def init_from_refBlade(self, refBlade):
# Code take from rotor_geometry.py (RotorSE). It computes layup properties, independent of which turbine it is
# Setup paths
strucpath = refBlade.getStructPath()
self.materials = Orthotropic2DMaterial.listFromPreCompFile(os.path.join(strucpath, 'materials.inp'))
npts = refBlade.npts
self.upperCS = [0]*npts
self.lowerCS = [0]*npts
self.websCS = [0]*npts
self.profile = [0]*npts
for i in range(npts):
webLoc = []
istr = str(i) if refBlade.name == '3_35MW' or refBlade.name == '10MW' else str(i+1)
self.upperCS[i], self.lowerCS[i], self.websCS[i] = CompositeSection.initFromPreCompLayupFile(os.path.join(strucpath, 'layup_' + istr + '.inp'), webLoc, self.materials , readLocW=True)
self.profile[i] = Profile.initFromPreCompFile(os.path.join(strucpath, 'shape_' + istr + '.inp'))
self.name = refBlade.name
self.bladeLength = refBlade.bladeLength
# self.eta = refBlade.r
self.r = refBlade.r * refBlade.bladeLength
self.chord = refBlade.chord_ref
self.le_location = refBlade.le_location
# --- aero and structural analysis options ---
rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power
rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at
rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve
rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.)
rotor.drivetrainType = 'geared' # (Enum)
rotor.nF = 5 # (Int): number of natural frequencies to compute
rotor.dynamic_amplication_tip_deflection = 1.35 # (Float): a dynamic amplification factor to adjust the static deflection calculation
# ----------------------
# --- materials and composite layup ---
basepath = os.path.join(os.path.dirname(rotorse.__file__),
'5MW_PreCompFiles')
# basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), '5MW_PrecompFiles')
materials = Orthotropic2DMaterial.listFromPreCompFile(
os.path.join(basepath, 'materials.inp'))
ncomp = len(rotor.initial_str_grid)
upper = [0] * ncomp
lower = [0] * ncomp
webs = [0] * ncomp
profile = [0] * ncomp
rotor.leLoc = np.array(
[
0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.498, 0.497, 0.465, 0.447,
0.43, 0.411, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4,
0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4
]
) # (Array): array of leading-edge positions from a reference blade axis (usually blade pitch axis). locations are normalized by the local chord length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference axis. positive in -x direction for airfoil-aligned coordinate system
rotor.sector_idx_strain_spar = [
def configure_nrel5mw_turbine(turbine, wind_class='I', sea_depth=0.0):
"""
Inputs:
rotor = RotorSE()
nacelle = DriveSE()
tower = TowerSE()
wind_class : str ('I', 'III', 'Offshore' - selected wind class for project)
sea_depth : float (sea depth if an offshore wind plant)
"""
# === Turbine ===
turbine.rho = 1.225 # (Float, kg/m**3): density of air
turbine.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air
turbine.shear_exponent = 0.2 # (Float): shear exponent
turbine.hub_height = 90.0 # (Float, m): hub height
turbine.turbine_class = 'I' # (Enum): IEC turbine class
turbine.turbulence_class = 'B' # (Enum): IEC turbulence class class
turbine.cdf_reference_height_wind_speed = 90.0 # (Float): reference hub height for IEC wind speed (used in CDF calculation)
turbine.g = 9.81 # (Float, m/s**2): acceleration of gravity
# ======================
# === rotor ===
# --- blade grid ---
turbine.rotor.initial_aero_grid = np.array([
0.02222276, 0.06666667, 0.11111057, 0.16666667, 0.23333333, 0.3,
0.36666667, 0.43333333, 0.5, 0.56666667, 0.63333333, 0.7, 0.76666667,
0.83333333, 0.88888943, 0.93333333, 0.97777724
]) # (Array): initial aerodynamic grid on unit radius
turbine.rotor.initial_str_grid = np.array([
0.0, 0.00492790457512, 0.00652942887106, 0.00813095316699,
0.00983257273154, 0.0114340970275, 0.0130356213234, 0.02222276,
0.024446481932, 0.026048006228, 0.06666667, 0.089508406455, 0.11111057,
0.146462614229, 0.16666667, 0.195309105255, 0.23333333, 0.276686558545,
0.3, 0.333640766319, 0.36666667, 0.400404310407, 0.43333333, 0.5,
0.520818918408, 0.56666667, 0.602196371696, 0.63333333, 0.667358391486,
0.683573824984, 0.7, 0.73242031601, 0.76666667, 0.83333333, 0.88888943,
0.93333333, 0.97777724, 1.0
]) # (Array): initial structural grid on unit radius
turbine.rotor.idx_cylinder_aero = 3 # (Int): first idx in r_aero_unit of non-cylindrical section, constant twist inboard of here
turbine.rotor.idx_cylinder_str = 14 # (Int): first idx in r_str_unit of non-cylindrical section
turbine.rotor.hubFraction = 0.025 # (Float): hub location as fraction of radius
# ------------------
# --- blade geometry ---
turbine.rotor.r_aero = np.array([
0.02222276, 0.06666667, 0.11111057, 0.2, 0.23333333, 0.3, 0.36666667,
0.43333333, 0.5, 0.56666667, 0.63333333, 0.64, 0.7, 0.83333333,
0.88888943, 0.93333333, 0.97777724
]) # (Array): new aerodynamic grid on unit radius
turbine.rotor.r_max_chord = 0.23577 # (Float): location of max chord on unit radius
turbine.rotor.chord_sub = [
3.2612, 4.5709, 3.3178, 1.4621
] # (Array, m): chord at control points. defined at hub, then at linearly spaced locations from r_max_chord to tip
turbine.rotor.theta_sub = [
13.2783, 7.46036, 2.89317, -0.0878099
] # (Array, deg): twist at control points. defined at linearly spaced locations from r[idx_cylinder] to tip
turbine.rotor.precurve_sub = [
0.0, 0.0, 0.0
] # (Array, m): precurve at control points. defined at same locations at chord, starting at 2nd control point (root must be zero precurve)
turbine.rotor.delta_precurve_sub = [
0.0, 0.0, 0.0
] # (Array, m): adjustment to precurve to account for curvature from loading
turbine.rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398
] # (Array, m): spar cap thickness parameters
turbine.rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569
] # (Array, m): trailing-edge thickness parameters
turbine.rotor.bladeLength = 61.5 # (Float, m): blade length (if not precurved or swept) otherwise length of blade before curvature
turbine.rotor.delta_bladeLength = 0.0 # (Float, m): adjustment to blade length to account for curvature from loading
turbine.rotor.precone = 2.5 # (Float, deg): precone angle
turbine.rotor.tilt = 5.0 # (Float, deg): shaft tilt
turbine.rotor.yaw = 0.0 # (Float, deg): yaw error
turbine.rotor.nBlades = 3 # (Int): number of blades
# ------------------
# --- airfoil files ---
import rotorse
#basepath = os.path.join('5MW_files', '5MW_AFFiles')
basepath = os.path.join('..', 'reference_turbines', 'nrel5mw', 'airfoils')
# 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]]
turbine.rotor.airfoil_files = af # (List): names of airfoil file
# ----------------------
# --- control ---
turbine.rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed
turbine.rotor.control.Vout = 25.0 # (Float, m/s): cut-out wind speed
turbine.rotor.control.ratedPower = 5e6 # (Float, W): rated power
turbine.rotor.control.minOmega = 0.0 # (Float, rpm): minimum allowed rotor rotation speed
turbine.rotor.control.maxOmega = 12.0 # (Float, rpm): maximum allowed rotor rotation speed
turbine.rotor.control.tsr = 7.55 # (Float): tip-speed ratio in Region 2 (should be optimized externally)
turbine.rotor.control.pitch = 0.0 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines)
turbine.rotor.pitch_extreme = 0.0 # (Float, deg): worst-case pitch at survival wind condition
turbine.rotor.azimuth_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition
turbine.rotor.VfactorPC = 0.7 # (Float): fraction of rated speed at which the deflection is assumed to representative throughout the power curve calculation
# ----------------------
# --- aero and structural analysis options ---
turbine.rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power
turbine.rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at
turbine.rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve
turbine.rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.)
turbine.rotor.drivetrainType = 'geared' # (Enum)
turbine.rotor.nF = 5 # (Int): number of natural frequencies to compute
turbine.rotor.dynamic_amplication_tip_deflection = 1.35 # (Float): a dynamic amplification factor to adjust the static deflection calculation
# ----------------------
# --- materials and composite layup ---
#basepath = os.path.join('5MW_files', '5MW_PrecompFiles')
basepath = os.path.join('..', 'reference_turbines', 'nrel5mw', 'blade')
materials = Orthotropic2DMaterial.listFromPreCompFile(
os.path.join(basepath, 'materials.inp'))
ncomp = len(turbine.rotor.initial_str_grid)
upper = [0] * ncomp
lower = [0] * ncomp
webs = [0] * ncomp
profile = [0] * ncomp
turbine.rotor.leLoc = np.array(
[
0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.498, 0.497, 0.465, 0.447,
0.43, 0.411, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4,
0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4
]
) # (Array): array of leading-edge positions from a reference blade axis (usually blade pitch axis). locations are normalized by the local chord length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference axis. positive in -x direction for airfoil-aligned coordinate system
turbine.rotor.sector_idx_strain_spar = [
2
] * ncomp # (Array): index of sector for spar (PreComp definition of sector)
turbine.rotor.sector_idx_strain_te = [
3
] * ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector)
web1 = np.array([
-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.4114, 0.4102, 0.4094,
0.3876, 0.3755, 0.3639, 0.345, 0.3342, 0.3313, 0.3274, 0.323, 0.3206,
0.3172, 0.3138, 0.3104, 0.307, 0.3003, 0.2982, 0.2935, 0.2899, 0.2867,
0.2833, 0.2817, 0.2799, 0.2767, 0.2731, 0.2664, 0.2607, 0.2562, 0.1886,
-1.0
])
web2 = np.array([
-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.5886, 0.5868, 0.5854,
0.5508, 0.5315, 0.5131, 0.4831, 0.4658, 0.4687, 0.4726, 0.477, 0.4794,
0.4828, 0.4862, 0.4896, 0.493, 0.4997, 0.5018, 0.5065, 0.5101, 0.5133,
0.5167, 0.5183, 0.5201, 0.5233, 0.5269, 0.5336, 0.5393, 0.5438, 0.6114,
-1.0
])
web3 = np.array([
-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0,
-1.0, -1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0,
1.0, 1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0
])
turbine.rotor.chord_str_ref = np.array(
[
3.2612, 3.3100915356, 3.32587052924, 3.34159388653, 3.35823798667,
3.37384375335, 3.38939112914, 3.4774055542, 3.49839685,
3.51343645709, 3.87017220335, 4.04645623801, 4.19408216643,
4.47641008477, 4.55844487985, 4.57383098262, 4.57285771934,
4.51914315648, 4.47677655262, 4.40075650022, 4.31069949379,
4.20483735936, 4.08985563932, 3.82931757126, 3.74220276467,
3.54415796922, 3.38732428502, 3.24931446473, 3.23421422609,
3.22701537997, 3.21972125648, 3.08979310611, 2.95152261813,
2.330753331, 2.05553464181, 1.82577817774, 1.5860853279, 1.4621
]
) # (Array, m): chord distribution for reference section, thickness of structural layup scaled with reference thickness (fixed t/c for this case)
for i in range(ncomp):
webLoc = []
if web1[i] != -1:
webLoc.append(web1[i])
if web2[i] != -1:
webLoc.append(web2[i])
if web3[i] != -1:
webLoc.append(web3[i])
upper[i], lower[i], webs[
i] = CompositeSection.initFromPreCompLayupFile(
os.path.join(basepath, 'layup_' + str(i + 1) + '.inp'), webLoc,
materials)
profile[i] = Profile.initFromPreCompFile(
os.path.join(basepath, 'shape_' + str(i + 1) + '.inp'))
turbine.rotor.materials = materials # (List): list of all Orthotropic2DMaterial objects used in defining the geometry
turbine.rotor.upperCS = upper # (List): list of CompositeSection objections defining the properties for upper surface
turbine.rotor.lowerCS = lower # (List): list of CompositeSection objections defining the properties for lower surface
turbine.rotor.websCS = webs # (List): list of CompositeSection objections defining the properties for shear webs
turbine.rotor.profile = profile # (List): airfoil shape at each radial position
# --------------------------------------
strain_ult_spar = 1.0e-2
strain_ult_te = 2500 * 1e-6
# --- fatigue ---
turbine.rotor.rstar_damage = np.array([
0.000, 0.022, 0.067, 0.111, 0.167, 0.233, 0.300, 0.367, 0.433, 0.500,
0.567, 0.633, 0.700, 0.767, 0.833, 0.889, 0.933, 0.978
]) # (Array): nondimensional radial locations of damage equivalent moments
turbine.rotor.Mxb_damage = 1e3 * np.array([
2.3743E+003, 2.0834E+003, 1.8108E+003, 1.5705E+003, 1.3104E+003,
1.0488E+003, 8.2367E+002, 6.3407E+002, 4.7727E+002, 3.4804E+002,
2.4458E+002, 1.6339E+002, 1.0252E+002, 5.7842E+001, 2.7349E+001,
1.1262E+001, 3.8549E+000, 4.4738E-001
]) # (Array, N*m): damage equivalent moments about blade c.s. x-direction
turbine.rotor.Myb_damage = 1e3 * np.array([
2.7732E+003, 2.8155E+003, 2.6004E+003, 2.3933E+003, 2.1371E+003,
1.8459E+003, 1.5582E+003, 1.2896E+003, 1.0427E+003, 8.2015E+002,
6.2449E+002, 4.5229E+002, 3.0658E+002, 1.8746E+002, 9.6475E+001,
4.2677E+001, 1.5409E+001, 1.8426E+000
]) # (Array, N*m): damage equivalent moments about blade c.s. y-direction
turbine.rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap
turbine.rotor.strain_ult_te = 2500 * 1e-6 * 2 # (Float): uptimate strain in trailing-edge panels, note that I am putting a factor of two for the damage part only.
turbine.rotor.eta_damage = 1.35 * 1.3 * 1.0 # (Float): safety factor for fatigue
turbine.rotor.m_damage = 10.0 # (Float): slope of S-N curve for fatigue analysis
turbine.rotor.N_damage = 365 * 24 * 3600 * 20.0 # (Float): number of cycles used in fatigue analysis TODO: make function of rotation speed
# ----------------
# =================
# === nacelle ======
turbine.nacelle.L_ms = 1.0 # (Float, m): main shaft length downwind of main bearing in low-speed shaft
turbine.nacelle.L_mb = 2.5 # (Float, m): main shaft length in low-speed shaft
turbine.nacelle.h0_front = 1.7 # (Float, m): height of Ibeam in bedplate front
turbine.nacelle.h0_rear = 1.35 # (Float, m): height of Ibeam in bedplate rear
turbine.nacelle.drivetrain_design = 'geared'
turbine.nacelle.crane = True # (Bool): flag for presence of crane
turbine.nacelle.bevel = 0 # (Int): Flag for the presence of a bevel stage - 1 if present, 0 if not
turbine.nacelle.gear_configuration = 'eep' # (Str): tring that represents the configuration of the gearbox (stage number and types)
turbine.nacelle.Np = [3, 3, 1] # (Array): number of planets in each stage
turbine.nacelle.ratio_type = 'optimal' # (Str): optimal or empirical stage ratios
turbine.nacelle.shaft_type = 'normal' # (Str): normal or short shaft length
#turbine.nacelle.shaft_angle = 5.0 # (Float, deg): Angle of the LSS inclindation with respect to the horizontal
turbine.nacelle.shaft_ratio = 0.10 # (Float): Ratio of inner diameter to outer diameter. Leave zero for solid LSS
turbine.nacelle.carrier_mass = 8000.0 # estimated for 5 MW
turbine.nacelle.mb1Type = 'CARB' # (Str): Main bearing type: CARB, TRB or SRB
turbine.nacelle.mb2Type = 'SRB' # (Str): Second bearing type: CARB, TRB or SRB
turbine.nacelle.yaw_motors_number = 8.0 # (Float): number of yaw motors
turbine.nacelle.uptower_transformer = True
turbine.nacelle.flange_length = 0.5 #m
turbine.nacelle.gearbox_cm = 0.1
turbine.nacelle.hss_length = 1.5
turbine.nacelle.overhang = 5.0 #TODO - should come from turbine configuration level
turbine.nacelle.check_fatigue = 0 #0 if no fatigue check, 1 if parameterized fatigue check, 2 if known loads inputs
# TODO: should come from rotor (these are FAST outputs)
turbine.nacelle.DrivetrainEfficiency = 0.95
#turbine.nacelle.rotor_bending_moment_x = 330770.0# Nm
#turbine.nacelle.rotor_bending_moment_y = -16665000.0 # Nm
#turbine.nacelle.rotor_bending_moment_z = 2896300.0 # Nm
#turbine.nacelle.rotor_force_x = 599610.0 # N
#turbine.nacelle.rotor_force_y = 186780.0 # N
#turbine.nacelle.rotor_force_z = -842710.0 # N'''
#turbine.nacelle.h0_rear = 1.35 # only used in drive smooth
#turbine.nacelle.h0_front = 1.7
# =================
# === tower ===
# ---- tower ------
turbine.tower.replace('wind1', PowerWind())
turbine.tower.replace('wind2', PowerWind())
# onshore (no waves)
if turbine.sea_depth <> 0.0:
turbine.tower.replace('wave1', LinearWaves())
turbine.tower.replace('wave2', LinearWaves())
turbine.tower.wave1.Uc = 0.0
turbine.tower.wave1.hs = 8.0 * 1.86
turbine.tower.wave1.T = 10.0
turbine.tower.wave1.z_surface = 0.0
turbine.tower.wave1.z_floor = -sea_depth
turbine.tower.wave1.g = 9.81
turbine.tower.wave1.betaWave = 0.0
turbine.tower.wave2.Uc = 0.0
turbine.tower.wave2.hs = 8.0 * 1.86
turbine.tower.wave2.T = 10.0
turbine.tower.wave2.z_surface = 0.0
turbine.tower.wave2.z_floor = -sea_depth
turbine.tower.wave2.g = 9.81
turbine.tower.wave2.betaWave = 0.0
if turbine.sea_depth == 0.0:
# --- geometry ----
#np.insert(turbine.tower.z_param,0,87.9)
#np.insert(turbine.tower.z_param,0,43.8)
#np.insert(turbine.tower.z_param,0,0.0)
turbine.tower.z_param = [0.0, 43.8, 87.9]
turbine.tower_d = [6.0, 4.935, 3.87]
turbine.tower.t_param = [0.027 * 1.3, 0.023 * 1.3, 0.019 * 1.3]
n = 15
turbine.tower.z_full = np.linspace(0.0, 87.6, n)
turbine.tower.L_reinforced = 30.0 * np.ones(n) # [m] buckling length
turbine.tower.theta_stress = 0.0 * np.ones(n)
turbine.tower.yaw = 0.0
# --- material props ---
turbine.tower.E = 210e9 * np.ones(n)
turbine.tower.G = 80.8e9 * np.ones(n)
turbine.tower.rho = 8500.0 * np.ones(n)
turbine.tower.sigma_y = 450.0e6 * np.ones(n)
else:
# --- geometry ----
#np.insert(turbine.tower.z_param,0,87.9)
#np.insert(turbine.tower.z_param,0,43.8)
#np.insert(turbine.tower.z_param,0,0.0)
#np.insert(turbine.tower.z_param,0,-20.0)
turbine.tower.z_param = [-20.0, 0.0, 43.8, 87.9]
turbine.tower_d = [6.0, 6.0, 4.935, 3.87]
turbine.tower.t_param = [0.06, 0.027 * 1.3, 0.023 * 1.3, 0.019 * 1.3]
n = 20
turbine.tower.z_full = np.linspace(-20, 87.6, n)
turbine.tower.L_reinforced = 30.0 * np.ones(n) # [m] buckling length
turbine.tower.theta_stress = 0.0 * np.ones(n)
turbine.tower.yaw = 0.0
# --- material props ---
turbine.tower.E = 210e9 * np.ones(n)
turbine.tower.G = 80.8e9 * np.ones(n)
turbine.tower.rho = 8500.0 * np.ones(n)
turbine.tower.sigma_y = 450.0e6 * np.ones(n)
# --- spring reaction data. Use float('inf') for rigid constraints. ---
turbine.tower.kidx = [0] # applied at base
turbine.tower.kx = [float('inf')]
turbine.tower.ky = [float('inf')]
turbine.tower.kz = [float('inf')]
turbine.tower.ktx = [float('inf')]
turbine.tower.kty = [float('inf')]
turbine.tower.ktz = [float('inf')]
# --- extra mass ----
turbine.tower.midx = [n - 1] # RNA mass at top
turbine.tower.m = [285598.8]
turbine.tower.mIxx = [1.14930678e+08]
turbine.tower.mIyy = [2.20354030e+07]
turbine.tower.mIzz = [1.87597425e+07]
turbine.tower.mIxy = [0.00000000e+00]
turbine.tower.mIxz = [5.03710467e+05]
turbine.tower.mIyz = [0.00000000e+00]
turbine.tower.mrhox = [-1.13197635]
turbine.tower.mrhoy = [0.]
turbine.tower.mrhoz = [0.50875268]
turbine.tower.addGravityLoadForExtraMass = True
# -----------
# --- wind ---
#turbine.tower.wind_zref = 90.0
turbine.tower.wind_z0 = 0.0
turbine.tower.wind1.shearExp = 0.2
turbine.tower.wind2.shearExp = 0.2
# ---------------
# if addGravityLoadForExtraMass=True be sure not to double count by adding those force here also
# # --- loading case 1: max Thrust ---
#turbine.tower.wind_Uref1 = 11.73732
turbine.tower.plidx1 = [n - 1] # at tower top
turbine.tower.Fx1 = [1284744.19620519]
turbine.tower.Fy1 = [0.]
turbine.tower.Fz1 = [-2914124.84400512]
turbine.tower.Mxx1 = [3963732.76208099]
turbine.tower.Myy1 = [-2275104.79420872]
turbine.tower.Mzz1 = [-346781.68192839]
# # ---------------
# # --- loading case 2: max wind speed ---
#turbine.tower.wind_Uref2 = 70.0
turbine.tower.plidx2 = [n - 1] # at tower top
turbine.tower.Fx2 = [930198.60063279]
turbine.tower.Fy2 = [0.]
turbine.tower.Fz2 = [-2883106.12368949]
turbine.tower.Mxx2 = [-1683669.22411597]
turbine.tower.Myy2 = [-2522475.34625363]
turbine.tower.Mzz2 = [147301.97023764]
# # ---------------
# --- safety factors ---
turbine.tower.gamma_f = 1.35
turbine.tower.gamma_m = 1.3
turbine.tower.gamma_n = 1.0
turbine.tower.gamma_b = 1.1
# ---------------
# --- fatigue ---
turbine.tower.z_DEL = np.array([
0.000, 1.327, 3.982, 6.636, 9.291, 11.945, 14.600, 17.255, 19.909,
22.564, 25.218, 27.873, 30.527, 33.182, 35.836, 38.491, 41.145, 43.800,
46.455, 49.109, 51.764, 54.418, 57.073, 59.727, 62.382, 65.036, 67.691,
70.345, 73.000, 75.655, 78.309, 80.964, 83.618, 86.273, 87.600
])
turbine.tower.M_DEL = 1e3 * np.array([
8.2940E+003, 8.1518E+003, 7.8831E+003, 7.6099E+003, 7.3359E+003,
7.0577E+003, 6.7821E+003, 6.5119E+003, 6.2391E+003, 5.9707E+003,
5.7070E+003, 5.4500E+003, 5.2015E+003, 4.9588E+003, 4.7202E+003,
4.4884E+003, 4.2577E+003, 4.0246E+003, 3.7942E+003, 3.5664E+003,
3.3406E+003, 3.1184E+003, 2.8977E+003, 2.6811E+003, 2.4719E+003,
2.2663E+003, 2.0673E+003, 1.8769E+003, 1.7017E+003, 1.5479E+003,
1.4207E+003, 1.3304E+003, 1.2780E+003, 1.2673E+003, 1.2761E+003
])
turbine.tower.gamma_fatigue = 1.35 * 1.3 * 1.0
turbine.tower.life = 20.0
turbine.tower.m_SN = 4
# ---------------
# --- constraints ---
turbine.tower.min_d_to_t = 120.0
turbine.tower.min_taper = 0.4
# ---------------
# ==== Other options
if wind_class == 'I':
turbine.rotor.turbine_class = 'I'
elif wind_class == 'III':
turbine.rotor.turbine_class = 'III'
# for fatigue based analysis of class III wind turbine
turbine.tower.M_DEL = 1.028713178 * 1e3 * np.array([
7.8792E+003, 7.7507E+003, 7.4918E+003, 7.2389E+003, 6.9815E+003,
6.7262E+003, 6.4730E+003, 6.2174E+003, 5.9615E+003, 5.7073E+003,
5.4591E+003, 5.2141E+003, 4.9741E+003, 4.7399E+003, 4.5117E+003,
4.2840E+003, 4.0606E+003, 3.8360E+003, 3.6118E+003, 3.3911E+003,
3.1723E+003, 2.9568E+003, 2.7391E+003, 2.5294E+003, 2.3229E+003,
2.1246E+003, 1.9321E+003, 1.7475E+003, 1.5790E+003, 1.4286E+003,
1.3101E+003, 1.2257E+003, 1.1787E+003, 1.1727E+003, 1.1821E+003
])
turbine.rotor.Mxb_damage = 1e3 * np.array([
2.3617E+003, 2.0751E+003, 1.8051E+003, 1.5631E+003, 1.2994E+003,
1.0388E+003, 8.1384E+002, 6.2492E+002, 4.6916E+002, 3.4078E+002,
2.3916E+002, 1.5916E+002, 9.9752E+001, 5.6139E+001, 2.6492E+001,
1.0886E+001, 3.7210E+000, 4.3206E-001
])
turbine.rotor.Myb_damage = 1e3 * np.array([
2.5492E+003, 2.6261E+003, 2.4265E+003, 2.2308E+003, 1.9882E+003,
1.7184E+003, 1.4438E+003, 1.1925E+003, 9.6251E+002, 7.5564E+002,
5.7332E+002, 4.1435E+002, 2.8036E+002, 1.7106E+002, 8.7732E+001,
3.8678E+001, 1.3942E+001, 1.6600E+000
])
elif wind_class == 'Offshore':
turbine.rotor.turbine_class = 'I'
# TODO: these should be specified at the turbine level and connected to other system inputs
if turbine.sea_depth == 0.0:
turbine.tower_d = [6.0, 4.935,
3.87] # (Array, m): diameters along tower
else:
turbine.tower_d = [6.0, 6.0, 4.935, 3.87]
turbine.generator_speed = 1173.7 # (Float, rpm) # generator speed
# --- aero and structural analysis options ---
rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power
rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at
rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve
rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.)
rotor.drivetrainType = 'geared' # (Enum)
rotor.nF = 5 # (Int): number of natural frequencies to compute
rotor.dynamic_amplication_tip_deflection = 1.35 # (Float): a dynamic amplification factor to adjust the static deflection calculation
# ----------------------
# --- materials and composite layup ---
basepath = os.path.join(os.path.dirname(rotorse.__file__), '5MW_PreCompFiles')
# basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), '5MW_PrecompFiles')
materials = Orthotropic2DMaterial.listFromPreCompFile(os.path.join(basepath, 'materials.inp'))
ncomp = len(rotor.initial_str_grid)
upper = [0]*ncomp
lower = [0]*ncomp
webs = [0]*ncomp
profile = [0]*ncomp
rotor.leLoc = np.array([0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.498, 0.497, 0.465, 0.447, 0.43, 0.411,
0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4,
0.4, 0.4, 0.4, 0.4]) # (Array): array of leading-edge positions from a reference blade axis (usually blade pitch axis). locations are normalized by the local chord length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference axis. positive in -x direction for airfoil-aligned coordinate system
rotor.sector_idx_strain_spar = [2]*ncomp # (Array): index of sector for spar (PreComp definition of sector)
rotor.sector_idx_strain_te = [3]*ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector)
web1 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.4114, 0.4102, 0.4094, 0.3876, 0.3755, 0.3639, 0.345, 0.3342, 0.3313, 0.3274, 0.323, 0.3206, 0.3172, 0.3138, 0.3104, 0.307, 0.3003, 0.2982, 0.2935, 0.2899, 0.2867, 0.2833, 0.2817, 0.2799, 0.2767, 0.2731, 0.2664, 0.2607, 0.2562, 0.1886, -1.0])
web2 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.5886, 0.5868, 0.5854, 0.5508, 0.5315, 0.5131, 0.4831, 0.4658, 0.4687, 0.4726, 0.477, 0.4794, 0.4828, 0.4862, 0.4896, 0.493, 0.4997, 0.5018, 0.5065, 0.5101, 0.5133, 0.5167, 0.5183, 0.5201, 0.5233, 0.5269, 0.5336, 0.5393, 0.5438, 0.6114, -1.0])
web3 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0])
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 example(wind_class='I',sea_depth=0.0,with_new_nacelle=False,with_landbos=False,flexible_blade=False,with_3pt_drive=False, with_ecn_opex=False, ecn_file=None,with_openwind=False,ow_file=None,ow_wkbook=None):
"""
Inputs:
wind_class : str ('I', 'III', 'Offshore' - selected wind class for project)
sea_depth : float (sea depth if an offshore wind plant)
"""
# === Create LCOE SE assembly ========
lcoe_se = lcoe_se_assembly(with_new_nacelle,with_landbos,flexible_blade,with_3pt_drive,with_ecn_opex,ecn_file)
# === Set assembly variables and objects ===
lcoe_se.sea_depth = sea_depth # 0.0 for land-based turbine
lcoe_se.turbine_number = 100
lcoe_se.year = 2009
lcoe_se.month = 12
rotor = lcoe_se.rotor
nacelle = lcoe_se.nacelle
jacket = lcoe_se.jacket
tcc_a = lcoe_se.tcc_a
# bos_a = lcoe_se.bos_a
# opex_a = lcoe_se.opex_a
aep_a = lcoe_se.aep_a
fin_a = lcoe_se.fin_a
# Turbine ===========
from wisdem.reference_turbines.nrel5mw.nrel5mw_jacket import configure_nrel5mw_turbine_with_jacket
configure_nrel5mw_turbine_with_jacket(lcoe_se,wind_class,lcoe_se.sea_depth)
# TODO: these should be specified at the turbine level and connected to other system inputs
lcoe_se.tower_dt = 3.87 # (Array, m): diameters along tower # float for jacket
lcoe_se.generator_speed = 1173.7 # (Float, rpm) # generator speed
# extra variable constant for now
#lcoe_se.nacelle.bedplate.rotor_bending_moment_y = -2.3250E+06 # shouldnt be needed anymore
# tcc ====
lcoe_se.advanced_blade = True
lcoe_se.offshore = False
lcoe_se.assemblyCostMultiplier = 0.30
lcoe_se.profitMultiplier = 0.20
lcoe_se.overheadCostMultiplier = 0.0
lcoe_se.transportMultiplier = 0.0
# for new landBOS
''' # === new landBOS ===
lcoe_se.voltage = 137
lcoe_se.distInter = 5
lcoe_se.terrain = 'FLAT_TO_ROLLING'
lcoe_se.layout = 'SIMPLE'
lcoe_se.soil = 'STANDARD' '''
# aep ====
if not with_openwind:
lcoe_se.array_losses = 0.059
lcoe_se.other_losses = 0.0
if not with_ecn_opex:
lcoe_se.availability = 0.94
# fin ===
lcoe_se.fixed_charge_rate = 0.095
lcoe_se.construction_finance_rate = 0.0
lcoe_se.tax_rate = 0.4
lcoe_se.discount_rate = 0.07
lcoe_se.construction_time = 1.0
lcoe_se.project_lifetime = 20.0
# Set plant level inputs ===
shearExp = 0.2 #TODO : should be an input to lcoe
rotor.cdf_reference_height_wind_speed = 90.0
if not with_openwind:
lcoe_se.array_losses = 0.1
lcoe_se.other_losses = 0.0
if not with_ecn_opex:
lcoe_se.availability = 0.98
rotor.turbulence_class = 'B'
lcoe_se.multiplier = 2.23
if wind_class == 'Offshore':
# rotor.cdf_reference_mean_wind_speed = 8.4 # TODO - aep from its own module
# rotor.cdf_reference_height_wind_speed = 50.0
# rotor.weibull_shape = 2.1
shearExp = 0.14 # TODO : should be an input to lcoe
lcoe_se.array_losses = 0.15
if not with_ecn_opex:
lcoe_se.availability = 0.96
lcoe_se.offshore = True
lcoe_se.multiplier = 2.33
lcoe_se.fixed_charge_rate = 0.118
rotor.shearExp = shearExp
#tower.wind1.shearExp = shearExp # not needed for jacket
#tower.wind2.shearExp = shearExp
# ====
from rotorse.precomp import Profile, Orthotropic2DMaterial, CompositeSection # TODO: can just pass file names and do this initialization inside of rotor
#from commonse.environment import PowerWind, TowerSoil
#from wisdem.reference_turbines.nrel5mw.nrel5mw_jacket import configure_nrel5mw_turbine_with_jacket
from commonse.utilities import print_vars
#configure_nrel5mw_turbine_with_jacket(turbine)
# print_vars(turbine, list_type='inputs', prefix='turbine')
rotor = lcoe_se.rotor
nacelle = lcoe_se.nacelle
jacket = lcoe_se.jacket
# =================
# === Turbine Configuration ===
# --- atmosphere ---
lcoe_se.rho = 1.225 # (Float, kg/m**3): density of air
lcoe_se.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air
lcoe_se.shear_exponent = 0.2 # (Float): shear exponent
lcoe_se.hub_height = 90.0 # (Float, m): hub height
lcoe_se.turbine_class = 'I' # (Enum): IEC turbine class
lcoe_se.turbulence_class = 'B' # (Enum): IEC turbulence class class
lcoe_se.cdf_reference_height_wind_speed = 90.0 # (Float): reference hub height for IEC wind speed (used in CDF calculation)
lcoe_se.g = 9.81 # (Float, m/s**2): acceleration of gravity
lcoe_se.downwind = False # (Bool): flag if rotor is downwind
lcoe_se.generator_speed = 1173.7 # (Float, rpm) # generator speed
lcoe_se.tower_dt = 3.87
# ----------------------
# ============================
# === rotor ===
# --- blade grid ---
rotor.initial_aero_grid = np.array([0.02222276, 0.06666667, 0.11111057, 0.16666667, 0.23333333, 0.3, 0.36666667,
0.43333333, 0.5, 0.56666667, 0.63333333, 0.7, 0.76666667, 0.83333333, 0.88888943, 0.93333333,
0.97777724]) # (Array): initial aerodynamic grid on unit radius
rotor.initial_str_grid = np.array([0.0, 0.00492790457512, 0.00652942887106, 0.00813095316699, 0.00983257273154,
0.0114340970275, 0.0130356213234, 0.02222276, 0.024446481932, 0.026048006228, 0.06666667, 0.089508406455,
0.11111057, 0.146462614229, 0.16666667, 0.195309105255, 0.23333333, 0.276686558545, 0.3, 0.333640766319,
0.36666667, 0.400404310407, 0.43333333, 0.5, 0.520818918408, 0.56666667, 0.602196371696, 0.63333333,
0.667358391486, 0.683573824984, 0.7, 0.73242031601, 0.76666667, 0.83333333, 0.88888943, 0.93333333, 0.97777724,
1.0]) # (Array): initial structural grid on unit radius
rotor.idx_cylinder_aero = 3 # (Int): first idx in r_aero_unit of non-cylindrical section, constant twist inboard of here
rotor.idx_cylinder_str = 14 # (Int): first idx in r_str_unit of non-cylindrical section
rotor.hubFraction = 0.025 # (Float): hub location as fraction of radius
# ------------------
# --- blade geometry ---
rotor.r_aero = np.array([0.02222276, 0.06666667, 0.11111057, 0.2, 0.23333333, 0.3, 0.36666667, 0.43333333,
0.5, 0.56666667, 0.63333333, 0.64, 0.7, 0.83333333, 0.88888943, 0.93333333,
0.97777724]) # (Array): new aerodynamic grid on unit radius
rotor.r_max_chord = 0.23577 # (Float): location of max chord on unit radius
rotor.chord_sub = [3.2612, 4.5709, 3.3178, 1.4621] # (Array, m): chord at control points. defined at hub, then at linearly spaced locations from r_max_chord to tip
rotor.theta_sub = [13.2783, 7.46036, 2.89317, -0.0878099] # (Array, deg): twist at control points. defined at linearly spaced locations from r[idx_cylinder] to tip
rotor.precurve_sub = [0.0, 0.0, 0.0] # (Array, m): precurve at control points. defined at same locations at chord, starting at 2nd control point (root must be zero precurve)
rotor.delta_precurve_sub = [0.0, 0.0, 0.0] # (Array, m): adjustment to precurve to account for curvature from loading
rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398] # (Array, m): spar cap thickness parameters
rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569] # (Array, m): trailing-edge thickness parameters
rotor.bladeLength = 61.5 # (Float, m): blade length (if not precurved or swept) otherwise length of blade before curvature
rotor.delta_bladeLength = 0.0 # (Float, m): adjustment to blade length to account for curvature from loading
rotor.precone = 2.5 # (Float, deg): precone angle
rotor.tilt = 5.0 # (Float, deg): shaft tilt
rotor.yaw = 0.0 # (Float, deg): yaw error
rotor.nBlades = 3 # (Int): number of blades
# ------------------
# --- airfoil files ---
import rotorse
basepath = os.path.join(os.path.dirname(rotorse.__file__), '5MW_AFFiles')
# basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), '5MW_AFFiles')
# load all airfoils
airfoil_types = [0]*8
airfoil_types[0] = os.path.join(basepath, 'Cylinder1.dat')
airfoil_types[1] = os.path.join(basepath, 'Cylinder2.dat')
airfoil_types[2] = os.path.join(basepath, 'DU40_A17.dat')
airfoil_types[3] = os.path.join(basepath, 'DU35_A17.dat')
airfoil_types[4] = os.path.join(basepath, 'DU30_A17.dat')
airfoil_types[5] = os.path.join(basepath, 'DU25_A17.dat')
airfoil_types[6] = os.path.join(basepath, 'DU21_A17.dat')
airfoil_types[7] = os.path.join(basepath, 'NACA64_A17.dat')
# place at appropriate radial stations
af_idx = [0, 0, 1, 2, 3, 3, 4, 5, 5, 6, 6, 7, 7, 7, 7, 7, 7]
n = len(af_idx)
af = [0]*n
for i in range(n):
af[i] = airfoil_types[af_idx[i]]
rotor.airfoil_files = af # (List): names of airfoil file
# ----------------------
# --- control ---
rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed
rotor.control.Vout = 25.0 # (Float, m/s): cut-out wind speed
#rotor.control.ratedPower = 5e6 # (Float, W): rated power
lcoe_se.machine_rating = 5e3 # (Float, kW): rated power
rotor.control.minOmega = 0.0 # (Float, rpm): minimum allowed rotor rotation speed
rotor.control.maxOmega = 12.0 # (Float, rpm): maximum allowed rotor rotation speed
rotor.control.tsr = 7.55 # (Float): tip-speed ratio in Region 2 (should be optimized externally)
rotor.control.pitch = 0.0 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines)
rotor.pitch_extreme = 0.0 # (Float, deg): worst-case pitch at survival wind condition
rotor.azimuth_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition
rotor.VfactorPC = 0.7 # (Float): fraction of rated speed at which the deflection is assumed to representative throughout the power curve calculation
# ----------------------
# --- aero and structural analysis options ---
rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power
rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at
rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve
rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.)
rotor.drivetrainType = 'geared' # (Enum)
rotor.nF = 5 # (Int): number of natural frequencies to compute
rotor.dynamic_amplication_tip_deflection = 1.35 # (Float): a dynamic amplification factor to adjust the static deflection calculation
# ----------------------
# --- materials and composite layup ---
basepath = os.path.join(os.path.dirname(rotorse.__file__), '5MW_PreCompFiles')
# basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), '5MW_PrecompFiles')
materials = Orthotropic2DMaterial.listFromPreCompFile(os.path.join(basepath, 'materials.inp'))
ncomp = len(rotor.initial_str_grid)
upper = [0]*ncomp
lower = [0]*ncomp
webs = [0]*ncomp
profile = [0]*ncomp
rotor.leLoc = np.array([0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.498, 0.497, 0.465, 0.447, 0.43, 0.411,
0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4,
0.4, 0.4, 0.4, 0.4]) # (Array): array of leading-edge positions from a reference blade axis (usually blade pitch axis). locations are normalized by the local chord length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference axis. positive in -x direction for airfoil-aligned coordinate system
rotor.sector_idx_strain_spar = [2]*ncomp # (Array): index of sector for spar (PreComp definition of sector)
rotor.sector_idx_strain_te = [3]*ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector)
web1 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.4114, 0.4102, 0.4094, 0.3876, 0.3755, 0.3639, 0.345, 0.3342, 0.3313, 0.3274, 0.323, 0.3206, 0.3172, 0.3138, 0.3104, 0.307, 0.3003, 0.2982, 0.2935, 0.2899, 0.2867, 0.2833, 0.2817, 0.2799, 0.2767, 0.2731, 0.2664, 0.2607, 0.2562, 0.1886, -1.0])
web2 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.5886, 0.5868, 0.5854, 0.5508, 0.5315, 0.5131, 0.4831, 0.4658, 0.4687, 0.4726, 0.477, 0.4794, 0.4828, 0.4862, 0.4896, 0.493, 0.4997, 0.5018, 0.5065, 0.5101, 0.5133, 0.5167, 0.5183, 0.5201, 0.5233, 0.5269, 0.5336, 0.5393, 0.5438, 0.6114, -1.0])
web3 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0])
rotor.chord_str_ref = np.array([3.2612, 3.3100915356, 3.32587052924, 3.34159388653, 3.35823798667, 3.37384375335,
3.38939112914, 3.4774055542, 3.49839685, 3.51343645709, 3.87017220335, 4.04645623801, 4.19408216643,
4.47641008477, 4.55844487985, 4.57383098262, 4.57285771934, 4.51914315648, 4.47677655262, 4.40075650022,
4.31069949379, 4.20483735936, 4.08985563932, 3.82931757126, 3.74220276467, 3.54415796922, 3.38732428502,
3.24931446473, 3.23421422609, 3.22701537997, 3.21972125648, 3.08979310611, 2.95152261813, 2.330753331,
2.05553464181, 1.82577817774, 1.5860853279, 1.4621]) # (Array, m): chord distribution for reference section, thickness of structural layup scaled with reference thickness (fixed t/c for this case)
for i in range(ncomp):
webLoc = []
if web1[i] != -1:
webLoc.append(web1[i])
if web2[i] != -1:
webLoc.append(web2[i])
if web3[i] != -1:
webLoc.append(web3[i])
upper[i], lower[i], webs[i] = CompositeSection.initFromPreCompLayupFile(os.path.join(basepath, 'layup_' + str(i+1) + '.inp'), webLoc, materials)
profile[i] = Profile.initFromPreCompFile(os.path.join(basepath, 'shape_' + str(i+1) + '.inp'))
rotor.materials = materials # (List): list of all Orthotropic2DMaterial objects used in defining the geometry
rotor.upperCS = upper # (List): list of CompositeSection objections defining the properties for upper surface
rotor.lowerCS = lower # (List): list of CompositeSection objections defining the properties for lower surface
rotor.websCS = webs # (List): list of CompositeSection objections defining the properties for shear webs
rotor.profile = profile # (List): airfoil shape at each radial position
# --------------------------------------
# --- fatigue ---
rotor.rstar_damage = np.array([0.000, 0.022, 0.067, 0.111, 0.167, 0.233, 0.300, 0.367, 0.433, 0.500,
0.567, 0.633, 0.700, 0.767, 0.833, 0.889, 0.933, 0.978]) # (Array): nondimensional radial locations of damage equivalent moments
rotor.Mxb_damage = 1e3*np.array([2.3743E+003, 2.0834E+003, 1.8108E+003, 1.5705E+003, 1.3104E+003,
1.0488E+003, 8.2367E+002, 6.3407E+002, 4.7727E+002, 3.4804E+002, 2.4458E+002, 1.6339E+002,
1.0252E+002, 5.7842E+001, 2.7349E+001, 1.1262E+001, 3.8549E+000, 4.4738E-001]) # (Array, N*m): damage equivalent moments about blade c.s. x-direction
rotor.Myb_damage = 1e3*np.array([2.7732E+003, 2.8155E+003, 2.6004E+003, 2.3933E+003, 2.1371E+003,
1.8459E+003, 1.5582E+003, 1.2896E+003, 1.0427E+003, 8.2015E+002, 6.2449E+002, 4.5229E+002,
3.0658E+002, 1.8746E+002, 9.6475E+001, 4.2677E+001, 1.5409E+001, 1.8426E+000]) # (Array, N*m): damage equivalent moments about blade c.s. y-direction
rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap
rotor.strain_ult_te = 2500*1e-6 * 2 # (Float): uptimate strain in trailing-edge panels, note that I am putting a factor of two for the damage part only.
rotor.eta_damage = 1.35*1.3*1.0 # (Float): safety factor for fatigue
rotor.m_damage = 10.0 # (Float): slope of S-N curve for fatigue analysis
rotor.N_damage = 365*24*3600*20.0 # (Float): number of cycles used in fatigue analysis TODO: make function of rotation speed
# ----------------
# =================
# === nacelle ======
nacelle.L_ms = 1.0 # (Float, m): main shaft length downwind of main bearing in low-speed shaft
nacelle.L_mb = 2.5 # (Float, m): main shaft length in low-speed shaft
nacelle.h0_front = 1.7 # (Float, m): height of Ibeam in bedplate front
nacelle.h0_rear = 1.35 # (Float, m): height of Ibeam in bedplate rear
# TODO: sync with rotor drivetrainType variable
nacelle.drivetrain_design = 'geared'
nacelle.crane = True # (Bool): flag for presence of crane
nacelle.bevel = 0 # (Int): Flag for the presence of a bevel stage - 1 if present, 0 if not
nacelle.gear_configuration = 'eep' # (Str): tring that represents the configuration of the gearbox (stage number and types)
nacelle.Np = [3, 3, 1] # (Array): number of planets in each stage
nacelle.ratio_type = 'optimal' # (Str): optimal or empirical stage ratios
nacelle.shaft_type = 'normal' # (Str): normal or short shaft length
#nacelle.shaft_angle = 5.0 # (Float, deg): Angle of the LSS inclindation with respect to the horizontal
nacelle.shaft_ratio = 0.10 # (Float): Ratio of inner diameter to outer diameter. Leave zero for solid LSS
#nacelle.shrink_disc_mass = 1000.0 # (Float, kg): Mass of the shrink disc
nacelle.mb1Type = 'CARB' # (Str): Main bearing type: CARB, TRB or SRB
nacelle.mb2Type = 'SRB' # (Str): Second bearing type: CARB, TRB or SRB
nacelle.yaw_motors_number = 8.0 # (Float): number of yaw motors
nacelle.uptower_transformer = True
nacelle.flange_length = 0.5 #m
nacelle.gearbox_cm = 0.1
nacelle.hss_length = 1.5
nacelle.overhang = 5.0 #TODO - should come from turbine configuration level
nacelle.check_fatigue = 0 #0 if no fatigue check, 1 if parameterized fatigue check, 2 if known loads inputs
# TODO: should come from rotor (these are FAST outputs)
nacelle.DrivetrainEfficiency = 0.95
nacelle.rotor_bending_moment_x = 330770.0# Nm
nacelle.rotor_bending_moment_y = -16665000.0 # Nm
nacelle.rotor_bending_moment_z = 2896300.0 # Nm
nacelle.rotor_force_x = 599610.0 # N
nacelle.rotor_force_y = 186780.0 # N
nacelle.rotor_force_z = -842710.0 # N
#nacelle.h0_rear = 1.35 # only used in drive smooth
#nacelle.h0_front = 1.7
# =================
# === jacket ===
#--- Set Jacket Input Parameters ---#
Jcktins=JcktGeoInputs()
Jcktins.nlegs =4
Jcktins.nbays =5
Jcktins.batter=12.
Jcktins.dck_botz =16.
Jcktins.dck_width=2*6.
Jcktins.weld2D =0.5
Jcktins.VPFlag = True #vertical pile T/F; to enable piles in frame3DD set pileinputs.ndiv>0
Jcktins.clamped= False #whether or not the bottom of the structure is rigidly connected. Use False when equivalent spring constants are being used.
Jcktins.AFflag = False #whether or not to use apparent fixity piles
Jcktins.PreBuildTPLvl = 5 #if >0, the TP is prebuilt according to rules per PreBuildTP
#Soil inputs
Soilinputs=SoilGeoInputs()
Soilinputs.zbots =-np.array([3.,5.,7.,15.,30.,50.])
Soilinputs.gammas =np.array([10000.,10000.,10000.,10000.,10000.,10000.])
Soilinputs.cus =np.array([60000.,60000.,60000.,60000.,60000.,60000.])
Soilinputs.phis =np.array([26.,26.,26.,26.,26.,26])#np.array([36.,33.,26.,37.,35.,37.5])#np.array([36.,33.,26.,37.,35.,37.5])
Soilinputs.delta =25.
Soilinputs.sndflg =True
Soilinputs.PenderSwtch =False #True
Soilinputs.SoilSF =1.
Soilinputs2=copy.copy(Soilinputs) #Parked case. We assume same stiffness although this may not be the case under a different load
#Water and wind inputs
Waterinputs=WaterInputs()
Waterinputs.wdepth =30.
Waterinputs.wlevel =30. #Distance from bottom of structure to surface THIS, I believe is no longer needed as piles may be negative in z, to check and remove in case
Waterinputs.T=12. #Wave Period
Waterinputs.HW=10. #Wave Height
Waterinputs.Cd=3. #Drag Coefficient, enhanced to account for marine growth and other members not calculated
Waterinputs.Cm=8.#2. #ADded mass Coefficient
Waterinputs2=copy.copy(Waterinputs) #PARKED CONDITIONS - still max wave here
Waterinputs.T=8. #Wave Period
Waterinputs.HW=4. #Wave Height
Windinputs=WindInputs()
Windinputs.Cdj=4. #Drag Coefficient for jacket members, enhanced to account for TP drag not calculated otherwise
Windinputs.Cdt=2 #Drag Coefficient for tower, enhanced to account for TP drag not calculated otherwise
Windinputs.HH=100. #CHECK HOW THIS COMPLIES....
Windinputs.U50HH=30. #assumed gust speed
## if turbine_jacket
##Windinputs.HH=90. #CHECK HOW THIS COMPLIES....
##Windinputs.U50HH=11.7373200354 # using rated loads
##Windinputs.rho = 1.225
##Windinputs.mu = 1.81206e-05
Windinputs2=copy.copy(Windinputs)
Windinputs2.U50HH=70. #assumed gust speed
#Pile data
Pilematin=MatInputs()
Pilematin.matname=np.array(['steel'])
Pilematin.E=np.array([ 25.e9])
Dpile=2.5#0.75 # 2.0
tpile=0.01
Lp=20. #45
Pileinputs=PileGeoInputs()
Pileinputs.Pilematins=Pilematin
Pileinputs.ndiv=0 #3
Pileinputs.Dpile=Dpile
Pileinputs.tpile=tpile
Pileinputs.Lp=Lp #[m] Embedment length
#Legs data
legmatin=MatInputs()
legmatin.matname=(['heavysteel','heavysteel','heavysteel','heavysteel'])
#legmatin.E=np.array([2.0e11])
Dleg=np.array([1.5,1.5,1.5,1.5,1.5,1.5])
tleg=1.5*np.array([0.0254]).repeat(Dleg.size)
leginputs=LegGeoInputs()
leginputs.legZbot = 1.0
leginputs.ndiv=1
leginputs.legmatins=legmatin
leginputs.Dleg0=Dleg[0]
leginputs.tleg0=tleg[0]
legbot_stmphin =1.5 #Distance from bottom of leg to second joint along z; must be>0
#Xbrc data
Xbrcmatin=MatInputs()
Xbrcmatin.matname=np.array(['heavysteel']).repeat(Jcktins.nbays)
#Xbrcmatin.E=np.array([ 2.2e11, 2.0e11,2.0e11,2.0e11,2.0e11])
Dbrc=np.array([1.,1.,1.0,1.0,1.0])
tbrc=np.array([1.,1.,1.0,1.0,1.0])*0.0254
Xbrcinputs=XBrcGeoInputs()
Xbrcinputs.Dbrc0=Dbrc[0]
Xbrcinputs.tbrc0=tbrc[0]
Xbrcinputs.ndiv=2#2
Xbrcinputs.Xbrcmatins=Xbrcmatin
Xbrcinputs.precalc=False #True #This can be set to true if we want Xbraces to be precalculated in D and t, in which case the above set Dbrc and tbrc would be overwritten
#Mbrc data
Mbrcmatin=MatInputs()
Mbrcmatin.matname=np.array(['heavysteel'])
#Mbrcmatin.E=np.array([ 2.5e11])
Dbrc_mud=1.5
Mbrcinputs=MudBrcGeoInputs()
Mbrcinputs.Dbrc_mud=Dbrc_mud
Mbrcinputs.ndiv=2
Mbrcinputs.Mbrcmatins=Mbrcmatin
Mbrcinputs.precalc=False #True #This can be set to true if we want Mudbrace to be precalculated in D and t, in which case the above set Dbrc_mud and tbrc_mud would be overwritten
#Hbrc data
Hbrcmatin=MatInputs()
Hbrcmatin.matname=np.array(['heavysteel'])
Hbrcmatin.E=np.array([ 2.5e11])
Dbrc_hbrc=1.1
Hbrcinputs=HBrcGeoInputs()
Hbrcinputs.Dbrch=Dbrc_hbrc
Hbrcinputs.ndiv=0#2
Hbrcinputs.Hbrcmatins=Hbrcmatin
Hbrcinputs.precalc=True #This can be set to true if we want Hbrace to be set=Xbrace top D and t, in which case the above set Dbrch and tbrch would be overwritten
#TP data
TPlumpinputs=TPlumpMass()
TPlumpinputs.mass=200.e3 #[kg]
TPstmpsmatin=MatInputs()
TPbrcmatin=MatInputs()
TPstemmatin=MatInputs()
TPbrcmatin.matname=np.array(['heavysteel'])
#TPbrcmatin.E=np.array([ 2.5e11])
TPstemmatin.matname=np.array(['heavysteel']).repeat(2)
#TPstemmatin.E=np.array([ 2.1e11]).repeat(2)
TPinputs=TPGeoInputs()
TPinputs.TPbrcmatins=TPbrcmatin
TPinputs.TPstemmatins=TPstemmatin
TPinputs.TPstmpmatins=TPstmpsmatin
TPinputs.Dstrut=leginputs.Dleg[-1]
TPinputs.tstrut=leginputs.tleg[-1]
TPinputs.Dgir=Dbrc_hbrc
TPinputs.tgir=0.0254
TPinputs.Dbrc=1.1
TPinputs.Dbrc=TPinputs.Dgir
TPinputs.tbrc=TPinputs.tgir
TPinputs.hstump=1.0#1.0
TPinputs.Dstump=1.25#1.0
TPinputs.stumpndiv=1#2
TPinputs.brcndiv=1#2
TPinputs.girndiv=1#2
TPinputs.strutndiv=1#2
TPinputs.stemndiv=1#2
TPinputs.nstems=3
TPinputs.Dstem=np.array([6.]).repeat(TPinputs.nstems)
TPinputs.tstem=np.array([0.1,0.11,0.11])
TPinputs.hstem=np.array([6./TPinputs.nstems]).repeat(TPinputs.nstems)
#Tower data
Twrmatin=MatInputs()
Twrmatin.matname=np.array(['heavysteel'])
#Twrmatin.E=np.array([ 2.77e11])
Twrinputs=TwrGeoInputs()
Twrinputs.Twrmatins=Twrmatin
#Twrinputs.Htwr=70. #Trumped by HH
Twrinputs.Htwr2frac=0.2 #fraction of tower height with constant x-section
Twrinputs.ndiv=np.array([6,12]) #ndiv for uniform and tapered section
Twrinputs.DeltaZmax= 6. #[m], maximum FE element length allowed in the tower members (i.e. the uniform and the tapered members)
Twrinputs.Db=5.6
Twrinputs.DTRb=130.
Twrinputs.DTRt=150.
Twrinputs.Dt=0.55*Twrinputs.Db
## if turbine_jacket
##Twrinputs.Dt = 3.87
TwrRigidTop=True #False #False=Account for RNA via math rather than a physical rigidmember
#RNA data
RNAins=RNAprops()
RNAins.mass=3*350.e3
RNAins.I[0]=86.579E+6
RNAins.I[1]=53.530E+6
RNAins.I[2]=58.112E+6
RNAins.CMoff[2]=2.34
RNAins.yawangle=45. #angle with respect to global X, CCW looking from above, wind from left
RNAins.rna_weightM=True
## if turbine_jacket
##RNAins.mass=285598.806453
##RNAins.I = np.array([1.14930678e8, 2.20354030e7, 1.87597425e7, 0.0, 5.03710467e5, 0.0])
##RNAins.CMoff = np.array([-1.13197635, 0.0, 0.50875268])
##RNAins.yawangle=0.0 #angle with respect to global X, CCW looking from above, wind from left
#RNAins.rna_weightM=True
RNAins2=copy.copy(RNAins) #PARKED CASE, for now assume the same
#RNA loads Fx-z, Mxx-zz
RNA_F=np.array([1000.e3,0.,0.,0.,0.,0.]) #operational
RNA_F2=np.array([500.e3,0.,0.,0.,0.,0.]) #Parked
## if turbine_jacket
##RNA_F=np.array([1284744.19620519,0.,-2914124.84400512,3963732.76208099,-2275104.79420872,-346781.68192839])
#Frame3DD parameters
FrameAuxIns=Frame3DDaux()
FrameAuxIns.sh_fg=1 #shear flag-->Timoshenko
FrameAuxIns.deltaz=5.
FrameAuxIns.geo_fg=0
FrameAuxIns.nModes = 6 # number of desired dynamic modes of vibration
FrameAuxIns.Mmethod = 1 # 1: subspace Jacobi 2: Stodola
FrameAuxIns.lump = 0 # 0: consistent mass ... 1: lumped mass matrix
FrameAuxIns.tol = 1e-9 # mode shape tolerance
FrameAuxIns.shift = 0.0 # shift value ... for unrestrained structures
FrameAuxIns.gvector=np.array([0.,0.,-9.8065]) #GRAVITY
## if turbine_jacket
##FrameAuxIns.gvector=np.array([0.,0.,-9.81]) #GRAVITY
#Decide whether or not to consider DLC 6.1 as well
twodlcs=False
#-----Launch the assembly-----#
#turbine.jacket=JacketSE(Jcktins.clamped,Jcktins.AFflag,twodlcs=twodlcs)
#turbine.jacket=set_as_top(JacketSE(Jcktins.clamped,Jcktins.AFflag,twodlcs=twodlcs)) ##(Jcktins.PreBuildTPLvl>0),
#Pass all inputs to assembly
lcoe_se.jacket.JcktGeoIn=Jcktins
lcoe_se.jacket.Soilinputs=Soilinputs
lcoe_se.jacket.Soilinputs2=Soilinputs2 #Parked conditions
lcoe_se.jacket.Waterinputs=Waterinputs
lcoe_se.jacket.Windinputs=Windinputs
lcoe_se.jacket.RNA_F=RNA_F
lcoe_se.jacket.Waterinputs2=Waterinputs2 #Parked conditions
lcoe_se.jacket.Windinputs2=Windinputs2 #Parked conditions
lcoe_se.jacket.RNA_F2=RNA_F2 #Parked conditions
lcoe_se.jacket.Pileinputs=Pileinputs
lcoe_se.jacket.leginputs=leginputs
#lcoe_se.jacket.legbot_stmphin =legbot_stmphin
lcoe_se.jacket.Xbrcinputs=Xbrcinputs
lcoe_se.jacket.Mbrcinputs=Mbrcinputs
lcoe_se.jacket.Hbrcinputs=Hbrcinputs
lcoe_se.jacket.TPlumpinputs=TPlumpinputs
lcoe_se.jacket.TPinputs=TPinputs
lcoe_se.jacket.RNAinputs=RNAins
lcoe_se.jacket.RNAinputs2=RNAins2
lcoe_se.jacket.Twrinputs=Twrinputs
lcoe_se.jacket.TwrRigidTop=TwrRigidTop
lcoe_se.jacket.FrameAuxIns=FrameAuxIns
# === Run default assembly and print results
lcoe_se.run()
# ====
# === Print ===
print "Key Turbine Outputs for NREL 5 MW Reference Turbine"
print 'mass rotor blades:{0:.2f} (kg) '.format(lcoe_se.rotor.mass_all_blades)
print 'mass hub system: {0:.2f} (kg) '.format(lcoe_se.hub.hub_system_mass)
print 'mass nacelle: {0:.2f} (kg) '.format(lcoe_se.nacelle.nacelle_mass)
print 'mass tower: {0:.2f} (kg) '.format(lcoe_se.jacket.Tower.Twrouts.mass)
print 'maximum tip deflection: {0:.2f} (m) '.format(lcoe_se.maxdeflection.max_tip_deflection)
print 'ground clearance: {0:.2f} (m) '.format(lcoe_se.maxdeflection.ground_clearance)
print
print "Key Plant Outputs for wind plant with NREL 5 MW Turbine"
#print "LCOE: ${0:.4f} USD/kWh".format(lcoe_se.lcoe) # not in base output set (add to assembly output if desired)
print "COE: ${0:.4f} USD/kWh".format(lcoe_se.coe)
print
print "AEP per turbine: {0:.1f} kWh/turbine".format(lcoe_se.net_aep / lcoe_se.turbine_number)
print "Turbine Cost: ${0:.2f} USD".format(lcoe_se.turbine_cost)
print "BOS costs per turbine: ${0:.2f} USD/turbine".format(lcoe_se.bos_costs / lcoe_se.turbine_number)
print "OPEX per turbine: ${0:.2f} USD/turbine".format(lcoe_se.avg_annual_opex / lcoe_se.turbine_number)
def configure_nrel5mw_turbine(turbine, wind_class="I", sea_depth=0.0):
"""
Inputs:
rotor = RotorSE()
nacelle = DriveSE()
tower = TowerSE()
wind_class : str ('I', 'III', 'Offshore' - selected wind class for project)
sea_depth : float (sea depth if an offshore wind plant)
"""
# === Turbine ===
turbine.rho = 1.225 # (Float, kg/m**3): density of air
turbine.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air
turbine.shear_exponent = 0.2 # (Float): shear exponent
turbine.hub_height = 90.0 # (Float, m): hub height
turbine.turbine_class = "I" # (Enum): IEC turbine class
turbine.turbulence_class = "B" # (Enum): IEC turbulence class class
turbine.cdf_reference_height_wind_speed = (
90.0
) # (Float): reference hub height for IEC wind speed (used in CDF calculation)
turbine.g = 9.81 # (Float, m/s**2): acceleration of gravity
# ======================
# === rotor ===
# --- blade grid ---
turbine.rotor.initial_aero_grid = np.array(
[
0.02222276,
0.06666667,
0.11111057,
0.16666667,
0.23333333,
0.3,
0.36666667,
0.43333333,
0.5,
0.56666667,
0.63333333,
0.7,
0.76666667,
0.83333333,
0.88888943,
0.93333333,
0.97777724,
]
) # (Array): initial aerodynamic grid on unit radius
turbine.rotor.initial_str_grid = np.array(
[
0.0,
0.00492790457512,
0.00652942887106,
0.00813095316699,
0.00983257273154,
0.0114340970275,
0.0130356213234,
0.02222276,
0.024446481932,
0.026048006228,
0.06666667,
0.089508406455,
0.11111057,
0.146462614229,
0.16666667,
0.195309105255,
0.23333333,
0.276686558545,
0.3,
0.333640766319,
0.36666667,
0.400404310407,
0.43333333,
0.5,
0.520818918408,
0.56666667,
0.602196371696,
0.63333333,
0.667358391486,
0.683573824984,
0.7,
0.73242031601,
0.76666667,
0.83333333,
0.88888943,
0.93333333,
0.97777724,
1.0,
]
) # (Array): initial structural grid on unit radius
turbine.rotor.idx_cylinder_aero = (
3
) # (Int): first idx in r_aero_unit of non-cylindrical section, constant twist inboard of here
turbine.rotor.idx_cylinder_str = 14 # (Int): first idx in r_str_unit of non-cylindrical section
turbine.rotor.hubFraction = 0.025 # (Float): hub location as fraction of radius
# ------------------
# --- blade geometry ---
turbine.rotor.r_aero = np.array(
[
0.02222276,
0.06666667,
0.11111057,
0.2,
0.23333333,
0.3,
0.36666667,
0.43333333,
0.5,
0.56666667,
0.63333333,
0.64,
0.7,
0.83333333,
0.88888943,
0.93333333,
0.97777724,
]
) # (Array): new aerodynamic grid on unit radius
turbine.rotor.r_max_chord = 0.23577 # (Float): location of max chord on unit radius
turbine.rotor.chord_sub = [
3.2612,
4.5709,
3.3178,
1.4621,
] # (Array, m): chord at control points. defined at hub, then at linearly spaced locations from r_max_chord to tip
turbine.rotor.theta_sub = [
13.2783,
7.46036,
2.89317,
-0.0878099,
] # (Array, deg): twist at control points. defined at linearly spaced locations from r[idx_cylinder] to tip
turbine.rotor.precurve_sub = [
0.0,
0.0,
0.0,
] # (Array, m): precurve at control points. defined at same locations at chord, starting at 2nd control point (root must be zero precurve)
turbine.rotor.delta_precurve_sub = [
0.0,
0.0,
0.0,
] # (Array, m): adjustment to precurve to account for curvature from loading
turbine.rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398] # (Array, m): spar cap thickness parameters
turbine.rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569] # (Array, m): trailing-edge thickness parameters
turbine.rotor.bladeLength = (
61.5
) # (Float, m): blade length (if not precurved or swept) otherwise length of blade before curvature
turbine.rotor.delta_bladeLength = (
0.0
) # (Float, m): adjustment to blade length to account for curvature from loading
turbine.rotor.precone = 2.5 # (Float, deg): precone angle
turbine.rotor.tilt = 5.0 # (Float, deg): shaft tilt
turbine.rotor.yaw = 0.0 # (Float, deg): yaw error
turbine.rotor.nBlades = 3 # (Int): number of blades
# ------------------
# --- airfoil files ---
import rotorse
# basepath = os.path.join('5MW_files', '5MW_AFFiles')
basepath = os.path.join("..", "reference_turbines", "nrel5mw", "airfoils")
# 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]]
turbine.rotor.airfoil_files = af # (List): names of airfoil file
# ----------------------
# --- control ---
turbine.rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed
turbine.rotor.control.Vout = 25.0 # (Float, m/s): cut-out wind speed
turbine.rotor.control.ratedPower = 5e6 # (Float, W): rated power
turbine.rotor.control.minOmega = 0.0 # (Float, rpm): minimum allowed rotor rotation speed
turbine.rotor.control.maxOmega = 12.0 # (Float, rpm): maximum allowed rotor rotation speed
turbine.rotor.control.tsr = 7.55 # (Float): tip-speed ratio in Region 2 (should be optimized externally)
turbine.rotor.control.pitch = 0.0 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines)
turbine.rotor.pitch_extreme = 0.0 # (Float, deg): worst-case pitch at survival wind condition
turbine.rotor.azimuth_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition
turbine.rotor.VfactorPC = (
0.7
) # (Float): fraction of rated speed at which the deflection is assumed to representative throughout the power curve calculation
# ----------------------
# --- aero and structural analysis options ---
turbine.rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power
turbine.rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at
turbine.rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve
turbine.rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.)
turbine.rotor.drivetrainType = "geared" # (Enum)
turbine.rotor.nF = 5 # (Int): number of natural frequencies to compute
turbine.rotor.dynamic_amplication_tip_deflection = (
1.35
) # (Float): a dynamic amplification factor to adjust the static deflection calculation
# ----------------------
# --- materials and composite layup ---
# basepath = os.path.join('5MW_files', '5MW_PrecompFiles')
basepath = os.path.join("..", "reference_turbines", "nrel5mw", "blade")
materials = Orthotropic2DMaterial.listFromPreCompFile(os.path.join(basepath, "materials.inp"))
ncomp = len(turbine.rotor.initial_str_grid)
upper = [0] * ncomp
lower = [0] * ncomp
webs = [0] * ncomp
profile = [0] * ncomp
turbine.rotor.leLoc = np.array(
[
0.5,
0.5,
0.5,
0.5,
0.5,
0.5,
0.5,
0.5,
0.498,
0.497,
0.465,
0.447,
0.43,
0.411,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
0.4,
]
) # (Array): array of leading-edge positions from a reference blade axis (usually blade pitch axis). locations are normalized by the local chord length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference axis. positive in -x direction for airfoil-aligned coordinate system
turbine.rotor.sector_idx_strain_spar = [
2
] * ncomp # (Array): index of sector for spar (PreComp definition of sector)
turbine.rotor.sector_idx_strain_te = [
3
] * ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector)
web1 = np.array(
[
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
0.4114,
0.4102,
0.4094,
0.3876,
0.3755,
0.3639,
0.345,
0.3342,
0.3313,
0.3274,
0.323,
0.3206,
0.3172,
0.3138,
0.3104,
0.307,
0.3003,
0.2982,
0.2935,
0.2899,
0.2867,
0.2833,
0.2817,
0.2799,
0.2767,
0.2731,
0.2664,
0.2607,
0.2562,
0.1886,
-1.0,
]
)
web2 = np.array(
[
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
0.5886,
0.5868,
0.5854,
0.5508,
0.5315,
0.5131,
0.4831,
0.4658,
0.4687,
0.4726,
0.477,
0.4794,
0.4828,
0.4862,
0.4896,
0.493,
0.4997,
0.5018,
0.5065,
0.5101,
0.5133,
0.5167,
0.5183,
0.5201,
0.5233,
0.5269,
0.5336,
0.5393,
0.5438,
0.6114,
-1.0,
]
)
web3 = np.array(
[
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
-1.0,
]
)
turbine.rotor.chord_str_ref = np.array(
[
3.2612,
3.3100915356,
3.32587052924,
3.34159388653,
3.35823798667,
3.37384375335,
3.38939112914,
3.4774055542,
3.49839685,
3.51343645709,
3.87017220335,
4.04645623801,
4.19408216643,
4.47641008477,
4.55844487985,
4.57383098262,
4.57285771934,
4.51914315648,
4.47677655262,
4.40075650022,
4.31069949379,
4.20483735936,
4.08985563932,
3.82931757126,
3.74220276467,
3.54415796922,
3.38732428502,
3.24931446473,
3.23421422609,
3.22701537997,
3.21972125648,
3.08979310611,
2.95152261813,
2.330753331,
2.05553464181,
1.82577817774,
1.5860853279,
1.4621,
]
) # (Array, m): chord distribution for reference section, thickness of structural layup scaled with reference thickness (fixed t/c for this case)
for i in range(ncomp):
webLoc = []
if web1[i] != -1:
webLoc.append(web1[i])
if web2[i] != -1:
webLoc.append(web2[i])
if web3[i] != -1:
webLoc.append(web3[i])
upper[i], lower[i], webs[i] = CompositeSection.initFromPreCompLayupFile(
os.path.join(basepath, "layup_" + str(i + 1) + ".inp"), webLoc, materials
)
profile[i] = Profile.initFromPreCompFile(os.path.join(basepath, "shape_" + str(i + 1) + ".inp"))
turbine.rotor.materials = (
materials
) # (List): list of all Orthotropic2DMaterial objects used in defining the geometry
turbine.rotor.upperCS = (
upper
) # (List): list of CompositeSection objections defining the properties for upper surface
turbine.rotor.lowerCS = (
lower
) # (List): list of CompositeSection objections defining the properties for lower surface
turbine.rotor.websCS = webs # (List): list of CompositeSection objections defining the properties for shear webs
turbine.rotor.profile = profile # (List): airfoil shape at each radial position
# --------------------------------------
strain_ult_spar = 1.0e-2
strain_ult_te = 2500 * 1e-6
# --- fatigue ---
turbine.rotor.rstar_damage = np.array(
[
0.000,
0.022,
0.067,
0.111,
0.167,
0.233,
0.300,
0.367,
0.433,
0.500,
0.567,
0.633,
0.700,
0.767,
0.833,
0.889,
0.933,
0.978,
]
) # (Array): nondimensional radial locations of damage equivalent moments
turbine.rotor.Mxb_damage = 1e3 * np.array(
[
2.3743e003,
2.0834e003,
1.8108e003,
1.5705e003,
1.3104e003,
1.0488e003,
8.2367e002,
6.3407e002,
4.7727e002,
3.4804e002,
2.4458e002,
1.6339e002,
1.0252e002,
5.7842e001,
2.7349e001,
1.1262e001,
3.8549e000,
4.4738e-001,
]
) # (Array, N*m): damage equivalent moments about blade c.s. x-direction
turbine.rotor.Myb_damage = 1e3 * np.array(
[
2.7732e003,
2.8155e003,
2.6004e003,
2.3933e003,
2.1371e003,
1.8459e003,
1.5582e003,
1.2896e003,
1.0427e003,
8.2015e002,
6.2449e002,
4.5229e002,
3.0658e002,
1.8746e002,
9.6475e001,
4.2677e001,
1.5409e001,
1.8426e000,
]
) # (Array, N*m): damage equivalent moments about blade c.s. y-direction
turbine.rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap
turbine.rotor.strain_ult_te = (
2500 * 1e-6 * 2
) # (Float): uptimate strain in trailing-edge panels, note that I am putting a factor of two for the damage part only.
turbine.rotor.eta_damage = 1.35 * 1.3 * 1.0 # (Float): safety factor for fatigue
turbine.rotor.m_damage = 10.0 # (Float): slope of S-N curve for fatigue analysis
turbine.rotor.N_damage = (
365 * 24 * 3600 * 20.0
) # (Float): number of cycles used in fatigue analysis TODO: make function of rotation speed
# ----------------
# =================
# === nacelle ======
turbine.nacelle.L_ms = 1.0 # (Float, m): main shaft length downwind of main bearing in low-speed shaft
turbine.nacelle.L_mb = 2.5 # (Float, m): main shaft length in low-speed shaft
turbine.nacelle.h0_front = 1.7 # (Float, m): height of Ibeam in bedplate front
turbine.nacelle.h0_rear = 1.35 # (Float, m): height of Ibeam in bedplate rear
turbine.nacelle.drivetrain_design = "geared"
turbine.nacelle.crane = True # (Bool): flag for presence of crane
turbine.nacelle.bevel = 0 # (Int): Flag for the presence of a bevel stage - 1 if present, 0 if not
turbine.nacelle.gear_configuration = (
"eep"
) # (Str): tring that represents the configuration of the gearbox (stage number and types)
turbine.nacelle.Np = [3, 3, 1] # (Array): number of planets in each stage
turbine.nacelle.ratio_type = "optimal" # (Str): optimal or empirical stage ratios
turbine.nacelle.shaft_type = "normal" # (Str): normal or short shaft length
# turbine.nacelle.shaft_angle = 5.0 # (Float, deg): Angle of the LSS inclindation with respect to the horizontal
turbine.nacelle.shaft_ratio = 0.10 # (Float): Ratio of inner diameter to outer diameter. Leave zero for solid LSS
turbine.nacelle.carrier_mass = 8000.0 # estimated for 5 MW
turbine.nacelle.mb1Type = "CARB" # (Str): Main bearing type: CARB, TRB or SRB
turbine.nacelle.mb2Type = "SRB" # (Str): Second bearing type: CARB, TRB or SRB
turbine.nacelle.yaw_motors_number = 8.0 # (Float): number of yaw motors
turbine.nacelle.uptower_transformer = True
turbine.nacelle.flange_length = 0.5 # m
turbine.nacelle.gearbox_cm = 0.1
turbine.nacelle.hss_length = 1.5
turbine.nacelle.overhang = 5.0 # TODO - should come from turbine configuration level
turbine.nacelle.check_fatigue = (
0
) # 0 if no fatigue check, 1 if parameterized fatigue check, 2 if known loads inputs
# TODO: should come from rotor (these are FAST outputs)
turbine.nacelle.DrivetrainEfficiency = 0.95
# turbine.nacelle.rotor_bending_moment_x = 330770.0# Nm
# turbine.nacelle.rotor_bending_moment_y = -16665000.0 # Nm
# turbine.nacelle.rotor_bending_moment_z = 2896300.0 # Nm
# turbine.nacelle.rotor_force_x = 599610.0 # N
# turbine.nacelle.rotor_force_y = 186780.0 # N
# turbine.nacelle.rotor_force_z = -842710.0 # N'''
# turbine.nacelle.h0_rear = 1.35 # only used in drive smooth
# turbine.nacelle.h0_front = 1.7
# =================
# === tower ===
# ---- tower ------
turbine.tower.replace("wind1", PowerWind())
turbine.tower.replace("wind2", PowerWind())
# onshore (no waves)
if turbine.sea_depth <> 0.0:
turbine.tower.replace("wave1", LinearWaves())
turbine.tower.replace("wave2", LinearWaves())
turbine.tower.wave1.Uc = 0.0
turbine.tower.wave1.hs = 8.0 * 1.86
turbine.tower.wave1.T = 10.0
turbine.tower.wave1.z_surface = 0.0
turbine.tower.wave1.z_floor = -sea_depth
turbine.tower.wave1.g = 9.81
turbine.tower.wave1.betaWave = 0.0
turbine.tower.wave2.Uc = 0.0
turbine.tower.wave2.hs = 8.0 * 1.86
turbine.tower.wave2.T = 10.0
turbine.tower.wave2.z_surface = 0.0
turbine.tower.wave2.z_floor = -sea_depth
turbine.tower.wave2.g = 9.81
turbine.tower.wave2.betaWave = 0.0
if turbine.sea_depth == 0.0:
# --- geometry ----
# np.insert(turbine.tower.z_param,0,87.9)
# np.insert(turbine.tower.z_param,0,43.8)
# np.insert(turbine.tower.z_param,0,0.0)
turbine.tower.z_param = [0.0, 43.8, 87.9]
turbine.tower_d = [6.0, 4.935, 3.87]
turbine.tower.t_param = [0.027 * 1.3, 0.023 * 1.3, 0.019 * 1.3]
n = 15
turbine.tower.z_full = np.linspace(0.0, 87.6, n)
turbine.tower.L_reinforced = 30.0 * np.ones(n) # [m] buckling length
turbine.tower.theta_stress = 0.0 * np.ones(n)
turbine.tower.yaw = 0.0
# --- material props ---
turbine.tower.E = 210e9 * np.ones(n)
turbine.tower.G = 80.8e9 * np.ones(n)
turbine.tower.rho = 8500.0 * np.ones(n)
turbine.tower.sigma_y = 450.0e6 * np.ones(n)
else:
# --- geometry ----
# np.insert(turbine.tower.z_param,0,87.9)
# np.insert(turbine.tower.z_param,0,43.8)
# np.insert(turbine.tower.z_param,0,0.0)
# np.insert(turbine.tower.z_param,0,-20.0)
turbine.tower.z_param = [-20.0, 0.0, 43.8, 87.9]
turbine.tower_d = [6.0, 6.0, 4.935, 3.87]
turbine.tower.t_param = [0.06, 0.027 * 1.3, 0.023 * 1.3, 0.019 * 1.3]
n = 20
turbine.tower.z_full = np.linspace(-20, 87.6, n)
turbine.tower.L_reinforced = 30.0 * np.ones(n) # [m] buckling length
turbine.tower.theta_stress = 0.0 * np.ones(n)
turbine.tower.yaw = 0.0
# --- material props ---
turbine.tower.E = 210e9 * np.ones(n)
turbine.tower.G = 80.8e9 * np.ones(n)
turbine.tower.rho = 8500.0 * np.ones(n)
turbine.tower.sigma_y = 450.0e6 * np.ones(n)
# --- spring reaction data. Use float('inf') for rigid constraints. ---
turbine.tower.kidx = [0] # applied at base
turbine.tower.kx = [float("inf")]
turbine.tower.ky = [float("inf")]
turbine.tower.kz = [float("inf")]
turbine.tower.ktx = [float("inf")]
turbine.tower.kty = [float("inf")]
turbine.tower.ktz = [float("inf")]
# --- extra mass ----
turbine.tower.midx = [n - 1] # RNA mass at top
turbine.tower.m = [285598.8]
turbine.tower.mIxx = [1.14930678e08]
turbine.tower.mIyy = [2.20354030e07]
turbine.tower.mIzz = [1.87597425e07]
turbine.tower.mIxy = [0.00000000e00]
turbine.tower.mIxz = [5.03710467e05]
turbine.tower.mIyz = [0.00000000e00]
turbine.tower.mrhox = [-1.13197635]
turbine.tower.mrhoy = [0.0]
turbine.tower.mrhoz = [0.50875268]
turbine.tower.addGravityLoadForExtraMass = True
# -----------
# --- wind ---
# turbine.tower.wind_zref = 90.0
turbine.tower.wind_z0 = 0.0
turbine.tower.wind1.shearExp = 0.2
turbine.tower.wind2.shearExp = 0.2
# ---------------
# if addGravityLoadForExtraMass=True be sure not to double count by adding those force here also
# # --- loading case 1: max Thrust ---
# turbine.tower.wind_Uref1 = 11.73732
turbine.tower.plidx1 = [n - 1] # at tower top
turbine.tower.Fx1 = [1284744.19620519]
turbine.tower.Fy1 = [0.0]
turbine.tower.Fz1 = [-2914124.84400512]
turbine.tower.Mxx1 = [3963732.76208099]
turbine.tower.Myy1 = [-2275104.79420872]
turbine.tower.Mzz1 = [-346781.68192839]
# # ---------------
# # --- loading case 2: max wind speed ---
# turbine.tower.wind_Uref2 = 70.0
turbine.tower.plidx2 = [n - 1] # at tower top
turbine.tower.Fx2 = [930198.60063279]
turbine.tower.Fy2 = [0.0]
turbine.tower.Fz2 = [-2883106.12368949]
turbine.tower.Mxx2 = [-1683669.22411597]
turbine.tower.Myy2 = [-2522475.34625363]
turbine.tower.Mzz2 = [147301.97023764]
# # ---------------
# --- safety factors ---
turbine.tower.gamma_f = 1.35
turbine.tower.gamma_m = 1.3
turbine.tower.gamma_n = 1.0
turbine.tower.gamma_b = 1.1
# ---------------
# --- fatigue ---
turbine.tower.z_DEL = np.array(
[
0.000,
1.327,
3.982,
6.636,
9.291,
11.945,
14.600,
17.255,
19.909,
22.564,
25.218,
27.873,
30.527,
33.182,
35.836,
38.491,
41.145,
43.800,
46.455,
49.109,
51.764,
54.418,
57.073,
59.727,
62.382,
65.036,
67.691,
70.345,
73.000,
75.655,
78.309,
80.964,
83.618,
86.273,
87.600,
]
)
turbine.tower.M_DEL = 1e3 * np.array(
[
8.2940e003,
8.1518e003,
7.8831e003,
7.6099e003,
7.3359e003,
7.0577e003,
6.7821e003,
6.5119e003,
6.2391e003,
5.9707e003,
5.7070e003,
5.4500e003,
5.2015e003,
4.9588e003,
4.7202e003,
4.4884e003,
4.2577e003,
4.0246e003,
3.7942e003,
3.5664e003,
3.3406e003,
3.1184e003,
2.8977e003,
2.6811e003,
2.4719e003,
2.2663e003,
2.0673e003,
1.8769e003,
1.7017e003,
1.5479e003,
1.4207e003,
1.3304e003,
1.2780e003,
1.2673e003,
1.2761e003,
]
)
turbine.tower.gamma_fatigue = 1.35 * 1.3 * 1.0
turbine.tower.life = 20.0
turbine.tower.m_SN = 4
# ---------------
# --- constraints ---
turbine.tower.min_d_to_t = 120.0
turbine.tower.min_taper = 0.4
# ---------------
# ==== Other options
if wind_class == "I":
turbine.rotor.turbine_class = "I"
elif wind_class == "III":
turbine.rotor.turbine_class = "III"
# for fatigue based analysis of class III wind turbine
turbine.tower.M_DEL = (
1.028713178
* 1e3
* np.array(
[
7.8792e003,
7.7507e003,
7.4918e003,
7.2389e003,
6.9815e003,
6.7262e003,
6.4730e003,
6.2174e003,
5.9615e003,
5.7073e003,
5.4591e003,
5.2141e003,
4.9741e003,
4.7399e003,
4.5117e003,
4.2840e003,
4.0606e003,
3.8360e003,
3.6118e003,
3.3911e003,
3.1723e003,
2.9568e003,
2.7391e003,
2.5294e003,
2.3229e003,
2.1246e003,
1.9321e003,
1.7475e003,
1.5790e003,
1.4286e003,
1.3101e003,
1.2257e003,
1.1787e003,
1.1727e003,
1.1821e003,
]
)
)
turbine.rotor.Mxb_damage = 1e3 * np.array(
[
2.3617e003,
2.0751e003,
1.8051e003,
1.5631e003,
1.2994e003,
1.0388e003,
8.1384e002,
6.2492e002,
4.6916e002,
3.4078e002,
2.3916e002,
1.5916e002,
9.9752e001,
5.6139e001,
2.6492e001,
1.0886e001,
3.7210e000,
4.3206e-001,
]
)
turbine.rotor.Myb_damage = 1e3 * np.array(
[
2.5492e003,
2.6261e003,
2.4265e003,
2.2308e003,
1.9882e003,
1.7184e003,
1.4438e003,
1.1925e003,
9.6251e002,
7.5564e002,
5.7332e002,
4.1435e002,
2.8036e002,
1.7106e002,
8.7732e001,
3.8678e001,
1.3942e001,
1.6600e000,
]
)
elif wind_class == "Offshore":
turbine.rotor.turbine_class = "I"
# TODO: these should be specified at the turbine level and connected to other system inputs
if turbine.sea_depth == 0.0:
turbine.tower_d = [6.0, 4.935, 3.87] # (Array, m): diameters along tower
else:
turbine.tower_d = [6.0, 6.0, 4.935, 3.87]
turbine.generator_speed = 1173.7 # (Float, rpm) # generator speed
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_nrel5mw_turbine_with_jacket(turbine,wind_class='I',sea_depth = 0.0):
"""
Inputs:
rotor = RotorSE()
nacelle = DriveSE()
jacket = JacketSE()
wind_class : str ('I', 'III', 'Offshore' - selected wind class for project)
sea_depth : float (sea depth if an offshore wind plant)
"""
# =================
# === Turbine ===
turbine.rho = 1.225 # (Float, kg/m**3): density of air
turbine.mu = 1.81206e-5 # (Float, kg/m/s): dynamic viscosity of air
turbine.shear_exponent = 0.2 # (Float): shear exponent
turbine.hub_height = 90.0 # (Float, m): hub height
turbine.turbine_class = 'I' # (Enum): IEC turbine class
turbine.turbulence_class = 'B' # (Enum): IEC turbulence class class
turbine.cdf_reference_height_wind_speed = 90.0 # (Float): reference hub height for IEC wind speed (used in CDF calculation)
turbine.g = 9.81 # (Float, m/s**2): acceleration of gravity
# ======================
# === rotor ===
# --- blade grid ---
turbine.rotor.initial_aero_grid = np.array([0.02222276, 0.06666667, 0.11111057, 0.16666667, 0.23333333, 0.3, 0.36666667,
0.43333333, 0.5, 0.56666667, 0.63333333, 0.7, 0.76666667, 0.83333333, 0.88888943, 0.93333333,
0.97777724]) # (Array): initial aerodynamic grid on unit radius
turbine.rotor.initial_str_grid = np.array([0.0, 0.00492790457512, 0.00652942887106, 0.00813095316699, 0.00983257273154,
0.0114340970275, 0.0130356213234, 0.02222276, 0.024446481932, 0.026048006228, 0.06666667, 0.089508406455,
0.11111057, 0.146462614229, 0.16666667, 0.195309105255, 0.23333333, 0.276686558545, 0.3, 0.333640766319,
0.36666667, 0.400404310407, 0.43333333, 0.5, 0.520818918408, 0.56666667, 0.602196371696, 0.63333333,
0.667358391486, 0.683573824984, 0.7, 0.73242031601, 0.76666667, 0.83333333, 0.88888943, 0.93333333, 0.97777724,
1.0]) # (Array): initial structural grid on unit radius
turbine.rotor.idx_cylinder_aero = 3 # (Int): first idx in r_aero_unit of non-cylindrical section, constant twist inboard of here
turbine.rotor.idx_cylinder_str = 14 # (Int): first idx in r_str_unit of non-cylindrical section
turbine.rotor.hubFraction = 0.025 # (Float): hub location as fraction of radius
# ------------------
# --- blade geometry ---
turbine.rotor.r_aero = np.array([0.02222276, 0.06666667, 0.11111057, 0.2, 0.23333333, 0.3, 0.36666667, 0.43333333,
0.5, 0.56666667, 0.63333333, 0.64, 0.7, 0.83333333, 0.88888943, 0.93333333,
0.97777724]) # (Array): new aerodynamic grid on unit radius
turbine.rotor.r_max_chord = 0.23577 # (Float): location of max chord on unit radius
turbine.rotor.chord_sub = [3.2612, 4.5709, 3.3178, 1.4621] # (Array, m): chord at control points. defined at hub, then at linearly spaced locations from r_max_chord to tip
turbine.rotor.theta_sub = [13.2783, 7.46036, 2.89317, -0.0878099] # (Array, deg): twist at control points. defined at linearly spaced locations from r[idx_cylinder] to tip
turbine.rotor.precurve_sub = [0.0, 0.0, 0.0] # (Array, m): precurve at control points. defined at same locations at chord, starting at 2nd control point (root must be zero precurve)
turbine.rotor.delta_precurve_sub = [0.0, 0.0, 0.0] # (Array, m): adjustment to precurve to account for curvature from loading
turbine.rotor.sparT = [0.05, 0.047754, 0.045376, 0.031085, 0.0061398] # (Array, m): spar cap thickness parameters
turbine.rotor.teT = [0.1, 0.09569, 0.06569, 0.02569, 0.00569] # (Array, m): trailing-edge thickness parameters
turbine.rotor.bladeLength = 61.5 # (Float, m): blade length (if not precurved or swept) otherwise length of blade before curvature
turbine.rotor.delta_bladeLength = 0.0 # (Float, m): adjustment to blade length to account for curvature from loading
turbine.rotor.precone = 2.5 # (Float, deg): precone angle
turbine.rotor.tilt = 5.0 # (Float, deg): shaft tilt
turbine.rotor.yaw = 0.0 # (Float, deg): yaw error
turbine.rotor.nBlades = 3 # (Int): number of blades
# ------------------
# --- airfoil files ---
import rotorse
#basepath = os.path.join('5MW_files', '5MW_AFFiles')
basepath = os.path.join('..','reference_turbines','nrel5mw','airfoils')
# 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]]
turbine.rotor.airfoil_files = af # (List): names of airfoil file
# ----------------------
# --- control ---
turbine.rotor.control.Vin = 3.0 # (Float, m/s): cut-in wind speed
turbine.rotor.control.Vout = 25.0 # (Float, m/s): cut-out wind speed
turbine.rotor.control.ratedPower = 5e6 # (Float, W): rated power
turbine.rotor.control.minOmega = 0.0 # (Float, rpm): minimum allowed rotor rotation speed
turbine.rotor.control.maxOmega = 12.0 # (Float, rpm): maximum allowed rotor rotation speed
turbine.rotor.control.tsr = 7.55 # (Float): tip-speed ratio in Region 2 (should be optimized externally)
turbine.rotor.control.pitch = 0.0 # (Float, deg): pitch angle in region 2 (and region 3 for fixed pitch machines)
turbine.rotor.pitch_extreme = 0.0 # (Float, deg): worst-case pitch at survival wind condition
turbine.rotor.azimuth_extreme = 0.0 # (Float, deg): worst-case azimuth at survival wind condition
turbine.rotor.VfactorPC = 0.7 # (Float): fraction of rated speed at which the deflection is assumed to representative throughout the power curve calculation
# ----------------------
# --- aero and structural analysis options ---
turbine.rotor.nSector = 4 # (Int): number of sectors to divide rotor face into in computing thrust and power
turbine.rotor.npts_coarse_power_curve = 20 # (Int): number of points to evaluate aero analysis at
turbine.rotor.npts_spline_power_curve = 200 # (Int): number of points to use in fitting spline to power curve
turbine.rotor.AEP_loss_factor = 1.0 # (Float): availability and other losses (soiling, array, etc.)
turbine.rotor.drivetrainType = 'geared' # (Enum)
turbine.rotor.nF = 5 # (Int): number of natural frequencies to compute
turbine.rotor.dynamic_amplication_tip_deflection = 1.35 # (Float): a dynamic amplification factor to adjust the static deflection calculation
# ----------------------
# --- materials and composite layup ---
#basepath = os.path.join('5MW_files', '5MW_PrecompFiles')
basepath = os.path.join('..', 'reference_turbines','nrel5mw','blade')
materials = Orthotropic2DMaterial.listFromPreCompFile(os.path.join(basepath, 'materials.inp'))
ncomp = len(turbine.rotor.initial_str_grid)
upper = [0]*ncomp
lower = [0]*ncomp
webs = [0]*ncomp
profile = [0]*ncomp
turbine.rotor.leLoc = np.array([0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.498, 0.497, 0.465, 0.447, 0.43, 0.411,
0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4, 0.4,
0.4, 0.4, 0.4, 0.4]) # (Array): array of leading-edge positions from a reference blade axis (usually blade pitch axis). locations are normalized by the local chord length. e.g. leLoc[i] = 0.2 means leading edge is 0.2*chord[i] from reference axis. positive in -x direction for airfoil-aligned coordinate system
turbine.rotor.sector_idx_strain_spar = [2]*ncomp # (Array): index of sector for spar (PreComp definition of sector)
turbine.rotor.sector_idx_strain_te = [3]*ncomp # (Array): index of sector for trailing-edge (PreComp definition of sector)
web1 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.4114, 0.4102, 0.4094, 0.3876, 0.3755, 0.3639, 0.345, 0.3342, 0.3313, 0.3274, 0.323, 0.3206, 0.3172, 0.3138, 0.3104, 0.307, 0.3003, 0.2982, 0.2935, 0.2899, 0.2867, 0.2833, 0.2817, 0.2799, 0.2767, 0.2731, 0.2664, 0.2607, 0.2562, 0.1886, -1.0])
web2 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 0.5886, 0.5868, 0.5854, 0.5508, 0.5315, 0.5131, 0.4831, 0.4658, 0.4687, 0.4726, 0.477, 0.4794, 0.4828, 0.4862, 0.4896, 0.493, 0.4997, 0.5018, 0.5065, 0.5101, 0.5133, 0.5167, 0.5183, 0.5201, 0.5233, 0.5269, 0.5336, 0.5393, 0.5438, 0.6114, -1.0])
web3 = np.array([-1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0, -1.0])
turbine.rotor.chord_str_ref = np.array([3.2612, 3.3100915356, 3.32587052924, 3.34159388653, 3.35823798667, 3.37384375335,
3.38939112914, 3.4774055542, 3.49839685, 3.51343645709, 3.87017220335, 4.04645623801, 4.19408216643,
4.47641008477, 4.55844487985, 4.57383098262, 4.57285771934, 4.51914315648, 4.47677655262, 4.40075650022,
4.31069949379, 4.20483735936, 4.08985563932, 3.82931757126, 3.74220276467, 3.54415796922, 3.38732428502,
3.24931446473, 3.23421422609, 3.22701537997, 3.21972125648, 3.08979310611, 2.95152261813, 2.330753331,
2.05553464181, 1.82577817774, 1.5860853279, 1.4621]) # (Array, m): chord distribution for reference section, thickness of structural layup scaled with reference thickness (fixed t/c for this case)
for i in range(ncomp):
webLoc = []
if web1[i] != -1:
webLoc.append(web1[i])
if web2[i] != -1:
webLoc.append(web2[i])
if web3[i] != -1:
webLoc.append(web3[i])
upper[i], lower[i], webs[i] = CompositeSection.initFromPreCompLayupFile(os.path.join(basepath, 'layup_' + str(i+1) + '.inp'), webLoc, materials)
profile[i] = Profile.initFromPreCompFile(os.path.join(basepath, 'shape_' + str(i+1) + '.inp'))
turbine.rotor.materials = materials # (List): list of all Orthotropic2DMaterial objects used in defining the geometry
turbine.rotor.upperCS = upper # (List): list of CompositeSection objections defining the properties for upper surface
turbine.rotor.lowerCS = lower # (List): list of CompositeSection objections defining the properties for lower surface
turbine.rotor.websCS = webs # (List): list of CompositeSection objections defining the properties for shear webs
turbine.rotor.profile = profile # (List): airfoil shape at each radial position
# --------------------------------------
strain_ult_spar = 1.0e-2
strain_ult_te = 2500*1e-6
# --- fatigue ---
turbine.rotor.rstar_damage = np.array([0.000, 0.022, 0.067, 0.111, 0.167, 0.233, 0.300, 0.367, 0.433, 0.500,
0.567, 0.633, 0.700, 0.767, 0.833, 0.889, 0.933, 0.978]) # (Array): nondimensional radial locations of damage equivalent moments
turbine.rotor.Mxb_damage = 1e3*np.array([2.3743E+003, 2.0834E+003, 1.8108E+003, 1.5705E+003, 1.3104E+003,
1.0488E+003, 8.2367E+002, 6.3407E+002, 4.7727E+002, 3.4804E+002, 2.4458E+002, 1.6339E+002,
1.0252E+002, 5.7842E+001, 2.7349E+001, 1.1262E+001, 3.8549E+000, 4.4738E-001]) # (Array, N*m): damage equivalent moments about blade c.s. x-direction
turbine.rotor.Myb_damage = 1e3*np.array([2.7732E+003, 2.8155E+003, 2.6004E+003, 2.3933E+003, 2.1371E+003,
1.8459E+003, 1.5582E+003, 1.2896E+003, 1.0427E+003, 8.2015E+002, 6.2449E+002, 4.5229E+002,
3.0658E+002, 1.8746E+002, 9.6475E+001, 4.2677E+001, 1.5409E+001, 1.8426E+000]) # (Array, N*m): damage equivalent moments about blade c.s. y-direction
turbine.rotor.strain_ult_spar = 1.0e-2 # (Float): ultimate strain in spar cap
turbine.rotor.strain_ult_te = 2500*1e-6 * 2 # (Float): uptimate strain in trailing-edge panels, note that I am putting a factor of two for the damage part only.
turbine.rotor.eta_damage = 1.35*1.3*1.0 # (Float): safety factor for fatigue
turbine.rotor.m_damage = 10.0 # (Float): slope of S-N curve for fatigue analysis
turbine.rotor.N_damage = 365*24*3600*20.0 # (Float): number of cycles used in fatigue analysis TODO: make function of rotation speed
# ----------------
# =================
# === nacelle ======
turbine.nacelle.L_ms = 1.0 # (Float, m): main shaft length downwind of main bearing in low-speed shaft
turbine.nacelle.L_mb = 2.5 # (Float, m): main shaft length in low-speed shaft
turbine.nacelle.h0_front = 1.7 # (Float, m): height of Ibeam in bedplate front
turbine.nacelle.h0_rear = 1.35 # (Float, m): height of Ibeam in bedplate rear
turbine.nacelle.drivetrain_design = 'geared'
turbine.nacelle.crane = True # (Bool): flag for presence of crane
turbine.nacelle.bevel = 0 # (Int): Flag for the presence of a bevel stage - 1 if present, 0 if not
turbine.nacelle.gear_configuration = 'eep' # (Str): tring that represents the configuration of the gearbox (stage number and types)
turbine.nacelle.Np = [3, 3, 1] # (Array): number of planets in each stage
turbine.nacelle.ratio_type = 'optimal' # (Str): optimal or empirical stage ratios
turbine.nacelle.shaft_type = 'normal' # (Str): normal or short shaft length
#turbine.nacelle.shaft_angle = 5.0 # (Float, deg): Angle of the LSS inclindation with respect to the horizontal
turbine.nacelle.shaft_ratio = 0.10 # (Float): Ratio of inner diameter to outer diameter. Leave zero for solid LSS
turbine.nacelle.carrier_mass = 8000.0 # estimated for 5 MW
turbine.nacelle.mb1Type = 'CARB' # (Str): Main bearing type: CARB, TRB or SRB
turbine.nacelle.mb2Type = 'SRB' # (Str): Second bearing type: CARB, TRB or SRB
turbine.nacelle.yaw_motors_number = 8.0 # (Float): number of yaw motors
turbine.nacelle.uptower_transformer = True
turbine.nacelle.flange_length = 0.5 #m
turbine.nacelle.gearbox_cm = 0.1
turbine.nacelle.hss_length = 1.5
turbine.nacelle.overhang = 5.0 #TODO - should come from turbine configuration level
turbine.nacelle.check_fatigue = 0 #0 if no fatigue check, 1 if parameterized fatigue check, 2 if known loads inputs
# TODO: should come from rotor (these are FAST outputs)
turbine.nacelle.DrivetrainEfficiency = 0.95
turbine.nacelle.rotor_bending_moment_x = 330770.0# Nm
turbine.nacelle.rotor_bending_moment_y = -16665000.0 # Nm
turbine.nacelle.rotor_bending_moment_z = 2896300.0 # Nm
turbine.nacelle.rotor_force_x = 599610.0 # N
turbine.nacelle.rotor_force_y = 186780.0 # N
turbine.nacelle.rotor_force_z = -842710.0 # N
#turbine.nacelle.h0_rear = 1.35 # only used in drive smooth
#turbine.nacelle.h0_front = 1.7
# =================
if wind_class == 'I':
turbine.rotor.turbine_class = 'I'
elif wind_class == 'III':
turbine.rotor.turbine_class = 'III'
# for fatigue based analysis of class III wind turbine
turbine.tower.M_DEL = 1.028713178 * 1e3*np.array([7.8792E+003, 7.7507E+003, 7.4918E+003, 7.2389E+003, 6.9815E+003, 6.7262E+003, 6.4730E+003, 6.2174E+003, 5.9615E+003, 5.7073E+003, 5.4591E+003, 5.2141E+003, 4.9741E+003, 4.7399E+003, 4.5117E+003, 4.2840E+003, 4.0606E+003, 3.8360E+003, 3.6118E+003, 3.3911E+003, 3.1723E+003, 2.9568E+003, 2.7391E+003, 2.5294E+003, 2.3229E+003, 2.1246E+003, 1.9321E+003, 1.7475E+003, 1.5790E+003, 1.4286E+003, 1.3101E+003, 1.2257E+003, 1.1787E+003, 1.1727E+003, 1.1821E+003])
turbine.rotor.Mxb_damage = 1e3*np.array([2.3617E+003, 2.0751E+003, 1.8051E+003, 1.5631E+003, 1.2994E+003, 1.0388E+003, 8.1384E+002, 6.2492E+002, 4.6916E+002, 3.4078E+002, 2.3916E+002, 1.5916E+002, 9.9752E+001, 5.6139E+001, 2.6492E+001, 1.0886E+001, 3.7210E+000, 4.3206E-001])
turbine.rotor.Myb_damage = 1e3*np.array([2.5492E+003, 2.6261E+003, 2.4265E+003, 2.2308E+003, 1.9882E+003, 1.7184E+003, 1.4438E+003, 1.1925E+003, 9.6251E+002, 7.5564E+002, 5.7332E+002, 4.1435E+002, 2.8036E+002, 1.7106E+002, 8.7732E+001, 3.8678E+001, 1.3942E+001, 1.6600E+000])
elif wind_class == 'Offshore':
turbine.rotor.turbine_class = 'I'
# =================
# === jacket ===
#--- Set Jacket Input Parameters ---#
Jcktins=JcktGeoInputs()
Jcktins.nlegs =4
Jcktins.nbays =5
Jcktins.batter=12.
Jcktins.dck_botz =16.
Jcktins.weld2D =0.5
Jcktins.VPFlag = True #vertical pile T/F; to enable piles in frame3DD set pileinputs.ndiv>0
Jcktins.clamped= False #whether or not the bottom of the structure is rigidly connected. Use False when equivalent spring constants are being used.
Jcktins.AFflag = False #whether or not to use apparent fixity piles
Jcktins.PreBuildTPLvl = 2 #if >0, the TP is prebuilt according to rules per PreBuildTP
#Soil inputs
Soilinputs=SoilGeoInputs()
Soilinputs.zbots =-np.array([3.,5.,7.,15.,30.,50.])
Soilinputs.gammas =np.array([10000.,10000.,10000.,10000.,10000.,10000.])
Soilinputs.cus =np.array([60000.,60000.,60000.,60000.,60000.,60000.])
Soilinputs.phis =np.array([26.,26.,26.,26.,26.,26])#np.array([36.,33.,26.,37.,35.,37.5])#np.array([36.,33.,26.,37.,35.,37.5])
Soilinputs.delta =25.
Soilinputs.sndflg =True
Soilinputs.PenderSwtch =False #True
Soilinputs.SoilSF =1.
#Water and wind inputs
Waterinputs=WaterInputs()
Waterinputs.wdepth =30.
Waterinputs.wlevel =30. #Distance from bottom of structure to surface THIS, I believe is no longer needed as piles may be negative in z, to check and remove in case
Waterinputs.T=12. #Wave Period
Waterinputs.HW=10. #Wave Height
'''Windinputs=WindInputs()
Windinputs.HH=100. #CHECK HOW THIS COMPLIES....
Windinputs.U50HH=30. #assumed gust speed'''
#RNA loads Fx-z, Mxx-zz
#RNA_F=np.array([1000.e3,0.,0.,0.,0.,0.])
#Pile data
Pilematin=MatInputs()
Pilematin.matname=np.array(['steel'])
Pilematin.E=np.array([ 25.e9])
Dpile=2.5#0.75 # 2.0
tpile=0.01
Lp=20. #45
Pileinputs=PileGeoInputs()
Pileinputs.Pilematins=Pilematin
Pileinputs.ndiv=0 #3
Pileinputs.Dpile=Dpile
Pileinputs.tpile=tpile
Pileinputs.Lp=Lp #[m] Embedment length
#Legs data
legmatin=MatInputs()
legmatin.matname=(['steel','steel','steel','steel'])
legmatin.E=np.array([2.0e11])
Dleg=np.array([2.0,1.8,1.8,1.8,1.8,1.8])
tleg=1.55*np.array([0.0254]).repeat(Dleg.size)
leginputs=LegGeoInputs()
leginputs.legZbot = 1.0
leginputs.ndiv=1
leginputs.legmatins=legmatin
leginputs.Dleg=Dleg
leginputs.tleg=tleg
legbot_stmphin =1.5 #Distance from bottom of leg to second joint along z; must be>0
#Xbrc data
Xbrcmatin=MatInputs()
Xbrcmatin.matname=np.array(['steel']).repeat(Jcktins.nbays)
Xbrcmatin.E=np.array([ 2.2e11, 2.0e11,2.0e11,2.0e11,2.0e11])
Dbrc=np.array([1.,1.,1.0,1.0,1.0])
tbrc=np.array([1.,1.,1.0,1.0,1.0])*0.0254
Xbrcinputs=XBrcGeoInputs()
Xbrcinputs.Dbrc=Dbrc
Xbrcinputs.tbrc=tbrc
Xbrcinputs.ndiv=2#2
Xbrcinputs.Xbrcmatins=Xbrcmatin
Xbrcinputs.precalc=True #This can be set to true if we want Xbraces to be precalculated in D and t, in which case the above set Dbrc and tbrc would be overwritten
#Mbrc data
Mbrcmatin=MatInputs()
Mbrcmatin.matname=np.array(['steel'])
Mbrcmatin.E=np.array([ 2.5e11])
Dbrc_mud=1.5
Mbrcinputs=MudBrcGeoInputs()
Mbrcinputs.Dbrc_mud=Dbrc_mud
Mbrcinputs.ndiv=2
Mbrcinputs.Mbrcmatins=Mbrcmatin
Mbrcinputs.precalc=True #This can be set to true if we want Mudbrace to be precalculated in D and t, in which case the above set Dbrc_mud and tbrc_mud would be overwritten
#Hbrc data
Hbrcmatin=MatInputs()
Hbrcmatin.matname=np.array(['steel'])
Hbrcmatin.E=np.array([ 2.5e11])
Dbrc_hbrc=1.1
Hbrcinputs=HBrcGeoInputs()
Hbrcinputs.Dbrch=Dbrc_hbrc
Hbrcinputs.ndiv=0#2
Hbrcinputs.Hbrcmatins=Hbrcmatin
Hbrcinputs.precalc=True #This can be set to true if we want Hbrace to be set=Xbrace top D and t, in which case the above set Dbrch and tbrch would be overwritten
#TP data
TPlumpinputs=TPlumpMass()
TPlumpinputs.mass=300.e3 #[kg]
TPstmpsmatin=MatInputs()
TPbrcmatin=MatInputs()
TPstemmatin=MatInputs()
TPbrcmatin.matname=np.array(['steel'])
TPbrcmatin.E=np.array([ 2.5e11])
TPstemmatin.matname=np.array(['steel']).repeat(2)
TPstemmatin.E=np.array([ 2.1e11]).repeat(2)
TPinputs=TPGeoInputs()
TPinputs.TPbrcmatins=TPbrcmatin
TPinputs.TPstemmatins=TPstemmatin
TPinputs.TPstmpmatins=TPstmpsmatin
TPinputs.Dstrut=1.6
TPinputs.Dgir=Dbrc_hbrc
TPinputs.Dbrc=1.1
TPinputs.hstump=0.0#1.0
TPinputs.stumpndiv=1#2
TPinputs.brcndiv=1#2
TPinputs.girndiv=1#2
TPinputs.strutndiv=1#2
TPinputs.stemndiv=1#2
TPinputs.nstems=3
TPinputs.Dstem=np.array([6.]).repeat(TPinputs.nstems)
TPinputs.tstem=np.array([0.1,0.11,0.11])
TPinputs.hstem=np.array([4.,3.,1.])
#Tower data
Twrmatin=MatInputs()
Twrmatin.matname=np.array(['steel'])
Twrmatin.E=np.array([ 2.77e11])
Db=5.6
tb=0.05
Dt=Db*0.55
'''Twrinputs=TwrGeoInputs()
Twrinputs.Twrmatins=Twrmatin
#Twrinputs.Htwr=70. #Trumped by HH
Twrinputs.Htwr2frac=0.2 #fraction of tower height with constant x-section
Twrinputs.ndiv=np.array([6,6]) #ndiv for uniform and tapered section
Twrinputs.Db=Db
Twrinputs.DTRb=Db/tb
#Twrinputs.Dt=Dt'''
TwrRigidTop=True #False #False=Account for RNA via math rather than a physical rigidmember
#RNA data
'''RNAins=RNAprops()
RNAins.mass=3*350.e3
RNAins.I[0]=86.579E+6
RNAins.I[1]=53.530E+6
RNAins.I[2]=58.112E+6
RNAins.CMoff[2]=2.34
RNAins.yawangle=45. #angle with respect to global X, CCW looking from above, wind from left
RNAins.rna_weightM=True'''
#Frame3DD parameters
FrameAuxIns=Frame3DDaux()
FrameAuxIns.sh_fg=1 #shear flag-->Timoshenko
FrameAuxIns.deltaz=5.
FrameAuxIns.geo_fg=0
FrameAuxIns.nModes = 6 # number of desired dynamic modes of vibration
FrameAuxIns.Mmethod = 1 # 1: subspace Jacobi 2: Stodola
FrameAuxIns.lump = 0 # 0: consistent mass ... 1: lumped mass matrix
FrameAuxIns.tol = 1e-9 # mode shape tolerance
FrameAuxIns.shift = 0.0 # shift value ... for unrestrained structures
FrameAuxIns.gvector=np.array([0.,0.,-9.8065]) #GRAVITY
#Pass all inputs to jacket assembly
turbine.jacket.JcktGeoIn=Jcktins
turbine.jacket.Soilinputs=Soilinputs
turbine.jacket.Waterinputs=Waterinputs
#turbine.jacket.Windinputs=Windinputs
#turbine.jacket.RNA_F=RNA_F
turbine.jacket.Pileinputs=Pileinputs
turbine.jacket.leginputs=leginputs
turbine.jacket.legbot_stmphin =legbot_stmphin
turbine.jacket.Xbrcinputs=Xbrcinputs
turbine.jacket.Mbrcinputs=Mbrcinputs
turbine.jacket.Hbrcinputs=Hbrcinputs
turbine.jacket.TPlumpinputs=TPlumpinputs
turbine.jacket.TPinputs=TPinputs
#turbine.jacket.RNAinputs=RNAins
#turbine.jacket.Twrinputs=Twrinputs
turbine.jacket.Twrinputs.Twrmatins=Twrmatin
turbine.jacket.Twrinputs.Htwr2frac=0.2 #fraction of tower height with constant x-section
turbine.jacket.Twrinputs.ndiv=np.array([6,6]) #ndiv for uniform and tapered section
turbine.jacket.Twrinputs.Db=Db
turbine.jacket.Twrinputs.Dt=Dt
turbine.jacket.Twrinputs.DTRb=Db/tb
turbine.jacket.Twrinputs.DTRt=Db/Dt # TODO double check
turbine.jacket.TwrRigidTop=TwrRigidTop
turbine.jacket.FrameAuxIns=FrameAuxIns