comp.add_output('precone', val=0., units='deg')
# comp.add_output('omega', val=236, shape=NUM_NODES, units='rad/s')
comp.add_output('hub_diameter', val=30, units='cm')
comp.add_output('prop_diameter', val=150, units='cm')
comp.add_output('pitch', val=0, shape=NUM_NODES, units='rad')
comp.add_output('chord_dv', val=10, shape=NUM_CP, units='cm')
comp.add_output('theta_dv', val=np.linspace(65., 25., NUM_CP)*np.pi/180.,
shape=NUM_CP, units='rad')
comp.add_output('omega_max', val=500, units='rad/s')
comp.add_output('omega_min', val=200, units='rad/s')
comp.add_output('tsr2', val=200)
p.model.add_subsystem('ivc', comp, promotes=['*'])
comp = GeometryGroup(num_nodes=NUM_NODES, num_cp=NUM_CP,
num_radial=NUM_RADIAL)
p.model.add_subsystem('geom', comp,
promotes_inputs=['chord_dv', 'theta_dv', 'pitch'],
promotes_outputs=['radii', 'dradii', 'chord', 'theta']
)
p.model.connect('hub_diameter', 'geom.hub_diameter', src_indices=[0]*NUM_NODES)
p.model.connect('prop_diameter', 'geom.prop_diameter', src_indices=[0]*NUM_NODES)
comp = ccb.CCBladeGroup(num_nodes=NUM_NODES, num_radial=NUM_RADIAL,
airfoil_interp=ccblade_interp,
turbine=False)
p.model.add_subsystem('omega_calc', Omega(num_nodes=NUM_NODES),
promotes_inputs=['prop_diameter', 'omega_min', 'omega_max', 'tsr2', 'v'],
def main():
interp = ViternaAirfoil().create_akima('mh117',
Re_scaling=False,
extend_alpha=True)
def ccblade_interp(alpha, Re, Mach):
shape = alpha.shape
x = np.concatenate(
[alpha.flatten()[:, np.newaxis],
Re.flatten()[:, np.newaxis]],
axis=-1)
y = interp(x)
y.shape = shape + (2, )
return y[..., 0], y[..., 1]
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
chord = 10.
theta = np.linspace(65., 25., num_cp) * np.pi / 180.
pitch = 0.
prop_data = {
'num_radial': num_radial,
'num_cp': num_cp,
'pitch': pitch,
'chord': chord,
'theta': theta,
'spline_type': 'akima',
'B': num_blades,
'interp': interp
}
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4 * 287.058 * 300.) # meters/second
rho0 = 1.4 * 98600. / (c0 * c0) # kg/m^3
omega = 236.
prob = Problem()
comp = IndepVarComp()
comp.add_discrete_input('B', val=num_blades)
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter',
val=hub_diameter,
shape=num_nodes,
units='cm')
comp.add_output('prop_diameter',
val=prop_diameter,
shape=num_nodes,
units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob.model.add_subsystem('inputs_comp', comp, promotes=['*'])
prob.model.add_subsystem('bemt_group',
BEMTGroup(num_nodes=num_nodes,
prop_data=prop_data),
promotes_inputs=[
'rho', 'mu', 'v', 'alpha', 'incidence',
'omega', 'hub_diameter', 'prop_diameter',
'pitch', 'chord_dv', 'theta_dv'
],
promotes_outputs=[
('normal_load_dist', 'openbemt_normal_load'),
('circum_load_dist', 'openbemt_circum_load')
])
comp = GeometryGroup(num_nodes=num_nodes,
num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group',
comp,
promotes_inputs=[
'hub_diameter', 'prop_diameter', 'chord_dv', 'theta_dv', 'pitch'
],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = SimpleInflow(num_nodes=num_nodes, num_radial=num_radial)
prob.model.add_subsystem(
'inflow_comp',
comp,
promotes_inputs=['v', 'omega', 'radii', 'precone'],
promotes_outputs=['Vx', 'Vy'])
comp = CCBladeGroup(num_nodes=num_nodes,
num_radial=num_radial,
airfoil_interp=ccblade_interp,
turbine=False,
phi_residual_solve_nonlinear='bracketing')
prob.model.add_subsystem('ccblade_group',
comp,
promotes_inputs=[
'B', 'radii', 'dradii', 'chord', 'theta',
'rho', 'mu', 'asound', 'Vx', 'Vy', 'v',
'precone', 'omega', 'hub_diameter',
'prop_diameter'
],
promotes_outputs=[('Np', 'ccblade_normal_load'),
('Tp', 'ccblade_circum_load')])
prob.setup()
prob.final_setup()
prob.run_model()
make_plots(prob)
def main():
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
af_filename = 'mh117.dat'
chord = np.tile(10., (num_nodes, num_cp))
theta = np.tile(np.linspace(65., 25., num_cp)*np.pi/180., (num_nodes, 1))
pitch = 0.
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4*287.058*300.) # meters/second
rho0 = 1.4*98600./(c0*c0) # kg/m^3
omega = 236.
prob = Problem()
v = np.linspace(1., 1.5, num_nodes)*77.2
comp = IndepVarComp()
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=v, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., shape=num_nodes, units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter', val=hub_diameter, shape=num_nodes, units='cm')
comp.add_output('prop_diameter', val=prop_diameter, shape=num_nodes, units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=(num_nodes, num_cp), units='cm')
comp.add_output('theta_dv', val=theta, shape=(num_nodes, num_cp), units='rad')
prob.model.add_subsystem('indep_var_comp', comp, promotes=['*'])
comp = GeometryGroup(num_nodes=num_nodes, num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group', comp,
promotes_inputs=['hub_diameter', 'prop_diameter', 'chord_dv',
'theta_dv', 'pitch'],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = SimpleInflow(num_nodes=num_nodes, num_radial=num_radial)
prob.model.add_subsystem(
'inflow_comp', comp,
promotes_inputs=['v', 'omega', 'radii', 'precone'],
promotes_outputs=['Vx', 'Vy'])
comp = CCBladeGroup(num_nodes=num_nodes, num_radial=num_radial,
num_blades=num_blades, af_filename=af_filename,
turbine=False)
prob.model.add_subsystem(
'ccblade_group', comp,
promotes_inputs=['radii', 'dradii', 'chord', 'theta', 'rho', 'mu',
'asound', 'v', 'precone', 'omega', 'Vx', 'Vy',
'precone', 'hub_diameter', 'prop_diameter'],
promotes_outputs=['thrust', 'torque', 'efficiency'])
# prob.model.add_design_var('chord_dv', lower=1., upper=20.,
# scaler=5e-2)
# prob.model.add_design_var('theta_dv',
# lower=20.*np.pi/180., upper=90*np.pi/180.)
# prob.model.add_objective('efficiency', scaler=-1.,)
# prob.model.add_constraint('thrust', equals=700., scaler=1e-3,
# indices=np.arange(num_nodes))
# prob.driver = pyOptSparseDriver()
# prob.driver.options['optimizer'] = 'SNOPT'
prob.setup()
prob.final_setup()
st = time.time()
# prob.run_driver()
prob.run_model()
elapsed_time = time.time() - st
make_plots(prob)
return elapsed_time
def main():
num_nodes = 1
num_blades = 10
num_radial = 15
num_cp = 6
af_filename = 'airfoils/mh117.dat'
chord = 20.
theta = 5.0*np.pi/180.0
pitch = 0.
# Numbers taken from the Aviary group's study of the RVLT tiltwing
# turboelectric concept vehicle.
n_props = 4
hub_diameter = 30. # cm
prop_diameter = 15*30.48 # 15 ft in cm
c0 = np.sqrt(1.4*287.058*300.) # meters/second
rho0 = 1.4*98600./(c0*c0) # kg/m^3
omega = 236. # rad/s
# Find the thrust per rotor from the vehicle's mass.
m_full = 6367 # kg
g = 9.81 # m/s**2
thrust_vtol = m_full*g/n_props
prob = Problem()
comp = IndepVarComp()
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=2., shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('hub_diameter', val=hub_diameter, shape=num_nodes, units='cm')
comp.add_output('prop_diameter', val=prop_diameter, shape=num_nodes, units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
comp.add_output('thrust_vtol', val=thrust_vtol, shape=num_nodes, units='N')
prob.model.add_subsystem('indep_var_comp', comp, promotes=['*'])
comp = GeometryGroup(num_nodes=num_nodes, num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group', comp,
promotes_inputs=['hub_diameter', 'prop_diameter', 'chord_dv',
'theta_dv', 'pitch'],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
balance_group = Group()
comp = CCBladeGroup(num_nodes=num_nodes, num_radial=num_radial,
num_blades=num_blades, af_filename=af_filename,
turbine=False)
balance_group.add_subsystem(
'ccblade_group', comp,
promotes_inputs=['radii', 'dradii', 'chord', 'theta', 'rho', 'mu',
'asound', 'v', 'precone', 'omega', 'hub_diameter',
'prop_diameter'],
promotes_outputs=['thrust', 'torque', 'efficiency'])
comp = BalanceComp()
comp.add_balance(
name='omega',
eq_units='N', lhs_name='thrust', rhs_name='thrust_vtol',
val=omega, units='rad/s',
lower=0.)
balance_group.add_subsystem('thrust_balance_comp', comp, promotes=['*'])
balance_group.linear_solver = DirectSolver(assemble_jac=True)
# balance_group.nonlinear_solver = NewtonSolver(maxiter=20, iprint=2)
# balance_group.nonlinear_solver.options['solve_subsystems'] = True
# balance_group.nonlinear_solver.options['atol'] = 1e-9
prob.model.add_subsystem('thrust_balance_group', balance_group,
promotes=['*'])
prob.model.nonlinear_solver = NewtonSolver(maxiter=20, iprint=2)
prob.model.nonlinear_solver.options['solve_subsystems'] = True
prob.model.nonlinear_solver.options['atol'] = 1e-9
prob.model.nonlinear_solver.linesearch = BoundsEnforceLS()
prob.model.nonlinear_solver.linesearch.options['iprint'] = 2
prob.setup()
prob.final_setup()
# Calculate the induced axial velocity at the rotor for hover, used for
# non-diminsionalation.
rho = prob.get_val('rho', units='kg/m**3')[0]
hub_diameter = prob.get_val('hub_diameter', units='m')[0]
prop_diameter = prob.get_val('prop_diameter', units='m')[0]
thrust_vtol = prob.get_val('thrust_vtol', units='N')[0]
A_rotor = 0.25*np.pi*(prop_diameter**2 - hub_diameter**2)
v_h = np.sqrt(thrust_vtol/(2*rho*A_rotor))
# Climb:
climb_velocity_nondim = np.linspace(0.1, 2., 10)
induced_velocity_nondim = np.zeros_like(climb_velocity_nondim)
for vc, vi in np.nditer(
[climb_velocity_nondim, induced_velocity_nondim],
op_flags=[['readonly'], ['writeonly']]):
# Run the model with the requested climb velocity.
prob.set_val('v', vc*v_h, units='m/s')
print(f"v = {prob.get_val('v', units='m/s')}")
prob.run_model()
# Calculate the area-weighted average induced velocity at the rotor.
# Need the area of each blade section.
radii = prob.get_val('radii',
units='m')
dradii = prob.get_val('dradii',
units='m')
dArea = 2*np.pi*radii*dradii
# Get the induced velocity at the rotor plane for each blade section.
Vx = prob.get_val('ccblade_group.Vx', units='m/s')
a = prob.get_val('ccblade_group.ccblade_comp.a')
# Get the area-weighted average of the induced velocity.
vi[...] = np.sum(a*Vx*dArea/A_rotor)/v_h
# Induced velocity from plain old momentum theory (for climb).
induced_velocity_mt = (
-0.5*climb_velocity_nondim + np.sqrt((0.5*climb_velocity_nondim)**2 + 1.))
fig, ax = plt.subplots()
ax.plot(climb_velocity_nondim, -induced_velocity_nondim,
label='CCBlade.jl (climb)')
ax.plot(climb_velocity_nondim, induced_velocity_mt,
label='Momentum Theory (climb)')
# Descent:
climb_velocity_nondim = np.linspace(-4., -2.5, 10)
induced_velocity_nondim = np.zeros_like(climb_velocity_nondim)
for vc, vi in np.nditer(
[climb_velocity_nondim, induced_velocity_nondim],
op_flags=[['readonly'], ['writeonly']]):
# Run the model with the requested climb velocity.
prob.set_val('v', vc*v_h, units='m/s')
print(f"vc = {vc}, v = {prob.get_val('v', units='m/s')}")
prob.run_model()
# Calculate the area-weighted average induced velocity at the rotor.
# Need the area of each blade section.
radii = prob.get_val('radii',
units='m')
dradii = prob.get_val('dradii',
units='m')
dArea = 2*np.pi*radii*dradii
# Get the induced velocity at the rotor plane for each blade section.
Vx = prob.get_val('ccblade_group.Vx', units='m/s')
a = prob.get_val('ccblade_group.ccblade_comp.a')
# Get the area-weighted average of the induced velocity.
vi[...] = np.sum(a*Vx*dArea/A_rotor)/v_h
# Induced velocity from plain old momentum theory (for descent).
induced_velocity_mt = (
-0.5*climb_velocity_nondim - np.sqrt((0.5*climb_velocity_nondim)**2 - 1.))
# Plot the induced velocity for descent.
ax.plot(climb_velocity_nondim, -induced_velocity_nondim,
label='CCBlade.jl (descent)')
ax.plot(climb_velocity_nondim, induced_velocity_mt,
label='Momentum Theory (descent)')
# # Empirical region:
# climb_velocity_nondim = np.linspace(-1.9, -1.5, 5)
# induced_velocity_nondim = np.zeros_like(climb_velocity_nondim)
# for vc, vi in np.nditer(
# [climb_velocity_nondim, induced_velocity_nondim],
# op_flags=[['readonly'], ['writeonly']]):
# # Run the model with the requested climb velocity.
# prob.set_val('v', vc*v_h, units='m/s')
# print(f"vc = {vc}, v = {prob.get_val('v', units='m/s')}")
# prob.run_model()
# # Calculate the area-weighted average induced velocity at the rotor.
# # Need the area of each blade section.
# radii = prob.get_val('radii',
# units='m')
# dradii = prob.get_val('dradii',
# units='m')
# dArea = 2*np.pi*radii*dradii
# # Get the induced velocity at the rotor plane for each blade section.
# Vx = prob.get_val('ccblade_group.Vx', units='m/s')
# a = prob.get_val('ccblade_group.ccblade_comp.a')
# # Get the area-weighted average of the induced velocity.
# vi[...] = np.sum(a*Vx*dArea/A_rotor)/v_h
# # Plot the induced velocity for the empirical region.
# ax.plot(climb_velocity_nondim, -induced_velocity_nondim,
# label='CCBlade.jl (empirical region)')
ax.set_xlabel('Vc/vh')
ax.set_ylabel('Vi/vh')
ax.legend()
fig.savefig('induced_velocity.png')
def main():
interp = ViternaAirfoil().create_akima(
'mh117', Re_scaling=False, extend_alpha=True)
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
af_filename = 'airfoils/mh117.dat'
chord = 10.
theta = np.linspace(65., 25., num_cp)*np.pi/180.
pitch = 0.
prop_data = {
'num_radial': num_radial,
'num_cp': num_cp,
'pitch': pitch,
'chord': chord,
'theta': theta,
'spline_type': 'akima',
'B': num_blades,
'interp': interp}
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4*287.058*300.) # meters/second
rho0 = 1.4*98600./(c0*c0) # kg/m^3
omega = 236.
prob = Problem()
comp = IndepVarComp()
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter', val=hub_diameter, shape=num_nodes, units='cm')
comp.add_output('prop_diameter', val=prop_diameter, shape=num_nodes, units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob.model.add_subsystem('inputs_comp', comp, promotes=['*'])
prob.model.add_subsystem(
'bemt_group', BEMTGroup(num_nodes=num_nodes, prop_data=prop_data),
promotes_inputs=['rho', 'mu', 'v', 'alpha', 'incidence', 'omega',
'hub_diameter', 'prop_diameter', 'pitch', 'chord_dv',
'theta_dv'],
promotes_outputs=[('normal_load_dist', 'openbemt_normal_load'),
('circum_load_dist', 'openbemt_circum_load')])
comp = GeometryGroup(num_nodes=num_nodes, num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group', comp,
promotes_inputs=['hub_diameter', 'prop_diameter', 'chord_dv',
'theta_dv', 'pitch'],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = CCBladeGroup(num_nodes=num_nodes, num_radial=num_radial,
num_blades=num_blades, af_filename=af_filename,
turbine=False)
prob.model.add_subsystem(
'ccblade_group', comp,
promotes_inputs=['radii', 'dradii', 'chord', 'theta', 'rho', 'mu',
'asound', 'v', 'precone', 'omega', 'hub_diameter',
'prop_diameter'],
promotes_outputs=[('Np', 'ccblade_normal_load'),
('Tp', 'ccblade_circum_load')])
prob.setup()
prob.final_setup()
prob.run_model()
make_plots(prob)
def main():
interp = ViternaAirfoil().create_akima('mh117',
Re_scaling=False,
extend_alpha=True)
def ccblade_interp(alpha, Re, Mach):
shape = alpha.shape
x = np.concatenate(
[alpha.flatten()[:, np.newaxis],
Re.flatten()[:, np.newaxis]],
axis=-1)
y = interp(x)
y.shape = shape + (2, )
return y[..., 0], y[..., 1]
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
chord = 10.
theta = np.linspace(65., 25., num_cp) * np.pi / 180.
pitch = 0.
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4 * 287.058 * 300.) # meters/second
rho0 = 1.4 * 98600. / (c0 * c0) # kg/m^3
omega = 236.
prob = Problem()
comp = IndepVarComp()
comp.add_discrete_input('B', val=num_blades)
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter',
val=hub_diameter,
shape=num_nodes,
units='cm')
comp.add_output('prop_diameter',
val=prop_diameter,
shape=num_nodes,
units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob.model.add_subsystem('inputs_comp', comp, promotes=['*'])
comp = GeometryGroup(num_nodes=num_nodes,
num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group',
comp,
promotes_inputs=[
'hub_diameter', 'prop_diameter', 'chord_dv', 'theta_dv', 'pitch'
],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = CCBladeGroup(num_nodes=num_nodes,
num_radial=num_radial,
airfoil_interp=ccblade_interp,
turbine=False,
phi_residual_solve_nonlinear=False)
prob.model.add_subsystem('ccblade_group',
comp,
promotes_inputs=[
'B', 'radii', 'dradii', 'chord', 'theta',
'rho', 'mu', 'asound', 'v', 'precone',
'omega', 'hub_diameter', 'prop_diameter'
],
promotes_outputs=[('Np', 'ccblade_normal_load'),
('Tp', 'ccblade_circum_load')])
prob.setup()
prob.final_setup()
eps = 1e-2
num_phi = 45
phi = np.linspace(-0.5 * np.pi + eps, 0.0 - eps, num_phi)
phi = np.tile(phi[:, np.newaxis, np.newaxis], (1, num_nodes, num_radial))
phi_residual = np.zeros_like(phi)
for i in range(num_phi):
p = phi[i, :, :]
prob.set_val('ccblade_group.ccblade_comp.phi', p, units='rad')
prob.run_model()
prob.model.run_apply_nonlinear()
inputs, outputs, residuals = prob.model.get_nonlinear_vectors()
phi_residual[i, :, :] = residuals['ccblade_group.ccblade_comp.phi']
make_individual_plots(prob, phi, phi_residual, 'phi_residual-r{:02d}.png')
def main():
interp = ViternaAirfoil().create_akima(
'mh117', Re_scaling=False, extend_alpha=True)
def ccblade_interp(alpha, Re, Mach):
shape = alpha.shape
x = np.concatenate(
[
alpha.flatten()[:, np.newaxis],
Re.flatten()[:, np.newaxis]
], axis=-1)
y = interp(x)
y.shape = shape + (2,)
return y[..., 0], y[..., 1]
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
chord = 10.
theta = np.linspace(65., 25., num_cp)*np.pi/180.
pitch = 0.
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4*287.058*300.) # meters/second
rho0 = 1.4*98600./(c0*c0) # kg/m^3
omega = 236.
prob = Problem()
comp = IndepVarComp()
comp.add_discrete_input('B', val=num_blades)
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter', val=hub_diameter, shape=num_nodes, units='cm')
comp.add_output('prop_diameter', val=prop_diameter, shape=num_nodes, units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob.model.add_subsystem('indep_var_comp', comp, promotes=['*'])
comp = GeometryGroup(num_nodes=num_nodes, num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group', comp,
promotes_inputs=['hub_diameter', 'prop_diameter', 'chord_dv',
'theta_dv', 'pitch'],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = SimpleInflow(num_nodes=num_nodes, num_radial=num_radial)
prob.model.add_subsystem(
'inflow_comp', comp,
promotes_inputs=['v', 'omega', 'radii', 'precone'],
promotes_outputs=['Vx', 'Vy'])
comp = CCBladeGroup(num_nodes=num_nodes, num_radial=num_radial,
num_blades=num_blades,
airfoil_interp=ccblade_interp, turbine=False,
phi_residual_solve_nonlinear='bracketing')
prob.model.add_subsystem(
'ccblade_group', comp,
promotes_inputs=['radii', 'dradii', 'chord', 'theta', 'rho',
'mu', 'asound', 'v', 'omega', 'Vx', 'Vy', 'precone',
'hub_diameter', 'prop_diameter'],
promotes_outputs=['thrust', 'torque', 'efficiency'])
prob.model.add_design_var('chord_dv', lower=1., upper=20.,
scaler=5e-2)
prob.model.add_design_var('theta_dv',
lower=20.*np.pi/180., upper=90*np.pi/180.)
prob.model.add_objective('efficiency', scaler=-1.,)
prob.model.add_constraint('thrust', equals=700., scaler=1e-3,
indices=np.arange(num_nodes))
prob.driver = pyOptSparseDriver()
prob.driver.options['optimizer'] = 'SNOPT'
prob.setup()
prob.final_setup()
st = time.time()
prob.run_driver()
elapsed_time = time.time() - st
make_plots(prob)
return elapsed_time
def test_openbemt_optimization(self):
interp = ViternaAirfoil().create_akima('mh117',
Re_scaling=False,
extend_alpha=True)
def ccblade_interp(alpha, Re, Mach):
shape = alpha.shape
x = np.concatenate(
[alpha.flatten()[:, np.newaxis],
Re.flatten()[:, np.newaxis]],
axis=-1)
y = interp(x)
y.shape = shape + (2, )
return y[..., 0], y[..., 1]
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
chord = 10.
theta = np.linspace(65., 25., num_cp) * np.pi / 180.
pitch = 0.
prop_data = {
'num_radial': num_radial,
'num_cp': num_cp,
'pitch': pitch,
'chord': chord,
'theta': theta,
'spline_type': 'akima',
'B': num_blades,
'interp': interp
}
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4 * 287.058 * 300.) # meters/second
rho0 = 1.4 * 98600. / (c0 * c0) # kg/m^3
omega = 236.
prob_ccblade = om.Problem()
prob_openbemt = om.Problem()
comp = om.IndepVarComp()
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter', val=hub_diameter, units='cm')
comp.add_output('prop_diameter', val=prop_diameter, units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob_ccblade.model.add_subsystem('indep_var_comp',
comp,
promotes=['*'])
prob_openbemt.model.add_subsystem('indep_var_comp',
comp,
promotes=['*'])
comp = GeometryGroup(num_nodes=num_nodes,
num_cp=num_cp,
num_radial=num_radial)
prob_ccblade.model.add_subsystem(
'geometry_group',
comp,
promotes_inputs=[
'hub_diameter', 'prop_diameter', 'chord_dv', 'theta_dv',
'pitch'
],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = SimpleInflow(num_nodes=num_nodes, num_radial=num_radial)
prob_ccblade.model.add_subsystem(
'inflow_comp',
comp,
promotes_inputs=['v', 'omega', 'radii', 'precone'],
promotes_outputs=['Vx', 'Vy'])
comp = CCBladeGroup(num_nodes=num_nodes,
num_radial=num_radial,
num_blades=num_blades,
airfoil_interp=ccblade_interp,
turbine=False)
prob_ccblade.model.add_subsystem(
'ccblade_group',
comp,
promotes_inputs=[
'radii', 'dradii', 'chord', 'theta', 'rho', 'mu', 'asound',
'v', 'omega', 'Vx', 'Vy', 'precone', 'hub_diameter',
'prop_diameter'
],
promotes_outputs=['thrust', 'torque', 'efficiency'])
prob_ccblade.model.add_design_var('chord_dv',
lower=1.,
upper=20.,
scaler=5e-2)
prob_ccblade.model.add_design_var('theta_dv',
lower=20. * np.pi / 180.,
upper=90 * np.pi / 180.)
prob_ccblade.model.add_objective(
'efficiency',
scaler=-1.,
)
prob_ccblade.model.add_constraint('thrust',
equals=700.,
scaler=1e-3,
indices=np.arange(num_nodes))
prob_ccblade.driver = om.pyOptSparseDriver()
prob_ccblade.driver.options['optimizer'] = 'SNOPT'
prob_ccblade.setup()
prob_ccblade.final_setup()
prob_ccblade.run_driver()
ccblade_normal_load = prob_ccblade.get_val('ccblade_group.Np',
units='N/m') * num_blades
ccblade_circum_load = prob_ccblade.get_val('ccblade_group.Tp',
units='N/m') * num_blades
prob_openbemt.model.add_subsystem(
'bemt_group',
BEMTGroup(num_nodes=num_nodes, prop_data=prop_data),
promotes_inputs=[
'rho', 'mu', 'v', 'alpha', 'incidence', 'omega',
'hub_diameter', 'prop_diameter', 'pitch', 'chord_dv',
'theta_dv'
],
promotes_outputs=[('normal_load_dist', 'openbemt_normal_load'),
('circum_load_dist', 'openbemt_circum_load'),
'dradii', 'thrust', 'efficiency'])
prob_openbemt.model.add_design_var('chord_dv',
lower=1.,
upper=20.,
scaler=5e-2)
prob_openbemt.model.add_design_var('theta_dv',
lower=20. * np.pi / 180.,
upper=90 * np.pi / 180.)
prob_openbemt.model.add_objective(
'efficiency',
scaler=-1.,
)
prob_openbemt.model.add_constraint('thrust',
equals=700.,
scaler=1e-3,
indices=np.arange(num_nodes))
prob_openbemt.driver = om.pyOptSparseDriver()
prob_openbemt.driver.options['optimizer'] = 'SNOPT'
prob_openbemt.setup()
prob_openbemt.final_setup()
prob_openbemt.model.bemt_group.phi_group.nonlinear_solver.options[
'iprint'] = 0
prob_openbemt.run_driver()
openbemt_normal_load = prob_openbemt.get_val('openbemt_normal_load',
units='N')
openbemt_circum_load = prob_openbemt.get_val('openbemt_circum_load',
units='N')
dradii = prob_openbemt.get_val('dradii', units='m')
openbemt_normal_load /= dradii
openbemt_circum_load /= dradii
assert_rel_error(self, ccblade_normal_load, openbemt_normal_load, 1e-2)
assert_rel_error(self, ccblade_circum_load, openbemt_circum_load, 1e-2)