# Turbine Ontology input
fname_schema = "turbine_inputs/IEAontology_schema.yaml"
fname_input = "turbine_inputs/nrel5mw_mod_update.yaml"
# fname_input = "/mnt/c/Users/egaertne/IEA-15-240-RWT/WISDEM/IEA-15-240-RWT.yaml"
# fname_input = "/mnt/c/Users/egaertne/IEA-15-240-RWT/WISDEM/IEA-15-240-RWT_TipShape.yaml"
output_folder = "test/"
fname_output = output_folder + 'test_out.yaml'
Analysis_Level = 0 # 0: Run CCBlade; 1: Update FAST model at each iteration but do not run; 2: Run FAST w/ ElastoDyn; 3: (Not implemented) Run FAST w/ BeamDyn
# Initialize blade design
refBlade = ReferenceBlade()
refBlade.verbose = True
refBlade.NINPUT = 8
refBlade.NPTS = 50
refBlade.apply_stall_delay = False
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)
# Set FAST Inputs
if Analysis_Level >= 1:
# File management
FASTpref = {}
FASTpref['Analysis_Level'] = Analysis_Level
FASTpref['FAST_ver'] = 'OpenFAST'
FASTpref['dev_branch'] = True
FASTpref[
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']['leT_in'] = inputs['leT_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']
refBlade.apply_stall_delay = blade['apply_stall_delay']
refBlade.user_update_routine = self.options['user_update_routine']
if blade['analysis_level'] < 3:
refBlade.spar_var = blade['precomp']['spar_var']
refBlade.te_var = blade['precomp']['te_var']
# if 'le_var' in blade['precomp']:
# refBlade.le_var = blade['precomp']['le_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']