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Merge pull request #55 from su2code/develop
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‎incompressible_flow/Inc_Combustion/1__premixed_hydrogen/H2_burner.cfg

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% SU2 configuration file %
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% Case description: Laminar premixed flame stabilized on isothermal burner %
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% Author: Evert Bunschoten %
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% Institution: Delft University of Technology %
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% Date: 16/06/2023 %
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% File Version 7.5.1 "Blackbird" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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SOLVER = INC_NAVIER_STOKES
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KIND_TURB_MODEL= NONE
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%
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% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
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%
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INC_DENSITY_MODEL= VARIABLE
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INC_ENERGY_EQUATION = YES
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INC_DENSITY_INIT= 1.00
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INC_VELOCITY_INIT= (0.575, 0.0, 0.0)
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INC_TEMPERATURE_INIT= 300.0
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INC_NONDIM= DIMENSIONAL
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%
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CUSTOM_OUTPUTS= 'outlet_YNO : AreaAvg{SPECIES[3]}[outlet];\
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outlet_T : AreaAvg{TEMPERATURE}[outlet];\
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inlet_P : AreaAvg{PRESSURE}[inlet];'
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OBJECTIVE_FUNCTION= CUSTOM_OBJFUNC
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CUSTOM_OBJFUNC= outlet_YNO
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% -------------------- FLUID MODEL --------------------------------------- %
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%
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FLUID_MODEL= FLUID_FLAMELET
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% List the MLP files describing the respective architectures.
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INTERPOLATION_METHOD= MLP
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FILENAMES_INTERPOLATOR= (MLP_TD1.mlp, MLP_TD2.mlp, MLP_PD.mlp, MLP_SPV.mlp, MLP_PNO.mlp, MLP_null.mlp)
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% FGM controlling variable names (must include mixture fraction for partial
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% premixed cases)
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PREFERENTIAL_DIFFUSION=YES
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CONTROLLING_VARIABLE_NAMES=(ProgressVariable,EnthalpyTot,MixtureFraction)
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CONTROLLING_VARIABLE_SOURCE_NAMES=(ProdRateTot_PV,NULL,NULL)
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USER_SCALAR_NAMES= (Y_NO)
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USER_SOURCE_NAMES = ( \
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Y_dot_net-NO, NULL \
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)
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LOOKUP_NAMES=(Heat_Release)
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% -------------------- SCALAR TRANSPORT ---------------------------------------%
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%
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KIND_SCALAR_MODEL= FLAMELET
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DIFFUSIVITY_MODEL= FLAMELET
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VISCOSITY_MODEL= FLAMELET
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CONDUCTIVITY_MODEL= FLAMELET
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FLAME_INIT_METHOD= SPARK
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SPARK_INIT= (0.001, 0.0004, 0.00, 1e-4, 100, 5)
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SPARK_REACTION_RATES=(1000, 0, 0)
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CONV_NUM_METHOD_SPECIES= BOUNDED_SCALAR
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MUSCL_SPECIES= YES
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SLOPE_LIMITER_SPECIES= NONE
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TIME_DISCRE_SPECIES= EULER_IMPLICIT
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% SCALAR CLIPPING
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SPECIES_CLIPPING= YES
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SPECIES_CLIPPING_MIN= -1.5064702033996582e+00 -3.4190245000000000e+06 +5.0012799911201000e-03 0
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SPECIES_CLIPPING_MAX= +4.6642374992370605e-01 +2.1569957500000000e+06 +1.4977467060089111e-01 1
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%
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% Inlet and initial condition corresponding to mixture at T=300K, eq ratio 0.5
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SPECIES_INIT=(-0.575, 2.227e3, 1.447e-2, 0)
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MARKER_INLET_SPECIES = (inlet, -0.575, 2.227e3, 1.447e-2, 0)
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INC_INLET_TYPE= VELOCITY_INLET
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MARKER_INLET=(inlet, 300.0, 0.575,1,0,0)
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CFL_REDUCTION_SPECIES= 1.0
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MARKER_ISOTHERMAL=(burner_wall, 350, \
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cylinder_wall, 400)
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MARKER_SPECIES_STRONG_BC=(burner_wall,cylinder_wall)
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MARKER_INTERNAL=(fluid)
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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REF_LENGTH= 1.0
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REF_AREA= 1.0
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%
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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MARKER_SYM= (sides)
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INC_OUTLET_TYPE= PRESSURE_OUTLET
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INC_INLET_DAMPING = 0.05
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INC_OUTLET_DAMPING = 0.05
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MARKER_OUTLET= (outlet, 0.0)
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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CFL_NUMBER= 150
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CFL_ADAPT= NO
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ITER= 5
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%
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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LINEAR_SOLVER= FGMRES
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LINEAR_SOLVER_PREC= LU_SGS
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LINEAR_SOLVER_ERROR= 1E-04
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LINEAR_SOLVER_ITER= 5
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%
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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%
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MGLEVEL= 0
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%
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= FDS
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MUSCL_FLOW= YES
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SLOPE_LIMITER_FLOW = NONE
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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%
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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CONV_RESIDUAL_MINVAL= -15
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CONV_STARTITER= 10
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CONV_CAUCHY_ELEMS= 100
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CONV_CAUCHY_EPS= 1E-6
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SCREEN_OUTPUT = INNER_ITER RMS_VELOCITY-X RMS_PRESSURE RMS_ProgressVariable RMS_EnthalpyTot RMS_MixtureFraction
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HISTORY_OUTPUT = RMS_RES
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VOLUME_OUTPUT = SOLUTION
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CONV_FIELD = RMS_PRESSURE, RMS_VELOCITY-Z, RMS_VELOCITY-Y, RMS_MixtureFraction
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WRT_ZONE_HIST= YES
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%
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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RESTART_SOL=YES
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OUTPUT_PRECISION= 16
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TABULAR_FORMAT = CSV
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MESH_FILENAME=H2_burner.su2
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OUTPUT_FILES=(RESTART, PARAVIEW_MULTIBLOCK)

‎incompressible_flow/Inc_Combustion/1__premixed_hydrogen/H2_burner.geo

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domain_width=0.0008;
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hex_center=0.002;
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hex_radius=0.0003;
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//+
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Point(1) = {-0.003, 0, 0, 1.0};
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//+
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Point(2) = {-0.003, domain_width, 0, 1.0};
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//+
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Point(3) = {-0.001, domain_width, 0, 1.0};
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//+
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Point(4) = {-0.001, 0.5*domain_width, 0, 1.0};
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//+
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Point(5) = {-0.00, 0.5*domain_width, 0, 1.0};
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//+
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Point(6) = {-0.00, domain_width, 0, 1.0};
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//+
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Point(7) = {0.005, domain_width, 0, 1.0};
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//+
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Point(8) = {0.005, 0.000, 0, 1.0};
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//+
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Point(9) = {hex_center, 0.000, 0, 1.0};
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//+
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Point(10) = {hex_center+hex_radius, 0.000, 0, 1.0};
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//+
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Point(11) = {hex_center-hex_radius, 0.000, 0, 1.0};
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//+
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Line(1) = {2, 1};
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//+
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Line(2) = {2, 3};
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//+
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Line(3) = {3, 4};
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//+
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Line(4) = {4, 5};
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//+
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Line(5) = {5, 6};
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//+
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Line(6) = {6, 7};
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//+
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Line(7) = {7, 8};
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//+
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Line(8) = {10, 8};
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//+
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Line(9) = {1, 11};
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//+
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Circle(10) = {10, 9, 11};
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//+
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Curve Loop(1) = {1, 9, -10, 8, -7, -6, -5, -4, -3, -2};
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//+
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Plane Surface(1) = {1};
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//+
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//Physical Curve("inlet", 11) = {1};
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//+
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//Physical Curve("outlet", 12) = {7};
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//+
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//Physical Curve("burner_wall", 13) = {3, 4, 5};
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//+
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//Physical Curve("cylinder_wall", 14) = {10};
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//+
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//Physical Curve("sides", 15) = {2, 9, 6, 8};
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//+
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//Physical Surface("fluid", 16) = {1};
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//+
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Transfinite Curve {1, 7} = 30 Using Progression 1;
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//+
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Transfinite Curve {3, 5} = 30 Using Progression 1;
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//+
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Transfinite Curve {4} = 80 Using Progression 1;
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//+
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Transfinite Curve {2} = 100 Using Progression 1;
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//+
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Transfinite Curve {6} = 300 Using Progression 1;
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//+
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Transfinite Curve {8} = 200 Using Progression 1;
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//+
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Transfinite Curve {9} = 350 Using Progression 1;
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//+
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Transfinite Curve {10} = 100 Using Progression 1;
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//Mesh 2;
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//Save "H2_burner.su2";//+
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Extrude {{1, 0, 0}, {0, -0.001, 0}, Pi/8} {
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Surface{1}; Layers{10}; Recombine;
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}
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//+
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Physical Surface("inlet", 63) = {25};
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//+
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Physical Surface("outlet", 64) = {41};
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//+
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Physical Surface("sides", 65) = {62, 29, 61, 1, 45, 37};
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//+
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Physical Surface("burner_wall", 66) = {57, 53, 49};
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//+
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Physical Surface("cylinder_wall", 67) = {33};
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//+
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Physical Volume("fluid", 68) = {1};

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