############################################################################

# 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