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Merge pull request #3 from WISDEM/f/BRFM
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stall margin from OF
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@johnjasa
johnjasa authored Nov 19, 2020
2 parents 8f9d1d3 + 58800da commit 9e25445
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Showing 2 changed files with 41 additions and 5 deletions.
33 changes: 33 additions & 0 deletions weis/aeroelasticse/openmdao_openfast.py
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Original file line number Diff line number Diff line change
Expand Up @@ -265,6 +265,9 @@ def setup(self):
self.add_output('C_miners_SC_PS', val=np.zeros((n_span, n_mat, 2)), desc="Miner's rule cummulative damage to Spar Cap, pressure side")
# self.add_output('C_miners_TE_SS', val=np.zeros((n_span, n_mat, 2)), desc="Miner's rule cummulative damage to Trailing-Edge reinforcement, suction side")
# self.add_output('C_miners_TE_PS', val=np.zeros((n_span, n_mat, 2)), desc="Miner's rule cummulative damage to Trailing-Edge reinforcement, pressure side")
self.add_output('max_aoa', val=np.zeros(n_span), units='deg', desc='distributed angles of attack - max')
self.add_output('std_aoa', val=np.zeros(n_span), units='deg', desc='distributed angles of attack - std')
self.add_output('mean_aoa', val=np.zeros(n_span), units='deg', desc='distributed angles of attack - mean')

self.add_discrete_output('fst_vt_out', val={})

Expand Down Expand Up @@ -539,10 +542,12 @@ def run_FAST(self, inputs, discrete_inputs, fst_vt):
channels_out += ["Spn1MLyb1", "Spn2MLyb1", "Spn3MLyb1", "Spn4MLyb1", "Spn5MLyb1", "Spn6MLyb1", "Spn7MLyb1", "Spn8MLyb1", "Spn9MLyb1"]
channels_out += ["RtAeroFxh", "RtAeroFyh", "RtAeroFzh"]
channels_out += ["RotThrust", "LSShftFys", "LSShftFzs", "RotTorq", "LSSTipMys", "LSSTipMzs"]
channels_out += ["B1N1Alpha", "B1N2Alpha", "B1N3Alpha", "B1N4Alpha", "B1N5Alpha", "B1N6Alpha", "B1N7Alpha", "B1N8Alpha", "B1N9Alpha", "B2N1Alpha", "B2N2Alpha", "B2N3Alpha", "B2N4Alpha", "B2N5Alpha", "B2N6Alpha", "B2N7Alpha", "B2N8Alpha","B2N9Alpha"]
if self.n_blades > 2:
channels_out += ["TipDxc3", "TipDyc3", "TipDzc3", "RootMxc3", "RootMyc3", "RootMzc3", "TipDxb3", "TipDyb3", "TipDzb3", "RootMxb3",
"RootMyb3", "RootMzb3", "RootFxc3", "RootFyc3", "RootFzc3", "RootFxb3", "RootFyb3", "RootFzb3", "BldPitch3"]
channels_out += ["B3N1Fx", "B3N2Fx", "B3N3Fx", "B3N4Fx", "B3N5Fx", "B3N6Fx", "B3N7Fx", "B3N8Fx", "B3N9Fx", "B3N1Fy", "B3N2Fy", "B3N3Fy", "B3N4Fy", "B3N5Fy", "B3N6Fy", "B3N7Fy", "B3N8Fy", "B3N9Fy"]
channels_out += ["B3N1Alpha", "B3N2Alpha", "B3N3Alpha", "B3N4Alpha", "B3N5Alpha", "B3N6Alpha", "B3N7Alpha", "B3N8Alpha", "B3N9Alpha"]

# Add additional options
if ('channels_out',) in self.options['modeling_options']['openfast']['fst_settings']:
Expand Down Expand Up @@ -851,6 +856,34 @@ def post_process(self, FAST_Output, case_list, dlc_list, inputs, discrete_inputs
extreme_table['LSShftM'][np.argmax(sum_stats['LSShftM']['max'])]['LSSTipMys']['val'],
extreme_table['LSShftM'][np.argmax(sum_stats['LSShftM']['max'])]['LSSTipMzs']['val']])*1.e3

## Post process aerodynamic data
# Angles of attack - max, std, mean
blade1_chans_aoa = ["B1N1Alpha", "B1N2Alpha", "B1N3Alpha", "B1N4Alpha", "B1N5Alpha", "B1N6Alpha", "B1N7Alpha", "B1N8Alpha", "B1N9Alpha"]
blade2_chans_aoa = ["B2N1Alpha", "B2N2Alpha", "B2N3Alpha", "B2N4Alpha", "B2N5Alpha", "B2N6Alpha", "B2N7Alpha", "B2N8Alpha", "B2N9Alpha"]
aoa_max_B1 = [np.max(sum_stats[var]['max']) for var in blade1_chans_aoa]
aoa_mean_B1 = [np.mean(sum_stats[var]['mean']) for var in blade1_chans_aoa]
aoa_std_B1 = [np.mean(sum_stats[var]['std']) for var in blade1_chans_aoa]
aoa_max_B2 = [np.max(sum_stats[var]['max']) for var in blade2_chans_aoa]
aoa_mean_B2 = [np.mean(sum_stats[var]['mean']) for var in blade2_chans_aoa]
aoa_std_B2 = [np.mean(sum_stats[var]['std']) for var in blade2_chans_aoa]
if self.n_blades == 2:
spline_aoa_max = PchipInterpolator(self.R_out, np.max([aoa_max_B1, aoa_max_B2], axis=0))
spline_aoa_std = PchipInterpolator(self.R_out, np.mean([aoa_std_B1, aoa_std_B2], axis=0))
spline_aoa_mean = PchipInterpolator(self.R_out, np.mean([aoa_mean_B1, aoa_mean_B2], axis=0))
elif self.n_blades == 3:
blade3_chans_aoa = ["B3N1Alpha", "B3N2Alpha", "B3N3Alpha", "B3N4Alpha", "B3N5Alpha", "B3N6Alpha", "B3N7Alpha", "B3N8Alpha", "B3N9Alpha"]
aoa_max_B3 = [np.max(sum_stats[var]['max']) for var in blade3_chans_aoa]
aoa_mean_B3 = [np.mean(sum_stats[var]['mean']) for var in blade3_chans_aoa]
aoa_std_B3 = [np.mean(sum_stats[var]['std']) for var in blade3_chans_aoa]
spline_aoa_max = PchipInterpolator(self.R_out, np.max([aoa_max_B1, aoa_max_B2, aoa_max_B3], axis=0))
spline_aoa_std = PchipInterpolator(self.R_out, np.mean([aoa_max_B1, aoa_std_B2, aoa_std_B3], axis=0))
spline_aoa_mean = PchipInterpolator(self.R_out, np.mean([aoa_mean_B1, aoa_mean_B2, aoa_mean_B3], axis=0))
else:
raise Exception('The calculations only support 2 or 3 bladed rotors')
outputs['max_aoa'] = spline_aoa_max(r)
outputs['std_aoa'] = spline_aoa_std(r)
outputs['mean_aoa'] = spline_aoa_mean(r)

if self.FASTpref['dlc_settings']['run_blade_fatigue']:

# determine which dlc will be used for fatigue calculations, checks for dlc 1.2, then dlc 1.1
Expand Down
13 changes: 8 additions & 5 deletions weis/glue_code/glue_code.py
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Original file line number Diff line number Diff line change
Expand Up @@ -81,6 +81,7 @@ def setup(self):
self.add_subsystem('freq_tower', TowerSE(modeling_options=modeling_options))
self.add_subsystem('sse_tune', ServoSE_ROSCO(modeling_options = modeling_options)) # Aero analysis
self.add_subsystem('aeroelastic', FASTLoadCases(modeling_options = modeling_options, opt_options = opt_options))
self.add_subsystem('stall_check_of', NoStallConstraint(modeling_options = modeling_options))

self.add_subsystem('rlds', RotorLoadsDeflStrainsWEIS(modeling_options = modeling_options, opt_options = opt_options, freq_run=False))

Expand Down Expand Up @@ -255,15 +256,17 @@ def setup(self):
self.connect('configuration.turb_class', 'sse.gust.turbulence_class')

# Connections to the stall check
self.connect('blade.outer_shape_bem.s', 'stall_check.s')
self.connect('airfoils.aoa', 'stall_check.airfoils_aoa')
self.connect('xf.cl_interp_flaps', 'stall_check.airfoils_cl')
self.connect('xf.cd_interp_flaps', 'stall_check.airfoils_cd')
self.connect('xf.cm_interp_flaps', 'stall_check.airfoils_cm')
self.connect('blade.outer_shape_bem.s', ['stall_check.s', 'stall_check_of.s'])
self.connect('airfoils.aoa', ['stall_check.airfoils_aoa', 'stall_check_of.airfoils_aoa'])
self.connect('xf.cl_interp_flaps', ['stall_check.airfoils_cl', 'stall_check_of.airfoils_cl'])
self.connect('xf.cd_interp_flaps', ['stall_check.airfoils_cd', 'stall_check_of.airfoils_cd'])
self.connect('xf.cm_interp_flaps', ['stall_check.airfoils_cm', 'stall_check_of.airfoils_cm'])
if modeling_options['Analysis_Flags']['ServoSE']:
self.connect('sse.powercurve.aoa_regII', 'stall_check.aoa_along_span')
else:
self.connect('ccblade.alpha', 'stall_check.aoa_along_span')
if modeling_options['Analysis_Flags']['OpenFAST']:
self.connect('aeroelastic.max_aoa', 'stall_check_of.aoa_along_span')

if modeling_options['Analysis_Flags']['OpenFAST'] and modeling_options['Analysis_Flags']['ServoSE']:
self.connect('sse.powercurve.rated_V', ['sse_tune.tune_rosco.v_rated'])
Expand Down

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