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Added tutorial files for pre-mixed hydrogen combustion
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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: Nijso Beishuizen %
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% Institution: Bosch Thermotechnology %
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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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INTERPOLATION_METHOD= MLP
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FILENAMES_INTERPOLATOR= (MLP_Group1.mlp, MLP_Group2.mlp, MLP_Group3.mlp, MLP_Group4.mlp, MLP_Group5.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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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= NO
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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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SPECIES_INIT=(-0.5749236580085463, 2226.901776784524, 0.01446751783896619, 0)
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MARKER_INLET_SPECIES = (inlet, -0.5749236580085463, 2226.901776784524, 0.01446751783896619, 0)
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MARKER_INLET=(inlet, 300.0, 0.575,1,0,0)
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INC_INLET_TYPE= VELOCITY_INLET
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CFL_REDUCTION_SPECIES= 1.0
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MARKER_ISOTHERMAL=(burner_wall, 300, \
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cylinder_wall, 300)
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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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%__ADJOINT__MARKER_SYM= (sides, mixing_edge)
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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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% MARKER_SPECIES_STRONG_BC = (CHT_INTERFACE_FLUID_VENTURI, CHT_INTERFACE_FLUID_BURNER)
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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= 1000
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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= NO
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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 CUSTOM
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%__ADJOINT__SCREEN_OUTPUT = INNER_ITER RMS_ADJ_VELOCITY-X RMS_ADJ_VELOCITY-Y RMS_ADJ_PRESSURE RMS_ADJ_ProgressVariable RMS_ADJ_EnthalpyTot RMS_ADJ_MixtureFraction
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HISTORY_OUTPUT = RMS_RES CUSTOM
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%__ADJOINT__HISTORY_OUTPUT = RMS_RES
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VOLUME_OUTPUT = SOLUTION RESIDUAL SENSITIVITY LOOKUP TIMESTEP PRIMITIVE SOURCE
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CONV_FIELD = RMS_PRESSURE, RMS_VELOCITY-Z, RMS_VELOCITY-Y, RMS_MixtureFraction
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%__ADJOINT__CONV_FIELD = RMS_ADJ_PRESSURE, RMS_ADJ_VELOCITY-X, RMS_ADJ_VELOCITY-Y, RMS_ADJ_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_ASCII, PARAVIEW_MULTIBLOCK)
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WRT_PERFORMANCE = NO
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READ_BINARY_RESTART=NO
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SCREEN_WRT_FREQ_INNER = 1
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SCREEN_WRT_FREQ_OUTER = 1
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OUTPUT_WRT_FREQ=20

‎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} = 40 Using Progression 1;
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//+
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Transfinite Curve {3, 5} = 40 Using Progression 1;
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//+
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Transfinite Curve {4} = 100 Using Progression 1;
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//+
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Transfinite Curve {2} = 150 Using Progression 1;
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//+
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Transfinite Curve {6} = 400 Using Progression 1;
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//+
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Transfinite Curve {8} = 270 Using Progression 1;
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//+
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Transfinite Curve {9} = 470 Using Progression 1;
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//+
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Transfinite Curve {10} = 150 Using Progression 1;
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Mesh 2;
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Save "H2_burner.su2";

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