Develop

incompressible_flow/Inc_Combustion/1__premixed_hydrogen/H2_burner.cfg

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

incompressible_flow/Inc_Combustion/1__premixed_hydrogen/H2_burner.geo

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