def initialize_problem(Analysis_Level):
# Initialize blade design
refBlade = ReferenceBlade()
refBlade.verbose = True
refBlade.NINPUT = 200
Nsection_Tow = 19
refBlade.NPTS = 200
refBlade.spar_var = ['Spar_cap_ss', 'Spar_cap_ps'] # SS, then PS
refBlade.te_var = 'TE_reinforcement'
refBlade.validate = False
refBlade.fname_schema = fname_schema
blade = refBlade.initialize(fname_input)
FASTpref = {}
FASTpref['Analysis_Level'] = Analysis_Level
# Set FAST Inputs
if Analysis_Level >= 1:
# File management
FASTpref['FAST_ver'] = 'OpenFAST'
FASTpref['dev_branch'] = True
FASTpref['FAST_exe'] = '~/local/bin/openfast'
FASTpref['FAST_directory'] = '../OpenFAST' # Path to fst directory files
FASTpref['FAST_InputFile'] = 'IEA-15-240-RWT.fst' # FAST input file (ext=.fst)
FASTpref['Turbsim_exe'] = '~/local/bin/turbsim'
FASTpref['FAST_namingOut'] = 'IEA-15-240-RWT'
FASTpref['FAST_runDirectory'] = 'temp/' + FASTpref['FAST_namingOut']
# Run Settings
FASTpref['cores'] = 1
FASTpref['debug_level'] = 2 # verbosity: set to 0 for quiet, 1 & 2 for increasing levels of output
# DLCs
FASTpref['DLC_gust'] = None # Max deflection
# FASTpref['DLC_gust'] = RotorSE_DLC_1_4_Rated # Max deflection ### Not in place yet
FASTpref['DLC_extrm'] = None # Max strain
# FASTpref['DLC_extrm'] = RotorSE_DLC_7_1_Steady # Max strain ### Not in place yet
FASTpref['DLC_turbulent'] = None
# FASTpref['DLC_turbulent'] = RotorSE_DLC_1_1_Turb # Alternate turbulent case, replacing rated and extreme DLCs for calculating max deflection and strain
FASTpref['DLC_powercurve'] = None # AEP
# FASTpref['DLC_powercurve'] = None # AEP
# Initialize, read initial FAST files to avoid doing it iteratively
fast = InputReader_OpenFAST(FAST_ver=FASTpref['FAST_ver'], dev_branch=FASTpref['dev_branch'])
fast.FAST_InputFile = FASTpref['FAST_InputFile']
fast.FAST_directory = FASTpref['FAST_directory']
fast.execute()
fst_vt = fast.fst_vt
else:
fst_vt = {}
prob = om.Problem()
prob.model=MonopileTurbine(RefBlade=blade, Nsection_Tow=Nsection_Tow, VerbosityCosts=False, FASTpref=FASTpref)
prob.model.nonlinear_solver = om.NonlinearRunOnce()
prob.model.linear_solver = om.DirectSolver()
return prob, blade, fst_vt
def compute(self, inputs, outputs, discrete_inputs, discrete_outputs):
# initialization point
# if discrete_inputs['blade_in_overwrite'] != {}:
# blade = copy.deepcopy(discrete_inputs['blade_in_overwrite'])
# else:
blade = copy.deepcopy(self.refBlade)
NINPUT = len(blade['ctrl_pts']['r_in'])
# Set inputs to update blade geometry
Rhub = inputs['hubFraction'] * inputs['bladeLength']
Rtip = Rhub + inputs['bladeLength']
outputs['Rhub'] = Rhub
outputs['Rtip'] = Rtip
r_in = blade['ctrl_pts']['r_in']
outputs['r_in'] = Rhub + (Rtip - Rhub) * np.array(r_in)
blade['ctrl_pts']['bladeLength'] = inputs['bladeLength']
blade['ctrl_pts']['r_in'] = r_in
blade['ctrl_pts']['chord_in'] = inputs['chord_in']
blade['ctrl_pts']['theta_in'] = inputs['theta_in']
blade['ctrl_pts']['precurve_in'] = inputs['precurve_in']
blade['ctrl_pts']['presweep_in'] = inputs['presweep_in']
blade['ctrl_pts']['sparT_in'] = inputs['sparT_in']
blade['ctrl_pts']['teT_in'] = inputs['teT_in']
blade['ctrl_pts']['r_max_chord'] = inputs['r_max_chord']
#check that airfoil positions are increasing
correct_af_position = False
airfoil_position = copy.deepcopy(inputs['airfoil_position']).tolist()
for i in reversed(range(1, len(airfoil_position))):
if airfoil_position[i] <= airfoil_position[i - 1]:
airfoil_position[i - 1] = airfoil_position[i] - 0.001
correct_af_position = True
if correct_af_position:
blade['outer_shape_bem']['airfoil_position'][
'grid'] = airfoil_position
warning_corrected_airfoil_position = "Airfoil spanwise positions must be increasing. Changed from: %s to: %s" % (
inputs['airfoil_position'].tolist(), airfoil_position)
warnings.warn(warning_corrected_airfoil_position)
else:
blade['outer_shape_bem']['airfoil_position']['grid'] = inputs[
'airfoil_position'].tolist()
# Update
refBlade = ReferenceBlade()
refBlade.verbose = False
refBlade.NINPUT = len(outputs['r_in'])
refBlade.NPTS = len(blade['pf']['s'])
refBlade.analysis_level = blade['analysis_level']
if blade['analysis_level'] < 3:
refBlade.spar_var = blade['precomp']['spar_var']
refBlade.te_var = blade['precomp']['te_var']
blade_out = refBlade.update(blade)
# Get geometric outputs
outputs['hub_diameter'] = 2.0 * Rhub
outputs['r'] = Rhub + (Rtip - Rhub) * np.array(blade_out['pf']['s'])
outputs['diameter'] = 2.0 * outputs['r'][-1]
outputs['chord'] = blade_out['pf']['chord']
outputs['max_chord'] = max(blade_out['pf']['chord'])
outputs['theta'] = blade_out['pf']['theta']
outputs['precurve'] = blade_out['pf']['precurve']
outputs['presweep'] = blade_out['pf']['presweep']
outputs['rthick'] = blade_out['pf']['rthick']
outputs['le_location'] = blade_out['pf']['p_le']
# airfoils = blade_out['airfoils']
outputs['airfoils_cl'] = blade_out['airfoils_cl']
outputs['airfoils_cd'] = blade_out['airfoils_cd']
outputs['airfoils_cm'] = blade_out['airfoils_cm']
outputs['airfoils_aoa'] = blade_out['airfoils_aoa']
outputs['airfoils_Re'] = blade_out['airfoils_Re']
upperCS = blade_out['precomp']['upperCS']
lowerCS = blade_out['precomp']['lowerCS']
websCS = blade_out['precomp']['websCS']
profile = blade_out['precomp']['profile']
materials = blade_out['precomp']['materials']
for i in range(len(profile)):
outputs['airfoils_coord_x'][:, i] = blade_out['profile'][:, 0, i]
outputs['airfoils_coord_y'][:, i] = blade_out['profile'][:, 1, i]
# Assumptions:
# - if the composite layer is divided into multiple regions (i.e. if the spar cap is split into 3 regions due to the web locations),
# the middle region is selected with int(n_reg/2), note for an even number of regions, this rounds up
sector_idx_strain_spar_ss = blade_out['precomp'][
'sector_idx_strain_spar_ss']
sector_idx_strain_spar_ps = blade_out['precomp'][
'sector_idx_strain_spar_ps']
sector_idx_strain_te_ss = blade_out['precomp'][
'sector_idx_strain_te_ss']
sector_idx_strain_te_ps = blade_out['precomp'][
'sector_idx_strain_te_ps']
# Get Beam Properties
beam = PreComp(outputs['r'], outputs['chord'], outputs['theta'],
outputs['le_location'], outputs['precurve'],
outputs['presweep'], profile, materials, upperCS,
lowerCS, websCS, sector_idx_strain_spar_ps,
sector_idx_strain_spar_ss, sector_idx_strain_te_ps,
sector_idx_strain_te_ss)
EIxx, EIyy, GJ, EA, EIxy, x_ec, y_ec, rhoA, rhoJ, Tw_iner, flap_iner, edge_iner = beam.sectionProperties(
)
outputs['eps_crit_spar'] = beam.panelBucklingStrain(
sector_idx_strain_spar_ss)
outputs['eps_crit_te'] = beam.panelBucklingStrain(
sector_idx_strain_te_ss)
xu_strain_spar, xl_strain_spar, yu_strain_spar, yl_strain_spar = beam.criticalStrainLocations(
sector_idx_strain_spar_ss, sector_idx_strain_spar_ps)
xu_strain_te, xl_strain_te, yu_strain_te, yl_strain_te = beam.criticalStrainLocations(
sector_idx_strain_te_ss, sector_idx_strain_te_ps)
outputs['z'] = outputs['r']
outputs['EIxx'] = EIxx
outputs['EIyy'] = EIyy
outputs['GJ'] = GJ
outputs['EA'] = EA
outputs['EIxy'] = EIxy
outputs['x_ec'] = x_ec
outputs['y_ec'] = y_ec
outputs['rhoA'] = rhoA
outputs['rhoJ'] = rhoJ
outputs['Tw_iner'] = Tw_iner
outputs['flap_iner'] = flap_iner
outputs['edge_iner'] = edge_iner
outputs['xu_strain_spar'] = xu_strain_spar
outputs['xl_strain_spar'] = xl_strain_spar
outputs['yu_strain_spar'] = yu_strain_spar
outputs['yl_strain_spar'] = yl_strain_spar
outputs['xu_strain_te'] = xu_strain_te
outputs['xl_strain_te'] = xl_strain_te
outputs['yu_strain_te'] = yu_strain_te
outputs['yl_strain_te'] = yl_strain_te
# Blade cost model
bcm = blade_cost_model(
options=self.options
) # <------------- options, import blade cost model
bcm.name = blade_out['config']['name']
bcm.materials = materials
bcm.upperCS = upperCS
bcm.lowerCS = lowerCS
bcm.websCS = websCS
bcm.profile = profile
bcm.chord = outputs['chord']
bcm.r = (outputs['r'] - outputs['Rhub']) / (
outputs['Rtip'] - outputs['Rhub']) * float(inputs['bladeLength'])
bcm.bladeLength = float(inputs['bladeLength'])
bcm.le_location = outputs['le_location']
blade_cost, blade_mass = bcm.execute_blade_cost_model()
outputs['total_blade_cost'] = blade_cost
outputs['total_blade_mass'] = blade_mass
#
discrete_outputs['blade_out'] = blade_out
outputs['sparT_in_out'] = inputs['sparT_in']
'hub_height'] # (Float, m): hub height
rotor['turbine_class'] = blade['config']['turbine_class'].upper(
) #TURBINE_CLASS['I'] # (Enum): IEC turbine class
return rotor
if __name__ == "__main__":
# Turbine Ontology input
fname_input = "turbine_inputs/nrel5mw_mod_update.yaml"
# Initialize blade design
refBlade = ReferenceBlade()
refBlade.verbose = True
refBlade.NINPUT = NINPUT
refBlade.NPITS = 50
refBlade.validate = False
refBlade.fname_schema = "turbine_inputs/IEAontology_schema.yaml"
refBlade.spar_var = ['Spar_Cap_SS', 'Spar_Cap_PS']
refBlade.te_var = 'TE_reinforcement'
blade = refBlade.initialize(fname_input)
# setup
rotor = Problem()
rotor.model = RotorGeometry(RefBlade=blade, topLevelFlag=True)
rotor.setup()
rotor = Init_RotorGeometry_wRefBlade(rotor, blade)
rotor.run_driver()
def run_problem(optFlag=False, prob_ref=None):
# Initialize blade design
refBlade = ReferenceBlade()
if rank == 0:
refBlade.verbose = True
else:
refBlade.verbose = False
refBlade.NINPUT = 8
Nsection_Tow = 19
refBlade.NPTS = 30
refBlade.spar_var = ['Spar_cap_ss', 'Spar_cap_ps'] # SS, then PS
refBlade.te_var = 'TE_reinforcement'
refBlade.le_var = 'le_reinf'
refBlade.validate = False
refBlade.fname_schema = fname_schema
blade = refBlade.initialize(fname_input)
Analysis_Level = 0
FASTpref = {}
FASTpref['Analysis_Level'] = Analysis_Level
fst_vt = {}
# Initialize and execute OpenMDAO problem with input data
if MPI:
num_par_fd = MPI.COMM_WORLD.Get_size()
prob = om.Problem(model=om.Group(num_par_fd=num_par_fd))
prob.model.approx_totals(method='fd')
prob.model.add_subsystem('comp',
Optimize_MonopileTurbine(
RefBlade=blade,
Nsection_Tow=Nsection_Tow,
folder_output=folder_output),
promotes=['*'])
else:
prob = om.Problem()
prob.model = Optimize_MonopileTurbine(RefBlade=blade,
Nsection_Tow=Nsection_Tow,
folder_output=folder_output)
prob.model.nonlinear_solver = om.NonlinearRunOnce()
prob.model.linear_solver = om.DirectSolver()
if optFlag and not prob_ref is None:
if MPI:
num_par_fd = MPI.COMM_WORLD.Get_size()
prob = om.Problem(model=om.Group(num_par_fd=num_par_fd))
prob.model.approx_totals(method='fd')
prob.model.add_subsystem('comp',
Optimize_MonopileTurbine(
RefBlade=blade,
Nsection_Tow=Nsection_Tow,
folder_output=folder_output),
promotes=['*'])
else:
prob = om.Problem()
prob.model = Optimize_MonopileTurbine(RefBlade=blade,
Nsection_Tow=Nsection_Tow,
folder_output=folder_output)
# --- Driver ---
prob.driver = om.pyOptSparseDriver()
prob.driver.options['optimizer'] = 'CONMIN'
prob.driver.opt_settings['ITMAX'] = 15
prob.driver.opt_settings['IPRINT'] = 4
# ----------------------
# --- Objective ---
# prob.model.add_objective('lcoe')
prob.model.add_objective('AEP', scaler=-1.)
#prob.model.add_objective('mass_one_blade')
# ----------------------
# --- Design Variables ---
indices_no_root = range(2, refBlade.NINPUT)
indices_no_root_no_tip = range(2, refBlade.NINPUT - 1)
indices_no_max_chord = range(3, refBlade.NINPUT)
prob.model.add_design_var('sparT_in',
indices=indices_no_root_no_tip,
lower=0.001,
upper=0.200)
prob.model.add_design_var('chord_in',
indices=indices_no_max_chord,
lower=0.5,
upper=7.0)
prob.model.add_design_var('theta_in',
indices=indices_no_root,
lower=-7.5,
upper=20.0)
prob.model.add_design_var('teT_in',
lower=prob_ref['teT_in'] * 0.5,
upper=0.1)
#prob.model.add_design_var('leT_in', lower=prob_ref['leT_in']*0.5, upper=0.1)
# ----------------------
# --- Constraints ---
prob.model.add_subsystem('freq_check',
blade_freq_check(),
promotes=['freq_check_out'])
prob.model.connect('freq_curvefem',
'freq_check.freq_curvefem') #, src_indices=[0])
# Rotor
prob.model.add_constraint('tip_deflection_ratio', upper=1.0)
# prob.model.add_constraint('no_stall_constraint', upper=1.0)
prob.model.add_constraint('freq_check_out', lower=1.1)
#prob.model.add_constraint('rated_Q', lower=21.4e6, upper=21.6e6)
# prob.model.add_constraint('mass_one_blade', upper=prob_ref['mass_one_blade']*1.02)
prob.model.add_constraint('AEP', lower=0.99 * prob_ref['AEP'])
# ----------------------
# --- Recorder ---
filename_opt_log = folder_output + 'log_opt_' + blade['config']['name']
prob.driver.add_recorder(om.SqliteRecorder(filename_opt_log))
prob.driver.recording_options['includes'] = [
'AEP', 'total_blade_cost', 'lcoe', 'tip_deflection_ratio',
'mass_one_blade', 'theta_in'
]
prob.driver.recording_options['record_objectives'] = True
prob.driver.recording_options['record_constraints'] = True
prob.driver.recording_options['record_desvars'] = True
# ----------------------
# Initialize variable inputs
prob = initialize_variables(prob, blade, Analysis_Level, fst_vt)
# Run initial condition no matter what
print('Running at Initial Position:')
prob.run_model()
print('########################################')
print('')
print('Control variables')
print('Rotor diam: {:8.3f} m'.format(prob['diameter'][0]))
print('TSR: {:8.3f} -'.format(prob['control_tsr'][0]))
print('Rated vel: {:8.3f} m/s'.format(prob['rated_V'][0]))
print('Rated rpm: {:8.3f} rpm'.format(prob['rated_Omega'][0]))
print('Rated pitch: {:8.3f} deg'.format(prob['rated_pitch'][0]))
print('Rated thrust: {:8.3f} N'.format(prob['rated_T'][0]))
print('Rated torque: {:8.3f} N-m'.format(prob['rated_Q'][0]))
print('')
print('Constraints')
print('Max TD: {:8.3f} m'.format(prob['tip_deflection'][0]))
print('TD ratio: {:8.3f} -'.format(prob['tip_deflection_ratio'][0]))
print('Blade root M: {:8.3f} N-m'.format(prob['root_bending_moment'][0]))
print('')
print('Objectives')
print('AEP: {:8.3f} GWh'.format(prob['AEP'][0]))
print('LCoE: {:8.4f} $/MWh'.format(prob['lcoe'][0]))
print('')
print('Blades')
print('Blade mass: {:8.3f} kg'.format(prob['mass_one_blade'][0]))
print('Blade cost: {:8.3f} $'.format(prob['total_blade_cost'][0]))
print('Blade freq: {:8.3f} Hz'.format(prob['freq_curvefem'][0]))
print('3 blade M_of_I: ', prob['I_all_blades'], ' kg-m^2')
print('Hub M: ', prob['Mxyz_total'], ' kg-m^2')
print('')
print('RNA Summary')
print('RNA mass: {:8.3f} kg'.format(prob['tow.pre.mass'][0]))
print('RNA C_of_G (TT): ', prob['rna_cg'], ' m')
print('RNA M_of_I: ', prob['tow.pre.mI'], ' kg-m^2')
print('')
print('Tower')
print('Tower top F: ', prob['tow.pre.rna_F'], ' N')
print('Tower top M: ', prob['tow.pre.rna_M'], ' N-m')
print('Tower freqs: ', prob['tow.post.structural_frequencies'], ' Hz')
print('Tower vel: {:8.3f} kg'.format(prob['tow.wind.Uref'][0]))
print('Tower mass: {:8.3f} kg'.format(prob['tower_mass'][0]))
print('Tower cost: {:8.3f} $'.format(prob['tower_cost'][0]))
print('########################################')
# Angle of attack and stall angle
faoa, axaoa = plt.subplots(1, 1, figsize=(5.3, 4))
axaoa.plot(prob['r'],
prob['nostallconstraint.aoa_along_span'],
label='Initial aoa')
axaoa.plot(prob['r'],
prob['nostallconstraint.stall_angle_along_span'],
'.',
label='Initial stall')
axaoa.legend(fontsize=12)
plt.xlabel('Blade Span [m]', fontsize=14, fontweight='bold')
plt.ylabel('Angle [deg]', fontsize=14, fontweight='bold')
plt.xticks(fontsize=12)
plt.yticks(fontsize=12)
plt.grid(color=[0.8, 0.8, 0.8], linestyle='--')
plt.subplots_adjust(bottom=0.15, left=0.15)
fig_name = 'aoa.png'
faoa.savefig(folder_output + fig_name)
# Complete data dump
#prob.model.list_inputs(units=True)
#prob.model.list_outputs(units=True)
if optFlag:
if rank == 0:
print('Running Optimization:')
print('N design var: ',
2 * len(indices_no_root_no_tip) + len(indices_no_root) + 1)
if not MPI:
prob.model.approx_totals()
prob.run_driver()
if rank == 0:
# --- Save output .yaml ---
refBlade.write_ontology(fname_output, prob['blade_out'],
refBlade.wt_ref)
# --- Outputs plotting ---
print('AEP: \t\t\t %f\t%f GWh \t Difference: %f %%' %
(prob_ref['AEP'] * 1e-6, prob['AEP'] * 1e-6,
(prob['AEP'] - prob_ref['AEP']) / prob_ref['AEP'] * 100.))
print(
'LCoE: \t\t\t %f\t%f USD/MWh \t Difference: %f %%' %
(prob_ref['lcoe'] * 1.e003, prob['lcoe'] * 1.e003,
(prob['lcoe'] - prob_ref['lcoe']) / prob_ref['lcoe'] * 100.))
print('Blade cost: \t\t\t %f\t%f USD \t Difference: %f %%' %
(prob_ref['total_blade_cost'], prob['total_blade_cost'],
(prob['total_blade_cost'] - prob_ref['total_blade_cost']) /
prob_ref['total_blade_cost'] * 100.))
print('Blade mass: \t\t\t %f\t%f kg \t Difference: %f %%' %
(prob_ref['total_blade_mass'], prob['total_blade_mass'],
(prob['total_blade_mass'] - prob_ref['total_blade_mass']) /
prob_ref['total_blade_mass'] * 100.))
print('Tower cost: \t\t\t %f\t%f USD \t Difference: %f %%' %
(prob_ref['tower_cost'], prob['tower_cost'],
(prob['tower_cost'] - prob_ref['tower_cost']) /
prob_ref['tower_cost'] * 100.))
print('Tower mass: \t\t\t %f\t%f kg \t Difference: %f %%' %
(prob_ref['tower_mass'], prob['tower_mass'],
(prob['tower_mass'] - prob_ref['tower_mass']) /
prob_ref['tower_mass'] * 100.))
# ----------------------
# Theta
ft, axt = plt.subplots(1, 1, figsize=(5.3, 4))
axt.plot(prob_ref['r'], prob_ref['theta'], label='Initial')
axt.plot(prob_ref['r_in'], prob_ref['theta_in'], '.')
axt.plot(prob['r'], prob['theta'], label='Optimized')
axt.plot(prob['r_in'], prob['theta_in'], '.')
axt.legend(fontsize=12)
plt.xlabel('Blade Span [m]', fontsize=14, fontweight='bold')
plt.ylabel('Twist [deg]', fontsize=14, fontweight='bold')
plt.xticks(fontsize=12)
plt.yticks(fontsize=12)
plt.grid(color=[0.8, 0.8, 0.8], linestyle='--')
plt.subplots_adjust(bottom=0.15, left=0.15)
fig_name = 'theta.png'
ft.savefig(folder_output + fig_name)
# Angle of attack and stall angle
faoa, axaoa = plt.subplots(1, 1, figsize=(5.3, 4))
axaoa.plot(prob_ref['r'],
prob_ref['nostallconstraint.aoa_along_span'],
label='Initial aoa')
axaoa.plot(prob_ref['r'],
prob_ref['nostallconstraint.stall_angle_along_span'],
'.',
label='Initial stall')
axaoa.plot(prob['r'],
prob['nostallconstraint.aoa_along_span'],
label='Optimized aoa')
axaoa.plot(prob['r'],
prob['nostallconstraint.stall_angle_along_span'],
'.',
label='Optimized stall')
axaoa.legend(fontsize=12)
plt.xlabel('Blade Span [m]', fontsize=14, fontweight='bold')
plt.ylabel('Angle [deg]', fontsize=14, fontweight='bold')
plt.xticks(fontsize=12)
plt.yticks(fontsize=12)
plt.grid(color=[0.8, 0.8, 0.8], linestyle='--')
plt.subplots_adjust(bottom=0.15, left=0.15)
fig_name = 'aoa.png'
ft.savefig(folder_output + fig_name)
plt.show()
return prob, blade
def testAssembly(self):
# Global inputs and outputs
fname_schema = mydir + os.sep + 'IEAontology_schema.yaml'
fname_input = mydir + os.sep + 'IEA-15-240-RWT.yaml'
# Initialize blade design
refBlade = ReferenceBlade()
refBlade.verbose = True
refBlade.NINPUT = 8
Nsection_Tow = 19
refBlade.NPTS = 30
refBlade.spar_var = ['Spar_cap_ss', 'Spar_cap_ps'] # SS, then PS
refBlade.te_var = 'TE_reinforcement'
refBlade.validate = False
refBlade.fname_schema = fname_schema
blade = refBlade.initialize(fname_input)
Analysis_Level = 0
FASTpref = {}
FASTpref['Analysis_Level'] = Analysis_Level
fst_vt = {}
prob = om.Problem()
prob.model = MonopileTurbine(RefBlade=blade,
Nsection_Tow=Nsection_Tow,
VerbosityCosts=False,
FASTpref=FASTpref)
prob.model.nonlinear_solver = om.NonlinearRunOnce()
prob.model.linear_solver = om.DirectSolver()
prob.setup()
prob = Init_RotorSE_wRefBlade(prob,
blade,
Analysis_Level=Analysis_Level,
fst_vt=fst_vt)
# Environmental parameters for the tower
prob['significant_wave_height'] = 4.52
prob['significant_wave_period'] = 9.45
prob['water_depth'] = 30.
prob['wind_reference_height'] = prob['hub_height'] = 150.
prob['shearExp'] = 0.11
prob['rho'] = 1.225
prob['mu'] = 1.7934e-5
prob['water_density'] = 1025.0
prob['water_viscosity'] = 1.3351e-3
prob['wind_beta'] = prob['wave_beta'] = 0.0
# Steel properties for the tower
prob['material_density'] = 7850.0
prob['E'] = 210e9
prob['G'] = 79.3e9
prob['yield_stress'] = 345e6
prob['soil_G'] = 140e6
prob['soil_nu'] = 0.4
# Design constraints
prob['max_taper_ratio'] = 0.4
prob['min_diameter_thickness_ratio'] = 120.0
# Safety factors
prob['gamma_fatigue'] = 1.755 # (Float): safety factor for fatigue
prob['gamma_f'] = 1.35 # (Float): safety factor for loads/stresses
prob['gamma_m'] = 1.3 # (Float): safety factor for materials
prob[
'gamma_freq'] = 1.1 # (Float): safety factor for resonant frequencies
prob['gamma_n'] = 1.0
prob['gamma_b'] = 1.1
# Tower
prob['tower_buckling_length'] = 30.0
prob['tower_outfitting_factor'] = 1.07
prob['foundation_height'] = -30.
prob['suctionpile_depth'] = 45.
prob['tower_section_height'] = np.array([
5., 5., 5., 5., 5., 5., 5., 5., 5., 13., 13., 13., 13., 13., 13.,
13., 13., 13., 12.58244309
])
prob['tower_outer_diameter'] = np.array([
10., 10., 10., 10., 10., 10., 10., 10., 10., 10., 10., 9.92647687,
9.44319282, 8.83283769, 8.15148167, 7.38976138, 6.90908962,
6.74803581, 6.57231775, 6.5
])
prob['tower_wall_thickness'] = np.array([
0.05534138, 0.05344902, 0.05150928, 0.04952705, 0.04751736,
0.04551709, 0.0435267, 0.04224176, 0.04105759, 0.0394965,
0.03645589, 0.03377851, 0.03219233, 0.03070819, 0.02910109,
0.02721289, 0.02400931, 0.0208264, 0.02399756
])
prob['tower_buckling_length'] = 15.0
prob['transition_piece_mass'] = 100e3
prob['transition_piece_height'] = 15.0
prob['DC'] = 80.0
prob['shear'] = True
prob['geom'] = True
prob['tower_force_discretization'] = 5.0
prob['nM'] = 2
prob['Mmethod'] = 1
prob['lump'] = 0
prob['tol'] = 1e-9
prob['shift'] = 0.0
# Offshore BOS
prob['wtiv'] = 'example_wtiv'
prob['feeder'] = 'future_feeder'
prob['num_feeders'] = 1
prob['oss_install_vessel'] = 'example_heavy_lift_vessel'
prob['site_distance'] = 40.0
prob['site_distance_to_landfall'] = 40.0
prob['site_distance_to_interconnection'] = 40.0
prob['plant_turbine_spacing'] = 7
prob['plant_row_spacing'] = 7
prob['plant_substation_distance'] = 1
prob['tower_deck_space'] = 0.
prob['nacelle_deck_space'] = 0.
prob['blade_deck_space'] = 0.
prob['port_cost_per_month'] = 2e6
prob['monopile_deck_space'] = 0.
prob['transition_piece_deck_space'] = 0.
prob['commissioning_pct'] = 0.01
prob['decommissioning_pct'] = 0.15
prob['project_lifetime'] = prob['lifetime'] = 20.0
prob['number_of_turbines'] = 40
prob['annual_opex'] = 43.56 # $/kW/yr
#prob['bos_costs'] = 1234.5 # $/kW
prob['tower_add_gravity'] = True
# For turbine costs
prob['offshore'] = True
prob['crane'] = False
prob['bearing_number'] = 2
prob['crane_cost'] = 0.0
prob['labor_cost_rate'] = 3.0
prob['material_cost_rate'] = 2.0
prob['painting_cost_rate'] = 28.8
# Drivetrain
prob['tilt'] = 6.0
prob['overhang'] = 11.075
prob['hub_cm'] = np.array([-10.685, 0.0, 5.471])
prob['nac_cm'] = np.array([-5.718, 0.0, 4.048])
prob['hub_I'] = np.array(
[1382171.187, 2169261.099, 2160636.794, 0.0, 0.0, 0.0])
prob['nac_I'] = np.array(
[13442265.552, 21116729.439, 18382414.385, 0.0, 0.0, 0.0])
prob['hub_mass'] = 190e3
prob['nac_mass'] = 797.275e3 - 190e3
prob['hss_mass'] = 0.0
prob['lss_mass'] = 19.504e3
prob['cover_mass'] = 0.0
prob['pitch_system_mass'] = 50e3
prob['platforms_mass'] = 0.0
prob['spinner_mass'] = 0.0
prob['transformer_mass'] = 0.0
prob['vs_electronics_mass'] = 0.0
prob['yaw_mass'] = 100e3
prob['gearbox_mass'] = 0.0
prob['generator_mass'] = 226.7e3 + 145.25e3
prob['bedplate_mass'] = 39.434e3
prob['main_bearing_mass'] = 4.699e3
prob.run_model()
# Make sure we get here
self.assertTrue(True)