example runs glue code w/out OF

WISDEM · Aug 27, 2020 · 16b528f · 16b528f
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diff --git a/examples/rotor_opt/IEA-15-240-RWT.yaml b/examples/rotor_opt/IEA-15-240-RWT.yaml
diff --git a/examples/rotor_opt/analysis_options.yaml b/examples/rotor_opt/analysis_options.yaml
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+general:
+    folder_output: outputs
+    fname_output: refturb_output
+optimization_variables:
+  blade:
+    aero_shape:
+      twist:
+        flag: False  # Flag to optimize the twist
+        inverse: False # Flag to determine twist from the user-defined desired margin to stall (defined in constraints)
+        n_opt: 8     # Number of control points along blade span
+        lower_bound: [0.3490658503988659, 0.08726646259971647, 0.08726646259971647, 0., -0.08726646259971647, -0.08726646259971647, -0.08726646259971647, -0.08726646259971647]          # Lower bounds for the twist in [rad] at the n_opt locations
+        upper_bound: [0.4363323129985824, 0.3490658503988659, 0.3490658503988659, 0.2617993877991494, 0.2617993877991494, 0.17453292519943295, 0.17453292519943295, 0.08726646259971647] # Upper bounds for the twist in [rad] at the n_opt locations
+      chord:
+        flag: False     # Flag to optimize the chord
+        n_opt: 8        # Number of control points along blade span
+        min_gain: 0.2   # Nondimensional lower bound at the n_opt locations
+        max_gain: 2.0   # Nondimensional upper bound at the n_opt locations
+      af_positions:
+        flag: False     # Flag to optimize the airfoil positions
+        af_start: 4     # Index of the first airfoil from blade root that can have the location optimized. First airfoil is number 0. Last airfoil is always locked at blade tip.
+    structure:
+      spar_cap_ss:
+        flag: False     # Flag to optimize the spar cap thickness on the suction side
+        name: Spar_Cap_SS # Name in the yaml of the spar cap laminate on the suction side 
+        n_opt: 8        # Number of control points along blade span
+        min_gain: 0.2   # Nondimensional lower bound at the n_opt locations
+        max_gain: 2.0   # Nondimensional upper bound at the n_opt locations
+      spar_cap_ps:
+        flag: False     # Flag to optimize the spar cap thickness on the pressure side
+        name: Spar_Cap_PS # Name in the yaml of the spar cap laminate on the pressure side 
+        equal_to_suction: True # Flag to impose the spar cap thickness on pressure and suction sides equal
+        n_opt: 8        # Number of control points along blade span
+        min_gain: 0.2   # Nondimensional lower bound at the n_opt locations
+        max_gain: 2.0   # Nondimensional upper bound at the n_opt locations
+      te_ss:
+        flag: False     # Flag to optimize the trailing edge reinforcement thickness on the suction side
+        name: TE_reinforcement # Name in the yaml of the trailing edge reinforcement laminate on the suction side 
+        n_opt: 8        # Number of control points along blade span
+        min_gain: 0.2   # Nondimensional lower bound at the n_opt locations
+        max_gain: 2.0   # Nondimensional upper bound at the n_opt locations
+      te_ps:
+        flag: False     # Flag to optimize the trailing edge reinforcement thickness on the pressure side
+        name: TE_reinforcement # Name in the yaml of the trailing edge reinforcement laminate on the pressure side
+        n_opt: 8        # Number of control points along blade span
+        min_gain: 0.2   # Nondimensional lower bound at the n_opt locations
+        max_gain: 2.0   # Nondimensional upper bound at the n_opt locations
+    dac:
+      te_flap_ext:
+        flag: False
+        min_ext: 0.0
+        max_ext: 0.3
+      te_flap_end:
+        flag: False
+        min_end: 0.3
+        max_end: 1.0
+  control:
+    tsr:
+      flag: False     # Flag to optimize the rotor tip speed ratio
+      min_gain: 0.9   # Nondimensional lower bound
+      max_gain: 1.1   # Nondimensional upper bound
+    servo:
+      pitch_control:
+        flag: False
+        omega_min: 0.1
+        omega_max: 0.7
+        zeta_min: 0.4
+        zeta_max: 1.5
+      torque_control:
+        flag: False
+        omega_min: 0.1
+        omega_max: 0.7
+        zeta_min: 0.4
+        zeta_max: 1.5
+      flap_control:
+        flag: False
+        omega_min: 2.7
+        omega_max: 3.5
+        zeta_min: 0.7
+        zeta_max: 1.3
+
+  tower:
+    outer_diameter:
+      flag: False
+      lower_bound: 3.87
+      upper_bound: 10.0
+    layer_thickness:
+      flag: False
+      lower_bound: 4e-3
+      upper_bound: 2e-1
+
+merit_figure: LCOE  # Merit figure of the optimization problem. The options are 'AEP' - 'LCOE' - 'Cp' - 'blade_mass' - 'blade_tip_deflection'
+
+constraints:
+  blade:
+    strains_spar_cap_ss:
+      flag: False     # Flag to impose constraints on maximum strains (absolute value) in the spar cap on the blade suction side
+      max:  3500.e-6  # Value of maximum strains [-]
+    strains_spar_cap_ps:
+      flag: False     # Flag to impose constraints on maximum strains (absolute value) in the spar cap on the blade pressure side
+      max:  3500.e-6  # Value of maximum strains [-]
+    tip_deflection:
+      flag: False     # Constraint that maximum tip deflection cannot exceed 70% of tower clearance. Only for upwind rotors
+    rail_transport:
+      flag: True
+      8_axle: False
+      4_axle: True
+    stall:
+      flag: False     # Constraint on minimum stall margin
+      margin: 0.05233 # Value of minimum stall margin in [rad]
+    chord:
+      flag: False # Constraint on maximum chord
+      max: 4.75   # Value of maximum chord in [m]
+    frequency:
+      flap_above_3P: False
+      edge_above_3P: False
+      flap_below_3P: False
+      edge_below_3P: False
+    moment_coefficient:
+      flag: False
+      max: 0.15 #0.16333
+      min: 0.13
+    match_cl_cd:
+      flag_cl: False
+      flag_cd: False
+      filename: /path2file.txt
+    match_L_D:
+      flag_L: False
+      flag_D: False
+      filename: /path2file.txt
+  tower:
+    height_constraint:
+      flag: False
+      lower_bound: 1.e-2
+      upper_bound: 1.e-2
+    stress:
+      flag: False
+    global_buckling:
+      flag: False
+    shell_buckling:
+      flag: False
+    constr_d_to_t:
+      flag: False
+    constr_taper:
+      flag: False
+    slope:
+      flag: False
+    frequency_1:
+      flag: False
+      lower_bound: 0.13
+      upper_bound: 0.40
+  control:
+    flap_control:
+      flag: False
+      min: 0.0
+      max: 0.1
+
+driver:
+    tol: 1.e-2            # Optimality tolerance
+    max_major_iter: 10    # Maximum number of major design iterations (SNOPT)
+    max_minor_iter: 100   # Maximum number of minor design iterations (SNOPT)
+    max_iter: 100         # Maximum number of iterations (SLSQP)
+    solver: SLSQP         # Optimization solver. Other options are 'SLSQP' - 'CONMIN'
+    step_size: 1.e-3      # Step size for finite differencing
+    form: central         # Finite differencing mode, either forward or central
+
+recorder:
+    flag: True              # Flag to activate OpenMDAO recorder
+    file_name: log_opt.sql  # Name of OpenMDAO recorder
diff --git a/examples/rotor_opt/modeling_options.yaml b/examples/rotor_opt/modeling_options.yaml
@@ -0,0 +1,120 @@
+general:
+    verbosity: False  # When set to True, the code prints to screen many infos
+
+Analysis_Flags:
+    # Control which WISDEM modules are executed.
+    # (GOAL) If inputs are missing for a module, a warning will be written to the screen and the module disabled.
+    RotorSE:  True
+    DriveSE:  True
+    TowerSE:  True
+    ServoSE:  True
+    BOS:      True
+    OpenFAST: False   # Flag to run aeroelasticse, the wrapper of OpenFAST
+
+yaml:
+    validate: False    # When set to True, the code runs a yam validation package. This checks whether the yams has the right formatting.
+    path2schema: windIO/windIO/turbine/IEAontology_schema.yaml   # Path to the yams schema to run the validation
+
+xfoil:
+    path       : Xfoil/bin/xfoil # Path to xfoil executable. Only used for blades with distributed aerodynamic control devices 
+    run_parallel: True
+
+rotorse:
+    n_aoa: 200        # Number of angles of attack used to define polars
+    n_xy: 200         # Number of angles of coordinate points used to discretize each airfoil
+    n_span: 30        # Number of spanwise stations used to define the blade properties
+
+openfast:
+    analysis_settings:
+        Analysis_Level:     1           # Flag to set the call to OpenFAST. 1 - generate OpenFAST model, 2 - generate and run OpenFAST model
+        update_hub_nacelle: False
+        update_tower:       False
+        generate_af_coords: False
+        debug_level:        2    # Flag to set the debug level, do not change
+    file_management:
+        FAST_ver:          OpenFAST          # Version of OpenFAST, do not change
+        FAST_exe:          ../../local/bin/openfast    # Path to OpenFAST executable
+        FAST_directory:    ../IEA-15-240-RWT/IEA-15-240-RWT-Monopile/"  # Path to folder with the OpenFAST input files
+        FAST_InputFile:    IEA-15-240-RWT-Monopile.fst             # Name of the main OpenFAST input file (.fst)
+        path2dll:          ../../local/lib/libdiscon.dylib     # Path to the the compiled ROSCO controller
+        Turbsim_exe:       ../../local/bin/openfast   # Path to TurbSim executable
+        FAST_namingOut:    Testing_v2         # Name of the OpenFAST output files
+        FAST_runDirectory: temp/Testing_v2             # Path to folder with the OpenFAST output files
+        Simulation_Settings_File: openfast_settings.yaml
+    dlc_settings:
+        run_power_curve:   False
+        run_IEC:           False
+        run_blade_fatigue: False
+        IEC: # Currently supported: 1.1, 1.3, 1.4, 1.5, 5.1, 6.1, 6.3
+            - DLC:   1.1
+              U:     [3., 5., 7., 9., 11., 13., 15., 17., 19., 21., 23., 25.]
+              Seeds: [11, 12, 13]
+            # - DLC:   1.3
+            #   U:     [3., 5., 7., 9., 11., 13., 15., 17., 19., 21., 23., 25.]
+            #   Seeds: [11, 12, 13, 14, 15, 16]
+            # - DLC:   1.4
+            # - DLC:   1.5
+            #   U:     [3., 5., 7., 9., 11., 13., 15., 17., 19., 21., 23., 25.]
+            #   Seeds: [11, 12, 13, 14, 15, 16]
+            # - DLC:   5.1
+            #   Seeds: [11, 12, 13, 14, 15, 16]
+            # - DLC:   6.1
+            #   Seeds: [11, 12, 13, 14, 15, 16]
+            # - DLC:   6.3
+            #   Seeds: [11, 12, 13, 14, 15, 16]
+        Power_Curve:
+            # Note: if running turbulent power curve, can set U:[], and analysis will default to using the IEC - DLC 1.1 results.  This can be used to prevent running redundant turbulent operational cases
+            turbulent_power_curve: True # False: Steady Wind, True: Turbulent Inflow
+            # U:     [3., 5., 7., 9., 11., 13., 15., 17., 19., 21., 23., 25.]
+            # Seeds: [11, 12, 13, 14, 15, 16] # Used only when turbulent_power_curve=True
+            # U:     [3., 9., 11., 15.]
+            # Seeds: [11, 12] # Used only when turbulent_power_curve=True
+            U:     []
+            Seeds: []
+
+
+tower:             # Options of TowerSE module
+  nLC: 1           # Number of design load cases in TowerSE
+  wind: PowerWind  # Wind used in TowerSE
+  gamma_f: 1.35    # Safety factor for fatigue loads in TowerSE
+  gamma_m: 1.3     # Safety factor for material properties in TowerSE
+  gamma_n: 1.0     # Safety factor for ...
+  gamma_b: 1.1     # Safety factor for ...
+  gamma_fatigue: 1.9305  # Safety factor for fatigue loads in TowerSE
+  buckling_length: 30    # Buckling parameter in TowerSE
+  frame3dd:
+    DC: 80.0             # Options of beam solver frame3dd
+    shear: True
+    geom: True
+    dx: 5.0
+    nM: 2
+    Mmethod: 1
+    lump: 0
+    tol: 1e-9
+    shift: 0.0
+    add_gravity: True
+
+servose:
+    n_pc: 20                        # Number of wind speeds to compute the power curve
+    n_pc_spline: 200                # Number of wind speeds to spline the power curve 
+    n_pitch_perf_surfaces: 20       # Number of pitch angles to determine the Cp-Ct-Cq-surfaces
+    min_pitch_perf_surfaces: -5.    # Min pitch angle of the Cp-Ct-Cq-surfaces
+    max_pitch_perf_surfaces: 30.    # Max pitch angle of the Cp-Ct-Cq-surfaces
+    n_tsr_perf_surfaces: 20         # Number of tsr values to determine the Cp-Ct-Cq-surfaces
+    min_tsr_perf_surfaces: 2.       # Min TSR of the Cp-Ct-Cq-surfaces
+    max_tsr_perf_surfaces: 12.      # Max TSR of the Cp-Ct-Cq-surfaces
+    n_U_perf_surfaces: 1            # Number of wind speeds to determine the Cp-Ct-Cq-surfaces
+    regulation_reg_III: False       # Flag to derive the regulation trajectory in region III in terms of pitch and TSR
+    LoggingLevel: 1                 # {0: write no debug files, 1: write standard output .dbg-file, 2: write standard output .dbg-file and complete avrSWAP-array .dbg2-file
+    F_LPFType: 2                    # {1: first-order low-pass filter, 2: second-order low-pass filter}, [rad/s] (currently filters generator speed and pitch control signals)
+    F_NotchType: 0                  # Notch filter on generator speed and/or tower fore-aft motion (for floating) {0: disable, 1: generator speed, 2: tower-top fore-aft motion, 3: generator speed and tower-top fore-aft motion}
+    IPC_ControlMode: 0              # Turn Individual Pitch Control (IPC) for fatigue load reductions (pitch contribution) {0: off, 1: 1P reductions, 2: 1P+2P reductions}
+    VS_ControlMode: 2               # Generator torque control mode in above rated conditions {0: constant torque, 1: constant power, 2: TSR tracking PI control}
+    PC_ControlMode: 1               # Blade pitch control mode {0: No pitch, fix to fine pitch, 1: active PI blade pitch control}
+    Y_ControlMode: 0                # Yaw control mode {0: no yaw control, 1: yaw rate control, 2: yaw-by-IPC}
+    SS_Mode: 1                      # Setpoint Smoother mode {0: no setpoint smoothing, 1: introduce setpoint smoothing}
+    WE_Mode: 0                      # Wind speed estimator mode {0: One-second low pass filtered hub height wind speed, 1: Immersion and Invariance Estimator (Ortega et al.)}
+    PS_Mode: 0                      # Pitch saturation mode {0: no pitch saturation, 1: peak shaving, 2: Cp-maximizing pitch saturation, 3: peak shaving and Cp-maximizing pitch saturation}
+    SD_Mode: 0                      # Shutdown mode {0: no shutdown procedure, 1: pitch to max pitch at shutdown}
+    Fl_Mode: 0                      # Floating specific feedback mode {0: no nacelle velocity feedback, 1: nacelle velocity feedback}
+    Flp_Mode: 0                     # Flap control mode {0: no flap control, 1: steady state flap angle, 2: Proportional flap control}
diff --git a/examples/rotor_opt/openfast_settings.yaml b/examples/rotor_opt/openfast_settings.yaml
@@ -0,0 +1,26 @@
+# Variables are case sensitive.
+[Fst, TStart]          : 120.
+[Fst, TMax]            : 720.
+# [Fst, TStart]          : 0.
+# [Fst, TMax]            : 40.
+[Fst, OutFileFmt]      : 2
+[Fst, DT]              : 0.025
+
+[ServoDyn, DLL_DT]     : 0.025
+
+[AeroDyn15, TwrPotent] : 0
+[AeroDyn15, TwrShadow] : False
+[AeroDyn15, TwrAero]   : False
+
+[Fst, CompElast]       : 1
+[Fst, CompSub]         : 0
+[ElastoDyn, PtfmSgDOF] : False
+[ElastoDyn, PtfmSwDOF] : False
+[ElastoDyn, PtfmHvDOF] : False
+[ElastoDyn, PtfmRDOF]  : False
+[ElastoDyn, PtfmPDOF]  : False
+[ElastoDyn, PtfmYDOF]  : False
+
+[ElastoDyn, FlapDOF1]  : True
+[ElastoDyn, FlapDOF2]  : True
+[ElastoDyn, EdgeDOF]   : True