'))
assembly.add('project_lifetime',
Float(iotype='in', desc='Operating years', group='Global'))
assembly.add(
'rho_steel',
Float(7.8e3, iotype='in', desc='density of steel', group='Tower'))
assembly.add(
'lifetime_cycles',
Float(1.e7,
iotype='in',
desc='Equivalent lifetime cycles',
group='Rotor'))
assembly.add(
'stress_limit_extreme_tower',
Float(iotype='in',
units='MPa',
desc='Tower ultimate strength',
group='Tower'))
assembly.add(
'stress_limit_fatigue_tower',
Float(iotype='in',
units='MPa',
desc='Tower fatigue strength',
group='Tower'))
assembly.add(
'safety_factor_tower',
Float(iotype='in', desc='Tower loads safety factor', group='Tower'))
assembly.add('PMtarget_tower',
Float(1., iotype='in', desc='', group='Tower'))
assembly.add(
'wohler_exponent_tower',
Float(4.,
iotype='in',
desc='Tower fatigue Wohler exponent',
group='Tower'))
assembly.add('tower_z', Array(iotype='out', desc='Tower discretization'))
assembly.add('tower_wall_thickness',
Array(iotype='out', units='m', desc='Tower wall thickness'))
assembly.add('tower_mass',
Float(iotype='out', units='kg', desc='Tower mass'))
assembly.add(
'tsr',
Float(iotype='in',
units='m',
desc='Design tip speed ratio',
group='Aero'))
assembly.add(
'F', Float(iotype='in', desc='Rotor power loss factor', group='Aero'))
assembly.add(
'wohler_exponent_blade_flap',
Float(iotype='in', desc='Wohler Exponent blade flap', group='Rotor'))
assembly.add('nSigma4fatFlap', Float(iotype='in', desc='', group='Loads'))
assembly.add('nSigma4fatTower', Float(iotype='in', desc='', group='Loads'))
assembly.add('dLoad_dU_factor_flap',
Float(iotype='in', desc='', group='Loads'))
assembly.add('dLoad_dU_factor_tower',
Float(iotype='in', desc='', group='Loads'))
assembly.add(
'blade_edge_dynload_factor_ext',
Float(iotype='in',
desc='Extreme dynamic edgewise loads factor',
group='Loads'))
assembly.add(
'blade_edge_dynload_factor_fat',
Float(iotype='in',
desc='Fatigue dynamic edgewise loads factor',
group='Loads'))
assembly.add('PMtarget_blades',
Float(1., iotype='in', desc='', group='Rotor'))
assembly.add('max_tipspeed',
Float(iotype='in', desc='Maximum tip speed', group='Aero'))
assembly.add(
'n_wsp',
Int(iotype='in', desc='Number of wind speed bins', group='Aero'))
assembly.add(
'min_wsp',
Float(0.0,
iotype='in',
units='m/s',
desc='min wind speed',
group='Aero'))
assembly.add(
'max_wsp',
Float(iotype='in', units='m/s', desc='max wind speed', group='Aero'))
assembly.add(
'turbulence_int',
Float(iotype='in',
desc='Reference turbulence intensity',
group='Plant_AEP'))
# assembly.add('WeibullInput', Bool(True, iotype='in', desc='Flag for Weibull input', group='AEP'))
assembly.add(
'weibull_C',
Float(iotype='in',
units='m/s',
desc='Weibull scale factor',
group='AEP'))
assembly.add(
'weibull_k',
Float(iotype='in', desc='Weibull shape or form factor', group='AEP'))
assembly.add(
'blade_sections',
Int(iotype='in', desc='number of sections along blade', group='Rotor'))
assembly.add(
'wohler_exponent_blade_flap',
Float(iotype='in',
desc='Blade flap fatigue Wohler exponent',
group='Rotor'))
assembly.add(
'MaxChordrR',
Float(iotype='in',
units='m',
desc='Spanwise position of maximum chord',
group='Rotor'))
assembly.add(
'tif_blade_root_flap_ext',
Float(1.,
iotype='in',
desc='Technology improvement factor flap extreme',
group='Rotor'))
assembly.add(
'tif_blade_root_edge_ext',
Float(1.,
iotype='in',
desc='Technology improvement factor edge extreme',
group='Rotor'))
assembly.add(
'tif_blade_root_flap_fat',
Float(1.,
iotype='in',
desc='Technology improvement factor flap LEQ',
group='Rotor'))
assembly.add(
'sc_frac_flap',
Float(iotype='in', desc='spar cap fraction of chord', group='Rotor'))
assembly.add(
'sc_frac_edge',
Float(iotype='in',
desc='spar cap fraction of thickness',
group='Rotor'))
assembly.add(
'safety_factor_blade',
Float(iotype='in', desc='Blade loads safety factor', group='Rotor'))
assembly.add(
'stress_limit_extreme_blade',
Float(iotype='in',
units='MPa',
desc='Blade ultimate strength',
group='Rotor'))
assembly.add(
'stress_limit_fatigue_blade',
Float(iotype='in',
units='MPa',
desc='Blade fatigue strength',
group='Rotor'))
assembly.add(
'AddWeightFactorBlade',
Float(iotype='in',
desc='Additional weight factor for blade shell',
group='Rotor'))
assembly.add(
'blade_material_density',
Float(iotype='in',
units='kg/m**3',
desc='Average density of blade materials',
group='Rotor'))
assembly.add('blade_mass',
Float(iotype='out', units='kg', desc='Blade mass'))
# assembly.add('mean_wsp', Float(iotype = 'in', units = 'm/s', desc = 'mean wind speed', group='Aero')) # [m/s]
assembly.add('air_density',
Float(iotype='in',
units='kg/m**3',
desc='density of air',
group='Plant_AEP')) # [kg / m^3]
assembly.add('max_Cp', Float(iotype='in', desc='max CP', group='Aero'))
assembly.add(
'gearloss_const',
Float(iotype='in', desc='Gear loss constant', group='Drivetrain'))
assembly.add(
'gearloss_var',
Float(iotype='in', desc='Gear loss variable', group='Drivetrain'))
assembly.add('genloss',
Float(iotype='in', desc='Generator loss', group='Drivetrain'))
assembly.add('convloss',
Float(iotype='in', desc='Converter loss', group='Drivetrain'))
# Outputs
assembly.add(
'rated_wind_speed',
Float(units='m / s', iotype='out', desc='wind speed for rated power'))
assembly.add(
'ideal_power_curve',
Array(iotype='out',
units='kW',
desc='total power before losses and turbulence'))
assembly.add(
'power_curve',
Array(iotype='out',
units='kW',
desc='total power including losses and turbulence'))
assembly.add(
'wind_curve',
Array(iotype='out',
units='m/s',
desc='wind curve associated with power curve'))
assembly.add(
'aep',
Float(iotype='out',
units='mW*h',
desc='Annual energy production in mWh'))
assembly.add(
'total_aep',
Float(iotype='out',
units='mW*h',
desc='AEP for total years of production'))
# END SEAM Variables ----------------------
# Add SEAM components and connections
assembly.add('loads', SEAMLoads())
assembly.add('tower_design', SEAMTower(21))
assembly.add('blade_design', SEAMBladeStructure())
assembly.add('aep_calc', SEAM_PowerCurve())
assembly.driver.workflow.add(
['loads', 'tower_design', 'blade_design', 'aep_calc'])
assembly.connect('loads.tower_bottom_moment_max',
'tower_design.tower_bottom_moment_max')
assembly.connect('loads.tower_bottom_moment_leq',
'tower_design.tower_bottom_moment_leq')
assembly.connect('loads.blade_root_flap_max',
'blade_design.blade_root_flap_max')
assembly.connect('loads.blade_root_edge_max',
'blade_design.blade_root_edge_max')
assembly.connect('loads.blade_root_flap_leq',
'blade_design.blade_root_flap_leq')
assembly.connect('loads.blade_root_edge_leq',
'blade_design.blade_root_edge_leq')
connect_io(assembly, assembly.aep_calc)
connect_io(assembly, assembly.loads)
connect_io(assembly, assembly.tower_design)
connect_io(assembly, assembly.blade_design)
# End SEAM add components and connections -------------
if with_new_nacelle:
assembly.add('hub', HubSE())
assembly.add('hubSystem', Hub_System_Adder_drive())
if with_3pt_drive:
assembly.add('nacelle', Drive3pt())
else:
assembly.add('nacelle', Drive4pt())
else:
assembly.add('nacelle', DriveWPACT())
assembly.add('hub', HubWPACT())
assembly.driver.workflow.add(['hub', 'nacelle'])
if with_new_nacelle:
assembly.driver.workflow.add(['hubSystem'])
# connections to hub and hub system
assembly.connect('blade_design.blade_mass', 'hub.blade_mass')
assembly.connect('loads.blade_root_flap_max', 'hub.rotor_bending_moment')
assembly.connect('rotor_diameter', ['hub.rotor_diameter'])
assembly.connect('blade_design.blade_root_diameter',
'hub.blade_root_diameter')
assembly.add('blade_number',
Int(3, iotype='in', desc='number of blades', group='Aero'))
assembly.connect('blade_number', 'hub.blade_number')
if with_new_nacelle:
assembly.connect('rated_power', 'hub.machine_rating')
assembly.connect('rotor_diameter', ['hubSystem.rotor_diameter'])
assembly.connect('nacelle.MB1_location',
'hubSystem.MB1_location') # TODO: bearing locations
assembly.connect('nacelle.L_rb', 'hubSystem.L_rb')
assembly.add('rotor_tilt',
Float(5.0, iotype='in', desc='rotor tilt', group='Rotor'))
assembly.connect('rotor_tilt', 'hubSystem.shaft_angle')
assembly.connect('hub.hub_diameter', 'hubSystem.hub_diameter')
assembly.connect('hub.hub_thickness', 'hubSystem.hub_thickness')
assembly.connect('hub.hub_mass', 'hubSystem.hub_mass')
assembly.connect('hub.spinner_mass', 'hubSystem.spinner_mass')
assembly.connect('hub.pitch_system_mass',
'hubSystem.pitch_system_mass')
# connections to nacelle #TODO: fatigue option variables
assembly.connect('rotor_diameter', 'nacelle.rotor_diameter')
assembly.connect('1.5 * aep_calc.rated_torque', 'nacelle.rotor_torque')
assembly.connect('loads.max_thrust', 'nacelle.rotor_thrust')
assembly.connect('aep_calc.rated_speed', 'nacelle.rotor_speed')
assembly.connect('rated_power', 'nacelle.machine_rating')
assembly.add('generator_speed',
Float(1173.7,
iotype='in',
units='rpm',
desc='speed of generator',
group='Drivetrain')) # - should be in nacelle
assembly.connect('generator_speed/aep_calc.rated_speed',
'nacelle.gear_ratio')
assembly.connect('tower_top_diameter', 'nacelle.tower_top_diameter')
assembly.connect(
'blade_number * blade_design.blade_mass + hub.hub_system_mass',
'nacelle.rotor_mass') # assuming not already in rotor force / moments
# variable connections for new nacelle
if with_new_nacelle:
assembly.connect('blade_number', 'nacelle.blade_number')
assembly.connect('rotor_tilt', 'nacelle.shaft_angle')
assembly.connect('333.3 * rated_power / 1000.0',
'nacelle.shrink_disc_mass')
assembly.connect('blade_design.blade_root_diameter',
'nacelle.blade_root_diameter')
#moments - ignoring for now (nacelle will use internal defaults)
#assembly.connect('rotor.Mxyz_0','moments.b1')
#assembly.connect('rotor.Mxyz_120','moments.b2')
#assembly.connect('rotor.Mxyz_240','moments.b3')
#assembly.connect('rotor.Pitch','moments.pitch_angle')
#assembly.connect('rotor.TotalCone','moments.cone_angle')
assembly.connect('1.5 * aep_calc.rated_torque',
'nacelle.rotor_bending_moment_x'
) #accounted for in ratedConditions.Q
#assembly.connect('moments.My','nacelle.rotor_bending_moment_y')
#assembly.connect('moments.Mz','nacelle.rotor_bending_moment_z')
#forces - ignoring for now (nacelle will use internal defaults)
#assembly.connect('rotor.Fxyz_0','forces.b1')
#assembly.connect('rotor.Fxyz_120','forces.b2')
#assembly.connect('rotor.Fxyz_240','forces.b3')
#assembly.connect('rotor.Pitch','forces.pitch_angle')
#assembly.connect('rotor.TotalCone','forces.cone_angle')
assembly.connect('loads.max_thrust', 'nacelle.rotor_force_x')
# 1 --------- from math import pi import numpy as np from drivese.hub import HubSE from drivese.drive import Drive4pt # 1 --------- # 2 --------- # simple test of hub model # NREL 5 MW turbine hubS = HubSE() hubS.rotor_diameter = 126.0 # m hubS.blade_number = 3 hubS.blade_root_diameter = 3.542 hubS.L_rb = 0.5 hubS.gamma = 5.0 hubS.MB1_location = np.array([-0.5, 0.0, 0.0]) hubS.machine_rating = 5000.0 # 2 ---------- # 3 ---------- hubS.run() # 3 ---------- # 4 ----------
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
# 1 --------- from math import pi import numpy as np from drivese.hub import HubSE from drivese.drive import Drive4pt # 1 --------- # 2 --------- # simple test of hub model # NREL 5 MW turbine hubS = HubSE() hubS.rotor_diameter = 126.0 # m hubS.blade_number = 3 hubS.blade_root_diameter = 3.542 hubS.L_rb = 0.5 hubS.gamma = 5.0 hubS.MB1_location = np.array([-0.5, 0.0, 0.0]) hubS.machine_rating = 5000.0 # 2 ---------- # 3 ---------- hubS.run() # 3 ---------- # 4 ----------
def configure_turbine(assembly,
with_new_nacelle=True,
flexible_blade=False,
with_3pt_drive=False):
"""a stand-alone configure method to allow for flatter assemblies
Parameters
----------
assembly : Assembly
an openmdao assembly to be configured
with_new_nacelle : bool
False uses the default implementation, True uses an experimental implementation designed
to smooth out discontinities making in amenable for gradient-based optimization
flexible_blade : bool
if True, internally solves the coupled aero/structural deflection using fixed point iteration.
Note that the coupling is currently only in the flapwise deflection, and is primarily
only important for highly flexible blades. If False, the aero loads are passed
to the structure but there is no further iteration.
"""
# --- general turbine configuration inputs---
assembly.add(
'rho',
Float(1.225,
iotype='in',
units='kg/m**3',
desc='density of air',
deriv_ignore=True))
assembly.add(
'mu',
Float(1.81206e-5,
iotype='in',
units='kg/m/s',
desc='dynamic viscosity of air',
deriv_ignore=True))
assembly.add(
'shear_exponent',
Float(0.2, iotype='in', desc='shear exponent', deriv_ignore=True))
assembly.add('hub_height',
Float(90.0, iotype='in', units='m', desc='hub height'))
assembly.add(
'turbine_class',
Enum('I', ('I', 'II', 'III', 'IV'),
iotype='in',
desc='IEC turbine class'))
assembly.add(
'turbulence_class',
Enum('B', ('A', 'B', 'C'),
iotype='in',
desc='IEC turbulence class class'))
assembly.add(
'g',
Float(9.81,
iotype='in',
units='m/s**2',
desc='acceleration of gravity',
deriv_ignore=True))
assembly.add(
'cdf_reference_height_wind_speed',
Float(
90.0,
iotype='in',
desc=
'reference hub height for IEC wind speed (used in CDF calculation)'
))
assembly.add('downwind',
Bool(False, iotype='in', desc='flag if rotor is downwind'))
assembly.add(
'tower_d',
Array([0.0], iotype='in', units='m', desc='diameters along tower'))
assembly.add('generator_speed',
Float(iotype='in', units='rpm', desc='generator speed'))
assembly.add(
'machine_rating',
Float(5000.0, units='kW', iotype='in', desc='machine rated power'))
assembly.add(
'rna_weightM',
Bool(True,
iotype='in',
desc='flag to consider or not the RNA weight effect on Moment'))
assembly.add('rotor', RotorSE())
if with_new_nacelle:
assembly.add('hub', HubSE())
assembly.add('hubSystem', Hub_System_Adder_drive())
assembly.add('moments', blade_moment_transform())
assembly.add('forces', blade_force_transform())
if with_3pt_drive:
assembly.add('nacelle', Drive3pt())
else:
assembly.add('nacelle', Drive4pt())
else:
assembly.add('nacelle', DriveWPACT())
assembly.add('hub', HubWPACT())
assembly.add('rna', RNAMass())
assembly.add('rotorloads1', RotorLoads())
assembly.add('rotorloads2', RotorLoads())
assembly.add('tower', TowerSE())
assembly.add('maxdeflection', MaxTipDeflection())
if flexible_blade:
assembly.add('fpi', FixedPointIterator())
assembly.fpi.workflow.add(['rotor'])
assembly.fpi.add_parameter('rotor.delta_precurve_sub',
low=-1.e99,
high=1.e99)
assembly.fpi.add_parameter('rotor.delta_bladeLength',
low=-1.e99,
high=1.e99)
assembly.fpi.add_constraint(
'rotor.delta_precurve_sub = rotor.delta_precurve_sub_out')
assembly.fpi.add_constraint(
'rotor.delta_bladeLength = rotor.delta_bladeLength_out')
assembly.fpi.max_iteration = 20
assembly.fpi.tolerance = 1e-8
assembly.driver.workflow.add(['fpi'])
else:
assembly.driver.workflow.add(['rotor'])
assembly.driver.workflow.add([
'hub', 'nacelle', 'tower', 'maxdeflection', 'rna', 'rotorloads1',
'rotorloads2'
])
if with_new_nacelle:
assembly.driver.workflow.add(['hubSystem', 'moments', 'forces'])
# TODO: rotor drivetrain design should be connected to nacelle drivetrain design
# connections to rotor
assembly.connect('machine_rating', 'rotor.control.ratedPower')
assembly.connect('rho', 'rotor.rho')
assembly.connect('mu', 'rotor.mu')
assembly.connect('shear_exponent', 'rotor.shearExp')
assembly.connect('hub_height', 'rotor.hubHt')
assembly.connect('turbine_class', 'rotor.turbine_class')
assembly.connect('turbulence_class', 'rotor.turbulence_class')
assembly.connect('g', 'rotor.g')
assembly.connect('cdf_reference_height_wind_speed',
'rotor.cdf_reference_height_wind_speed')
# connections to hub and hub system
assembly.connect('rotor.mass_one_blade', 'hub.blade_mass')
assembly.connect('rotor.root_bending_moment', 'hub.rotor_bending_moment')
assembly.connect('rotor.diameter', ['hub.rotor_diameter'])
assembly.connect('rotor.hub_diameter', 'hub.blade_root_diameter')
assembly.connect('rotor.nBlades', 'hub.blade_number')
if with_new_nacelle:
assembly.connect('machine_rating', 'hub.machine_rating')
assembly.connect('rotor.diameter', ['hubSystem.rotor_diameter'])
assembly.connect('nacelle.MB1_location',
'hubSystem.MB1_location') # TODO: bearing locations
assembly.connect('nacelle.L_rb', 'hubSystem.L_rb')
assembly.connect('rotor.tilt', 'hubSystem.shaft_angle')
assembly.connect('hub.hub_diameter', 'hubSystem.hub_diameter')
assembly.connect('hub.hub_thickness', 'hubSystem.hub_thickness')
assembly.connect('hub.hub_mass', 'hubSystem.hub_mass')
assembly.connect('hub.spinner_mass', 'hubSystem.spinner_mass')
assembly.connect('hub.pitch_system_mass',
'hubSystem.pitch_system_mass')
# connections to nacelle #TODO: fatigue option variables
assembly.connect('rotor.diameter', 'nacelle.rotor_diameter')
assembly.connect('1.5 * rotor.ratedConditions.Q', 'nacelle.rotor_torque')
assembly.connect('rotor.ratedConditions.T', 'nacelle.rotor_thrust')
assembly.connect('rotor.ratedConditions.Omega', 'nacelle.rotor_speed')
assembly.connect('machine_rating', 'nacelle.machine_rating')
assembly.connect('rotor.root_bending_moment',
'nacelle.rotor_bending_moment')
assembly.connect('generator_speed/rotor.ratedConditions.Omega',
'nacelle.gear_ratio')
assembly.connect(
'tower_d[-1]',
'nacelle.tower_top_diameter') # OpenMDAO circular dependency issue
assembly.connect(
'rotor.mass_all_blades + hub.hub_system_mass',
'nacelle.rotor_mass') # assuming not already in rotor force / moments
# variable connections for new nacelle
if with_new_nacelle:
assembly.connect('rotor.nBlades', 'nacelle.blade_number')
assembly.connect('rotor.tilt', 'nacelle.shaft_angle')
assembly.connect('333.3 * machine_rating / 1000.0',
'nacelle.shrink_disc_mass')
assembly.connect('rotor.hub_diameter', 'nacelle.blade_root_diameter')
#moments
# assembly.connect('rotor.Q_extreme','nacelle.rotor_bending_moment_x')
assembly.connect('rotor.Mxyz_0', 'moments.b1')
assembly.connect('rotor.Mxyz_120', 'moments.b2')
assembly.connect('rotor.Mxyz_240', 'moments.b3')
assembly.connect('rotor.Pitch', 'moments.pitch_angle')
assembly.connect('rotor.TotalCone', 'moments.cone_angle')
assembly.connect('moments.Mx', 'nacelle.rotor_bending_moment_x'
) #accounted for in ratedConditions.Q
assembly.connect('moments.My', 'nacelle.rotor_bending_moment_y')
assembly.connect('moments.Mz', 'nacelle.rotor_bending_moment_z')
#forces
# assembly.connect('rotor.T_extreme','nacelle.rotor_force_x')
assembly.connect('rotor.Fxyz_0', 'forces.b1')
assembly.connect('rotor.Fxyz_120', 'forces.b2')
assembly.connect('rotor.Fxyz_240', 'forces.b3')
assembly.connect('rotor.Pitch', 'forces.pitch_angle')
assembly.connect('rotor.TotalCone', 'forces.cone_angle')
assembly.connect('forces.Fx', 'nacelle.rotor_force_x')
assembly.connect('forces.Fy', 'nacelle.rotor_force_y')
assembly.connect('forces.Fz', 'nacelle.rotor_force_z')
'''if with_new_nacelle:
assembly.connect('rotor.g', 'nacelle.g') # Only drive smooth taking g from rotor; TODO: update when drive_smooth is updated'''
# connections to rna
assembly.connect('rotor.mass_all_blades', 'rna.blades_mass')
assembly.connect('rotor.I_all_blades', 'rna.blades_I')
if with_new_nacelle:
assembly.connect('hubSystem.hub_system_mass', 'rna.hub_mass')
assembly.connect('hubSystem.hub_system_cm', 'rna.hub_cm')
assembly.connect('hubSystem.hub_system_I', 'rna.hub_I')
else:
assembly.connect('hub.hub_system_mass', 'rna.hub_mass')
assembly.connect('hub.hub_system_cm', 'rna.hub_cm')
assembly.connect('hub.hub_system_I', 'rna.hub_I')
assembly.connect('nacelle.nacelle_mass', 'rna.nac_mass')
assembly.connect('nacelle.nacelle_cm', 'rna.nac_cm')
assembly.connect('nacelle.nacelle_I', 'rna.nac_I')
# connections to rotorloads1
assembly.connect('downwind', 'rotorloads1.downwind')
assembly.connect('rna_weightM', 'rotorloads1.rna_weightM')
assembly.connect('1.8 * rotor.ratedConditions.T', 'rotorloads1.F[0]')
assembly.connect('rotor.ratedConditions.Q', 'rotorloads1.M[0]')
if with_new_nacelle:
assembly.connect('hubSystem.hub_system_cm', 'rotorloads1.r_hub')
else:
assembly.connect('hub.hub_system_cm', 'rotorloads1.r_hub')
assembly.connect('rna.rna_cm', 'rotorloads1.rna_cm')
assembly.connect('rotor.tilt', 'rotorloads1.tilt')
assembly.connect('g', 'rotorloads1.g')
assembly.connect('rna.rna_mass', 'rotorloads1.m_RNA')
# connections to rotorloads2
assembly.connect('downwind', 'rotorloads2.downwind')
assembly.connect('rna_weightM', 'rotorloads2.rna_weightM')
assembly.connect('rotor.T_extreme', 'rotorloads2.F[0]')
assembly.connect('rotor.Q_extreme', 'rotorloads2.M[0]')
if with_new_nacelle:
assembly.connect('hubSystem.hub_system_cm', 'rotorloads2.r_hub')
else:
assembly.connect('hub.hub_system_cm', 'rotorloads2.r_hub')
assembly.connect('rna.rna_cm', 'rotorloads2.rna_cm')
assembly.connect('rotor.tilt', 'rotorloads2.tilt')
assembly.connect('g', 'rotorloads2.g')
assembly.connect('rna.rna_mass', 'rotorloads2.m_RNA')
# connections to tower
assembly.connect('rho', 'tower.wind_rho')
assembly.connect('mu', 'tower.wind_mu')
assembly.connect('g', 'tower.g')
assembly.connect('hub_height', 'tower.wind_zref')
assembly.connect('tower_d', 'tower.d_param')
assembly.connect('rotor.ratedConditions.V', 'tower.wind_Uref1')
assembly.connect('rotor.V_extreme', 'tower.wind_Uref2')
assembly.connect('rotor.yaw', 'tower.yaw')
assembly.connect('hub_height - nacelle.nacelle_cm[2]',
'tower.z_param[-1]') #TODO: hub height should be derived
assembly.connect('rna.rna_mass', 'tower.m[0]')
assembly.connect('rna.rna_cm[0]', 'tower.mrhox[0]')
assembly.connect('rna.rna_cm[1]', 'tower.mrhoy[0]')
assembly.connect('rna.rna_cm[2]', 'tower.mrhoz[0]')
assembly.connect('rna.rna_I_TT[0]', 'tower.mIxx[0]')
assembly.connect('rna.rna_I_TT[1]', 'tower.mIyy[0]')
assembly.connect('rna.rna_I_TT[2]', 'tower.mIzz[0]')
assembly.connect('rna.rna_I_TT[3]', 'tower.mIxy[0]')
assembly.connect('rna.rna_I_TT[4]', 'tower.mIxz[0]')
assembly.connect('rna.rna_I_TT[5]', 'tower.mIyz[0]')
assembly.connect('rotorloads1.top_F[0]', 'tower.Fx1[0]')
assembly.connect('rotorloads1.top_F[1]', 'tower.Fy1[0]')
assembly.connect('rotorloads1.top_F[2]', 'tower.Fz1[0]')
assembly.connect('rotorloads1.top_M[0]', 'tower.Mxx1[0]')
assembly.connect('rotorloads1.top_M[1]', 'tower.Myy1[0]')
assembly.connect('rotorloads1.top_M[2]', 'tower.Mzz1[0]')
assembly.connect('rotorloads2.top_F[0]', 'tower.Fx2[0]')
assembly.connect('rotorloads2.top_F[1]', 'tower.Fy2[0]')
assembly.connect('rotorloads2.top_F[2]', 'tower.Fz2[0]')
assembly.connect('rotorloads2.top_M[0]', 'tower.Mxx2[0]')
assembly.connect('rotorloads2.top_M[1]', 'tower.Myy2[0]')
assembly.connect('rotorloads2.top_M[2]', 'tower.Mzz2[0]')
# connections to maxdeflection
assembly.connect('rotor.Rtip', 'maxdeflection.Rtip')
assembly.connect('rotor.precurveTip', 'maxdeflection.precurveTip')
assembly.connect('rotor.presweepTip', 'maxdeflection.presweepTip')
assembly.connect('rotor.precone', 'maxdeflection.precone')
assembly.connect('rotor.tilt', 'maxdeflection.tilt')
if with_new_nacelle:
assembly.connect('hubSystem.hub_system_cm', 'maxdeflection.hub_tt')
else:
assembly.connect('hub.hub_system_cm', 'maxdeflection.hub_tt')
assembly.connect('tower.z_param', 'maxdeflection.tower_z')
assembly.connect('tower.d_param', 'maxdeflection.tower_d')
assembly.connect('hub_height - nacelle.nacelle_cm[2]',
'maxdeflection.towerHt')