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Commit f5a62230 authored by Frederik Zahle's avatar Frederik Zahle
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fixing tests and other minor things

parent 73f4694a
Pipeline #288 failed with stage
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seamrotor/seamrotor.py
View file @ f5a62230
......@@ -11,10 +11,9 @@ from scipy.optimize import minimize
class SEAMBladeStructure(Component):
def __init__(self):
def __init__(self, nsections=21):
super(SEAMBladeStructure, self).__init__()
self.add_param('Nsections', 21, desc='number of sections')
self.add_param('lifetime_cycles', 1.e7, desc='')
self.add_param('wohler_exponent_blade_flap', 10.0, desc='')
......@@ -31,13 +30,13 @@ class SEAMBladeStructure(Component):
self.add_param('TIF_EDext', 1., desc='Technology improvement factor edge extreme')
self.add_param('TIF_FLfat', 1., desc='Technology improvement factor flap LEQ')
self.add_param('PMtarget', 1.0, desc='')
self.add_param('PMtarget_blade', 1.0, desc='')
self.add_param('sc_frac_flap', 0.3, desc='spar cap fraction of chord')
self.add_param('sc_frac_edge', 0.8, desc='spar cap fraction of thickness')
self.add_param('SF_blade', 1.1, desc='factor??')
self.add_param('Slim_ext_blade', 200.0, units='MPa', desc='')
self.add_param('Slim_fat_blade', 27, units='MPa', desc='')
self.add_param('Slim_fat_blade', 27., units='MPa', desc='')
self.add_param('AddWeightFactorBlade', 1.2, desc='Additional weight factor for blade shell')
self.add_param('blade_density', 2100., units='kg/m**3', desc='density of blades')
......@@ -45,6 +44,8 @@ class SEAMBladeStructure(Component):
self.add_output('blade_mass', 15.0, units='kg', desc='Blade mass' )
self.add_output('root_chord', 3.5, units='m', desc='blade root chord')
self.nsections = nsections
def solve_nonlinear(self, params, unknowns, resids):
rotor_radius = params['rotor_diameter'] / 2.
......@@ -70,7 +71,7 @@ class SEAMBladeStructure(Component):
W = Ine/(thick/2.)
sfat = np.maximum(1.e-6, params['SF_blade']*1.e3*Mfat_flap/ W / 1.e6)
PM = params['lifetime_cycles']/(pow(10, ( params['Slim_fat_blade'] - params['wohler_exponent_blade_flap']*np.log10(sfat))))
return abs(PM - params['PMtarget']) / norm
return abs(PM - params['PMtarget_blade']) / norm
# Solving for t in edge direction, fatigue
def solve_tfat_edge(t, C, thick, Mfat_edge, norm):
......@@ -78,9 +79,9 @@ class SEAMBladeStructure(Component):
W = Ine/(C/2.)
sfat = np.maximum(1.e-6, params['SF_blade']*1.e3*Mfat_edge/W/1.e6)
PM = params['lifetime_cycles']/(pow(10, ( params['Slim_fat_blade'] - params['wohler_exponent_blade_flap']*np.log10(sfat))))
return abs(PM - params['PMtarget']) / norm
return abs(PM - params['PMtarget_blade']) / norm
r = np.linspace(0, rotor_radius, params['Nsections'])
r = np.linspace(0, rotor_radius, self.nsections)
C = np.zeros(r.shape)
thick = np.zeros(r.shape)
root_chord = rotor_radius/25.
......@@ -93,7 +94,7 @@ class SEAMBladeStructure(Component):
unknowns['root_chord'] = root_chord
for i in range(params['Nsections']):
for i in range(self.nsections):
# Calculating the chord and thickness
if r[i] > (params['MaxChordrR']*rotor_radius):
......@@ -158,34 +159,33 @@ class SEAMBladeStructure(Component):
self.Mfat_edge = Mfat_edge
# Calculating thickness flapwise extreme
text_flap = np.zeros(params['Nsections'])
for i in range(params['Nsections']):
text_flap = np.zeros(self.nsections)
for i in range(self.nsections):
norm = solve_text_flap(0.01, C[i], thick[i], Mext_flap[i], 1.)
res = minimize(solve_text_flap, 0.01, args=(C[i], thick[i], Mext_flap[i], norm), bounds=[(1.e-6, 0.5)], method = 'SLSQP', tol = 1.e-8)
text_flap[i] = res['x']
if not res['success']: print('WARNING enter text_flap', i,res)
# Calculating thickness edgewise extreme
text_edge = np.zeros(params['Nsections'])
for i in range(params['Nsections']):
norm = solve_text_edge(0.01, C[i], thick[i], Mext_flap[i], 1.)
text_edge = np.zeros(self.nsections)
for i in range(self.nsections):
norm = solve_text_edge(0.01, C[i], thick[i], Mext_edge[i], 1.)
res = minimize(solve_text_edge, 0.01, args=(C[i], thick[i], Mext_edge[i], norm), bounds=[(1.e-6, 0.5)], method = 'SLSQP', tol = 1.e-8)
text_edge[i] = res['x']
if not res['success']: print('WARNING solve_text_edge', i,res)
# Calculating thickness flapwise fatigue
tfat_flap = np.zeros(params['Nsections'])
for i in range(params['Nsections']):
norm = solve_tfat_flap(0.01, C[i], thick[i], Mext_flap[i], 1.)
tfat_flap = np.zeros(self.nsections)
for i in range(self.nsections):
norm = solve_tfat_flap(0.01, C[i], thick[i], Mfat_flap[i], 1.)
res = minimize(solve_tfat_flap, 0.01, args=(C[i], thick[i], Mfat_flap[i], norm), bounds=[(1.e-6, 0.5)], method = 'SLSQP', tol = 1.e-8)
tfat_flap[i] = res['x']
if not res['success']: print('WARNING solve_tfat_flap', i, res)
# Calculating thickness edgewise fatigue
tfat_edge = np.zeros(params['Nsections'])
for i in range(params['Nsections']):
norm = solve_tfat_edge(0.01, C[i], thick[i], Mext_flap[i], 1.)
tfat_edge = np.zeros(self.nsections)
for i in range(self.nsections):
norm = solve_tfat_edge(0.01, C[i], thick[i], Mfat_edge[i], 1.)
res = minimize(solve_tfat_edge, 0.01, args=(C[i], thick[i], Mfat_edge[i], norm), bounds=[(1.e-6, 0.5)], method = 'SLSQP', tol = 1.e-8)
tfat_edge[i] = res['x']
if not res['success']: print('WARNING solve_tfat_edge', i,res)
......
seamrotor/test/test_seamrotor.py
View file @ f5a62230
......@@ -2,49 +2,38 @@
import unittest
import numpy as np
from openmdao.core import Group, Problem
from openmdao.api import Group, Problem, ScipyOptimizer, IndepVarComp
from seamrotor.seamrotor import SEAMBladeStructure
# __author__ = 'pire'
from openmdao.drivers.pyoptsparse_driver import pyOptSparseDriver
def setup_prob():
top = Problem(root=Group())
blade = top.root.add('blade', SEAMBladeStructure(), promotes=['*'])
top = Problem(root=Group())
blade = top.root.add('blade', SEAMBladeStructure(21), promotes=['*'])
top.setup()
blade.params['Nsections'] = 21
blade.params['lifetime_cycles'] = 1e7
blade.params['wohler_exponent_blade_flap'] = 10.0
blade.params['PMtarget'] = 1.0
blade.params['rotor_diameter'] = 177. #[m]
# blade.params['RootChord'] = 2.0 #[m]
# blade.params['MaxChord'] = 2.5 #[m]
blade.params['MaxChordrR'] = 0.2 #[m]
blade.params['blade_root_flap_max'] = 47225.
blade.params['blade_root_edge_max'] = 26712.
blade.params['TIF_FLext'] = 1. # Tech Impr Factor _ flap extreme
blade.params['TIF_EDext'] = 1.
blade.params['blade_root_flap_leq'] = 26975.
blade.params['blade_root_edge_leq'] = 24252.
blade.params['TIF_FLfat'] = 1.
blade.params['sc_frac_flap'] = 0.3 # sparcap fraction of chord flap
blade.params['sc_frac_edge'] = 0.8 # sparcap fraction of thickness edge
blade.params['SF_blade'] = 1.1 #[factor]
blade.params['Slim_ext_blade'] = 200.0
blade.params['Slim_fat_blade'] = 27
blade.params['AddWeightFactorBlade'] = 1.2 # Additional weight factor for blade shell
blade.params['blade_density'] = 2100. # [kg / m^3]
#blade.params['BladeCostPerMass'] = 15.0 #[e/kg]
#blade.params['HubCostPerMass'] = 3.5 #[e/kg]
#blade.params['SpinnerCostPerMass'] = 4.5 #[e/kg]
top['rotor_diameter'] = 177.
top['blade_root_flap_max'] = 47225.
top['blade_root_edge_max'] = 26712.
top['blade_root_flap_leq'] = 26975.
top['blade_root_edge_leq'] = 24252.
top['lifetime_cycles'] = 1e7
top['wohler_exponent_blade_flap'] = 10.0
top['PMtarget_blade'] = 1.0
top['MaxChordrR'] = 0.2
top['TIF_FLext'] = 1.
top['TIF_EDext'] = 1.
top['TIF_FLfat'] = 1.
top['sc_frac_flap'] = 0.3 # sparcap fraction of chord flap
top['sc_frac_edge'] = 0.8 # sparcap fraction of thickness edge
top['SF_blade'] = 1.1
top['Slim_ext_blade'] = 200.0
top['Slim_fat_blade'] = 27.
top['AddWeightFactorBlade'] = 1.2 # Additional weight factor for blade shell
top['blade_density'] = 2100. # [kg / m^3]
return top
class TestSEAMBladeStructure(unittest.TestCase):
......@@ -54,10 +43,10 @@ class TestSEAMBladeStructure(unittest.TestCase):
top = setup_prob()
top.run()
self.assertAlmostEqual(blade.unknowns['BladeWeight'], 30876.655915672229)
self.assertAlmostEqual(top['blade_mass']/33485.1942627, 1., places=6)
if __name__ == "__main__":
# unittest.main()
top = setup_prob()
top.run()
unittest.main()
# top = setup_prob()
# top.run()
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