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Merge pull request #55 from su2code/develop
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Develop
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@pcarruscag
pcarruscag authored Sep 28, 2024
2 parents 6d79df7 + 6f08542 commit e8d5cdb
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144 changes: 144 additions & 0 deletions 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)
97 changes: 97 additions & 0 deletions 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};
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