def configure_blade():
top = Assembly()
configure_bladesurface(top, planform_nC=6)
# load the planform file
top.pf_splines.pfIn = read_blade_planform(
os.path.join(PATH, 'data/DTU_10MW_RWT_blade_axis_prebend.dat'))
top.blade_length = 86.366
top.span_ni = 5
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 40
# load the airfoil shapes defining the blade
for f in [
os.path.join(PATH, 'data/ffaw3241.dat'),
os.path.join(PATH, 'data/ffaw3301.dat'),
os.path.join(PATH, 'data/ffaw3360.dat'),
os.path.join(PATH, 'data/ffaw3480.dat'),
os.path.join(PATH, 'data/cylinder.dat')
]:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 1.])
return top
def configure_blade():
top = Assembly()
configure_bladesurface(top, os.path.join(PATH, 'data/DTU_10MW_RWT_blade_axis_prebend.dat'), planform_nC=6)
# load the planform file
top.blade_length = 86.366
top.span_ni = 5
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 40
# load the airfoil shapes defining the blade
for f in [os.path.join(PATH, 'data/ffaw3241.dat'),
os.path.join(PATH, 'data/ffaw3301.dat'),
os.path.join(PATH, 'data/ffaw3360.dat'),
os.path.join(PATH, 'data/ffaw3480.dat') ,
os.path.join(PATH, 'data/cylinder.dat')]:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 1.])
return top
def lofted_blade_shape_example():
top = Assembly()
configure_bladesurface(top, planform_nC=6)
# load the planform file
top.pf_splines.pfIn = read_blade_planform('data/DTU_10MW_RWT_blade_axis_prebend.dat')
top.blade_length = 86.366
top.span_ni = 50
print 'planform variables: ', top.pf_splines.pfOut.list_vars()
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 200
# load the airfoil shapes defining the blade
for f in ['data/ffaw3241.dat',
'data/ffaw3301.dat',
'data/ffaw3360.dat',
'data/ffaw3480.dat' ,
'data/tc72.dat' ,
'data/cylinder.dat']:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 0.72, 1.])
top.run()
pf = top.pf_splines.pfOut
plt.figure()
plt.title('chord')
plt.plot(pf.s, pf.chord)
plt.savefig('chord.eps')
plt.figure()
plt.title('twist')
plt.plot(pf.s, pf.rot_z)
plt.savefig('twist.eps')
plt.figure()
plt.title('relative thickness')
plt.plot(pf.s, pf.rthick)
plt.savefig('rthick.eps')
plt.figure()
plt.title('pitch axis aft leading edge')
plt.plot(pf.s, pf.p_le)
plt.savefig('p_le.eps')
plt.figure()
plt.axis('equal')
for i in range(b.span_ni):
plt.plot(b.surfout.surface[:, i, 0], b.surfout.surface[:, i, 1])
plt.savefig('lofted_blade.eps')
return top
def lofted_blade_shape_example():
top = Assembly()
configure_bladesurface(top, 'data/DTU_10MW_RWT_blade_axis_prebend.dat', planform_nC=6)
# load the planform file
top.blade_length = 86.366
top.span_ni = 50
print 'planform variables: ', top.pf_splines.pfOut.list_vars()
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 200
# load the airfoil shapes defining the blade
for f in ['data/ffaw3241.dat',
'data/ffaw3301.dat',
'data/ffaw3360.dat',
'data/ffaw3480.dat' ,
'data/tc72.dat' ,
'data/cylinder.dat']:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 0.72, 1.])
top.run()
pf = top.pf_splines.pfOut
plt.figure()
plt.title('chord')
plt.plot(pf.s, pf.chord)
plt.savefig('chord.eps')
plt.figure()
plt.title('twist')
plt.plot(pf.s, pf.rot_z)
plt.savefig('twist.eps')
plt.figure()
plt.title('relative thickness')
plt.plot(pf.s, pf.rthick)
plt.savefig('rthick.eps')
plt.figure()
plt.title('pitch axis aft leading edge')
plt.plot(pf.s, pf.p_le)
plt.savefig('p_le.eps')
plt.figure()
plt.axis('equal')
for i in range(b.span_ni):
plt.plot(b.surfout.surface[:, i, 0], b.surfout.surface[:, i, 1])
plt.savefig('lofted_blade.eps')
plt.savefig('lofted_blade.png')
return top
def execute(self):
""" Calculate the wingsurface from the spar geometry """
# Make sure that input data has the same length
self.verify_input()
for beam in self.eqbeams:
a = Assembly()
# Add a splined blade planform from the input data
a.add('pf_splines', SplinedBladePlanform(True))
a.driver.workflow.add('pf_splines')
a.pf_splines.nC = 3
a.pf_splines.pfIn = beam
a.pf_splines.configure_splines()
a.create_passthrough('pf_splines.blade_length')
a.create_passthrough('pf_splines.span_ni')
a.add('blade_surface', LoftedBladeSurface())
a.driver.workflow.add('blade_surface')
a.connect('pf_splines.pfOut', 'blade_surface.pf')
a.connect('span_ni', 'blade_surface.span_ni')
# load the planform file
a.span_ni = self.span_ni
b = a.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 200
for f in self.airfoils:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.25, 0.75])
self.wingsurf.append(a)
blade_loads = VarTree(DistributedLoadsExtVT(), iotype='out', desc='Spanwise load distributions')
blade_disps = VarTree(BeamDisplacementsVT(), iotype='out', desc='Blade deflections and rotations')
def execute(self):
print 'run some analysis here'
# --- 2 ---
top = Assembly()
# add splined planform description
configure_planform(top, 'data/DTU_10MW_RWT_blade_axis_prebend.dat')
top.blade_length = 86.366
top.span_ni = 30
# add aeroelastic solver
top.add('ae', AEsolver())
top.driver.workflow.add('ae')
# --- 3 ---
# configure the turbine with standard sub-components
configure_turbine(top.ae.wt)
# define overall dimensions
wt = top.ae.wt
wt.turbine_name = 'DTU 10MW RWT'
wt.doc = 'FUSED-Wind definition of the DTU 10MW RWT'
wt.tower_height = 115.63
desc='Blade deflections and rotations')
def execute(self):
print 'run some analysis here'
# --- 2 ---
top = Assembly()
# add splined planform description
configure_planform(top, 'data/DTU_10MW_RWT_blade_axis_prebend.dat')
top.blade_length = 86.366
top.span_ni = 30
# add aeroelastic solver
top.add('ae', AEsolver())
top.driver.workflow.add('ae')
# --- 3 ---
# configure the turbine with standard sub-components
configure_turbine(top.ae.wt)
# define overall dimensions
wt = top.ae.wt
wt.turbine_name = 'DTU 10MW RWT'
wt.doc = 'FUSED-Wind definition of the DTU 10MW RWT'
wt.tower_height = 115.63
