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TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg
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| %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
| % % | ||
| % SU2 configuration file % | ||
| % Case description: AACHEN turbine 3D % | ||
| % Author: S. Vitale, A. Cappiello % | ||
| % Institution: Delft University of Technology % | ||
| % Date: Oct 20th, 2023 % | ||
| % File Version 8.0 develop % | ||
| % % | ||
| %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
| % | ||
| % | ||
| % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% | ||
| % | ||
| % Physical governing equations (EULER, NAVIER_STOKES, | ||
| % WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY, | ||
| % POISSON_EQUATION) | ||
| SOLVER= RANS | ||
| % | ||
| % Specify turbulent model (NONE, SA, SST) | ||
| KIND_TURB_MODEL= SA | ||
| % | ||
| % Mathematical problem (DIRECT, ADJOINT, LINEARIZED) | ||
| MATH_PROBLEM= DIRECT | ||
| % | ||
| % Restart solution (NO, YES) | ||
| RESTART_SOL= YES | ||
| % | ||
| MULTIZONE= YES | ||
| % | ||
| % List of config files for zone-specific options | ||
| CONFIG_LIST=(stator1.cfg, rotor.cfg, stator2.cfg) | ||
| % | ||
| % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% | ||
| % | ||
| % Mach number (non-dimensional, based on the free-stream values) | ||
| MACH_NUMBER= 0.05 | ||
| % | ||
| % Angle of attack (degrees, only for compressible flows) | ||
| AOA= 0.0 | ||
| % | ||
| % Free-stream pressure (101325.0 N/m^2 by default, only Euler flows) | ||
| FREESTREAM_PRESSURE= 140000.0 | ||
| % | ||
| % Free-stream temperature (273.15 K by default) | ||
| FREESTREAM_TEMPERATURE= 300.0 | ||
| % | ||
| % Free-stream temperature (1.2886 Kg/m3 by default) | ||
| FREESTREAM_DENSITY= 1.7418 | ||
| % | ||
| % Free-stream option to choose if you want to use Density (DENSITY_FS) or Temperature TEMPERATURE_FS) to initialize the solution | ||
| FREESTREAM_OPTION= TEMPERATURE_FS | ||
| % | ||
| % Free-stream Turbulence Intensity | ||
| FREESTREAM_TURBULENCEINTENSITY = 0.025 | ||
| % | ||
| % Free-stream Turbulent to Laminar viscosity ratio | ||
| FREESTREAM_TURB2LAMVISCRATIO = 100.0 | ||
| % | ||
| % | ||
| %Init option to choose between Reynolds (default) or thermodynamics quantities for initializing the solution (REYNOLDS, TD_CONDITIONS) | ||
| INIT_OPTION= TD_CONDITIONS | ||
| % | ||
| % ---------------------- REFERENCE VALUE DEFINITION ---------------------------% | ||
| % | ||
| % Reference origin for moment computation | ||
| REF_ORIGIN_MOMENT_X = 0.00 | ||
| REF_ORIGIN_MOMENT_Y = 0.00 | ||
| REF_ORIGIN_MOMENT_Z = 0.00 | ||
| % | ||
| % Reference area for force coefficients (0 implies automatic calculation) | ||
| REF_AREA= 1.0 | ||
| % | ||
| % Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, | ||
| % FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) | ||
| REF_DIMENSIONALIZATION= DIMENSIONAL | ||
| % | ||
| % | ||
| % ------------------------------ EQUATION OF STATE ----------------------------% | ||
| % | ||
| % Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS) | ||
| FLUID_MODEL= IDEAL_GAS | ||
| % | ||
| % Ratio of specific heats (1.4 default and the value is hardcoded for the model STANDARD_AIR) | ||
| GAMMA_VALUE= 1.4 | ||
| % | ||
| % Specific gas constant (287.058 J/kg*K default and this value is hardcoded for the model STANDARD_AIR) | ||
| GAS_CONSTANT= 287.058 | ||
| % | ||
| % Critical Temperature (273.15 K by default) | ||
| CRITICAL_TEMPERATURE= 273.15 | ||
| % | ||
| % Critical Pressure (101325.0 N/m^2 by default) | ||
| CRITICAL_PRESSURE= 101325.0 | ||
| % | ||
| % Acentri factor (0.035 (air)) | ||
| ACENTRIC_FACTOR= 0.035 | ||
| % | ||
| % --------------------------- VISCOSITY MODEL ---------------------------------% | ||
| % | ||
| % Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY). | ||
| VISCOSITY_MODEL= SUTHERLAND | ||
| % | ||
| % Molecular Viscosity that would be constant (1.716E-5 by default) | ||
| MU_CONSTANT= 1.716E-5 | ||
| % | ||
| % Sutherland Viscosity Ref (1.716E-5 default value for AIR SI) | ||
| MU_REF= 1.716E-5 | ||
| % | ||
| % Sutherland Temperature Ref (273.15 K default value for AIR SI) | ||
| MU_T_REF= 273.15 | ||
| % | ||
| % Sutherland constant (110.4 default value for AIR SI) | ||
| SUTHERLAND_CONSTANT= 110.4 | ||
| % | ||
| % --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------% | ||
| % | ||
| % Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL). | ||
| CONDUCTIVITY_MODEL= CONSTANT_PRANDTL | ||
| % | ||
| % -------------------- BOUNDARY CONDITION DEFINITION --------------------------% | ||
| % | ||
| %Navier-Stokes wall boundary marker(s) (NONE = no marker) | ||
| MARKER_HEATFLUX= (BLADE1, 0.0, BLADE2, 0.0, BLADE3, 0.0, HUB1, 0.0, SHROUD1, 0.0, HUB2, 0.0, SHROUD2, 0.0, HUB3, 0.0, SHROUD3, 0.0) | ||
| % | ||
| % Periodic boundary marker(s) (NONE = no marker) | ||
| % Format: ( periodic marker, donor marker, rot_cen_x, rot_cen_y, rot_cen_z, rot_angle_x-axis, rot_angle_y-axis, rot_angle_z-axis, translation_x, translation_y, translation_z) | ||
| MARKER_PERIODIC= (PER1_STATOR1, PER2_STATOR1, 0.0, 0.0, 0.0, 0.0, 0.0, 8.7804878, 0.0, 0.0, 0.0, PER1_ROTOR, PER2_ROTOR, 0.0, 0.0, 0.0, 0.0, 0.0, 8.7804878, 0.0, 0.0, 0.0, PER1_STATOR2, PER2_STATOR2, 0.0, 0.0, 0.0, 0.0, 0.0, 8.7804878, 0.0, 0.0, 0.0) | ||
| % | ||
| % | ||
| %-------- INFLOW/OUTFLOW BOUNDARY CONDITION SPECIFIC FOR TURBOMACHINERY --------% | ||
| % | ||
| % Inflow and Outflow markers must be specified, for each blade (zone), following the natural groth of the machine (i.e, from the first blade to the last) | ||
| MARKER_TURBOMACHINERY= (INFLOW_STATOR1, OUTFLOW_STATOR1, INFLOW_ROTOR, OUTFLOW_ROTOR, INFLOW_STATOR2, OUTFLOW_STATOR2) | ||
| MARKER_ANALYZE = (INFLOW_STATOR1, OUTFLOW_STATOR2) | ||
| % Mixing-plane interface markers must be specified to activate the transfer of information between zones | ||
| MARKER_MIXINGPLANE_INTERFACE= (OUTFLOW_STATOR1, INFLOW_ROTOR, OUTFLOW_ROTOR, INFLOW_STATOR2) | ||
| % Mixing-plane interface markers must be specified to activate the transfer of information between zones | ||
| MARKER_ZONE_INTERFACE= (OUTFLOW_STATOR1, INFLOW_ROTOR, OUTFLOW_ROTOR, INFLOW_STATOR2) | ||
| % | ||
| % Non reflecting boundary condition for inflow, outfolw and mixing-plane | ||
| % Format inlet: ( marker, TOTAL_CONDITIONS_PT, Total Pressure , Total Temperature, Flow dir-norm, Flow dir-tang, Flow dir-span, under-relax-avg, under-relax-fourier) | ||
| % Format outlet: ( marker, STATIC_PRESSURE, Static Pressure value, -, -, -, -, under-relax-avg, under-relax-fourier) | ||
| % Format mixing-plane in and out: ( marker, MIXING_IN or MIXING_OUT, -, -, -, -, -, -, under-relax-avg, under-relax-fourier) | ||
| MARKER_GILES= (INFLOW_STATOR1, TOTAL_CONDITIONS_PT, 158245.38, 308.26, 1.0, 0.0, 0.0, 0.3, 0.0, OUTFLOW_STATOR1, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, INFLOW_ROTOR, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, OUTFLOW_ROTOR, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, INFLOW_STATOR2, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, OUTFLOW_STATOR2, STATIC_PRESSURE_1D, 110050.96, 0.0, 0.0, 0.0, 0.0 , 1.0, 0.0) | ||
| SPATIAL_FOURIER= NO | ||
| % | ||
| % This option insert an extra under relaxation factor for the Giles BC at the hub and shroud levels | ||
| GILES_EXTRA_RELAXFACTOR= (0.05, 0.05) | ||
| % | ||
| %---------------------------- TURBOMACHINERY SIMULATION -----------------------------% | ||
| % | ||
| % Format: (marker) | ||
| % If the ROTATING_FRAME option is activated, this option force | ||
| % the velocity on the boundaries specified to 0.0 | ||
| MARKER_SHROUD= (SHROUD1, SHROUD2, SHROUD3) | ||
| % | ||
| % Specify kind of architecture (AXIAL, CENTRIPETAL, CENTRIFUGAL, CENTRIPETAL_AXIAL) | ||
| TURBOMACHINERY_KIND= AXIAL AXIAL AXIAL | ||
| % | ||
| % Uncomment to work with new_turbo_outputs | ||
| %TURBO_PERF_KIND= (TURBINE, TURBINE, TURBINE) | ||
| % | ||
| % Specify kind of interpolation for the mixing-plane (LINEAR_INTERPOLATION, NEAREST_SPAN, MATCHING) | ||
| MIXINGPLANE_INTERFACE_KIND= LINEAR_INTERPOLATION | ||
| % | ||
| % Specify option for turbulent mixing-plane (YES, NO) default NO | ||
| TURBULENT_MIXINGPLANE= YES | ||
| % | ||
| % Specify ramp option for Outlet pressure (YES, NO) default NO | ||
| RAMP_OUTLET_PRESSURE= NO | ||
| % | ||
| % Parameters of the outlet pressure ramp (starting outlet pressure, updating-iteration-frequency, total number of iteration for the ramp) | ||
| RAMP_OUTLET_PRESSURE_COEFF= (140000.0, 10.0, 2000) | ||
| % | ||
| % Specify Kind of average process for linearizing the Navier-Stokes equation at inflow and outflow BC included mixing-plane | ||
| % (ALGEBRAIC, AREA, MASSSFLUX, MIXEDOUT) default AREA | ||
| AVERAGE_PROCESS_KIND= MIXEDOUT | ||
| % | ||
| % Specify Kind of average process for computing turbomachienry performance parameters | ||
| % (ALGEBRAIC, AREA, MASSSFLUX, MIXEDOUT) default AREA | ||
| PERFORMANCE_AVERAGE_PROCESS_KIND= MIXEDOUT | ||
| % | ||
| %Parameters of the Newton method for the MIXEDOUT average algorithm (under relaxation factor, tollerance, max number of iterations) | ||
| MIXEDOUT_COEFF= (1.0, 1.0E-05, 15) | ||
| % | ||
| % Limit of Mach number below which the mixedout algorithm is substituted with a AREA average algorithm | ||
| AVERAGE_MACH_LIMIT= 0.03 | ||
| % | ||
| % | ||
| % ------------------------ SURFACES IDENTIFICATION ----------------------------% | ||
| % | ||
| % Marker(s) of the surface in the surface flow solution file | ||
| MARKER_PLOTTING= (BLADE1, BLADE2, BLADE3) | ||
| MARKER_MONITORING= (BLADE1, BLADE2, BLADE3) | ||
| % | ||
| % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% | ||
| % | ||
| % Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) | ||
| NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES | ||
| % | ||
| % Courant-Friedrichs-Lewy condition of the finest grid | ||
| CFL_NUMBER= 10 | ||
| % | ||
| % Adaptive CFL number (NO, YES) | ||
| CFL_ADAPT= NO | ||
| % | ||
| % Parameters of the adaptive CFL number (factor down, factor up, CFL min value, CFL max value ) | ||
| CFL_ADAPT_PARAM= ( 1.3, 1.2, 1.0, 10.0) | ||
| % | ||
| % | ||
| % ------------------------ LINEAR SOLVER DEFINITION ---------------------------% | ||
| % | ||
| % Linear solver or smoother for implicit formulations (BCGSTAB, FGMRES, SMOOTHER_JACOBI, SMOOTHER_ILU0, SMOOTHER_LUSGS, SMOOTHER_LINELET) | ||
| LINEAR_SOLVER= FGMRES | ||
| % | ||
| % Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI) | ||
| LINEAR_SOLVER_PREC= LU_SGS | ||
| % | ||
| % Min error of the linear solver for the implicit formulation | ||
| LINEAR_SOLVER_ERROR= 1E-4 | ||
| % | ||
| % Max number of iterations of the linear solver for the implicit formulation | ||
| LINEAR_SOLVER_ITER= 15 | ||
| % | ||
| % ----------------------- SLOPE LIMITER DEFINITION ----------------------------% | ||
| % | ||
| % Coefficient for the limiter | ||
| VENKAT_LIMITER_COEFF= 0.01 | ||
| % | ||
| % Freeze the value of the limiter after a number of iterations | ||
| LIMITER_ITER= 999999 | ||
| % | ||
| % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% | ||
| % | ||
| % Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, | ||
| % TURKEL_PREC, MSW) | ||
| CONV_NUM_METHOD_FLOW= ROE | ||
| ENTROPY_FIX_COEFF= 0.001 | ||
| % | ||
| JST_SENSOR_COEFF= ( 0.5, 0.25 ) | ||
| % Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER) | ||
| MUSCL_FLOW= NO | ||
| % | ||
| % Slope limiter (VENKATAKRISHNAN, VAN_ALBADA) | ||
| SLOPE_LIMITER_FLOW= VENKATAKRISHNAN | ||
| % | ||
| % | ||
| % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) | ||
| TIME_DISCRE_FLOW= EULER_IMPLICIT | ||
| % | ||
| % -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------% | ||
| % | ||
| % Convective numerical method (SCALAR_UPWIND) | ||
| CONV_NUM_METHOD_TURB= SCALAR_UPWIND | ||
| % | ||
| % Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER) | ||
| MUSCL_TURB= NO | ||
| % | ||
| % Slope limiter (VENKATAKRISHNAN, MINMOD) | ||
| SLOPE_LIMITER_TURB= VENKATAKRISHNAN | ||
| % | ||
| % Time discretization (EULER_IMPLICIT) | ||
| TIME_DISCRE_TURB= EULER_IMPLICIT | ||
| % | ||
| % Reduction factor of the CFL coefficient in the turbulence problem | ||
| CFL_REDUCTION_TURB= 0.1 | ||
| % | ||
| % ----------------------- DESIGN VARIABLE PARAMETERS --------------------------% | ||
| % | ||
| % Kind of deformation (NO_DEFORMATION, TRANSLATION, ROTATION, SCALE, | ||
| % FFD_SETTING, FFD_NACELLE | ||
| % FFD_CONTROL_POINT, FFD_CAMBER, FFD_THICKNESS, FFD_TWIST | ||
| % FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D, FFD_TWIST_2D, | ||
| % HICKS_HENNE, SURFACE_BUMP) | ||
| DV_KIND= NO_DEFORMATION | ||
| % | ||
| % Marker of the surface in which we are going apply the shape deformation | ||
| DV_MARKER= (BLADE1, BLADE2, BLADE3) | ||
| % | ||
| % Parameters of the shape deformation | ||
| DV_PARAM= ( 1, 0.5) | ||
| % | ||
| % Value of the shape deformation | ||
| DV_VALUE= 0.01 | ||
| % | ||
| % --------------------------- CONVERGENCE PARAMETERS --------------------------% | ||
| % | ||
| % Number of total iterations | ||
| OUTER_ITER=5 | ||
| % | ||
| % Convergence criteria (CAUCHY, RESIDUAL) | ||
| CONV_FIELD=RMS_ENERGY[0] | ||
| % | ||
| % Min value of the residual (log10 of the residual) | ||
| CONV_RESIDUAL_MINVAL= -12 | ||
| % | ||
| % Start convergence criteria at iteration number | ||
| CONV_STARTITER= 10 | ||
| % | ||
| % Number of elements to apply the criteria | ||
| CONV_CAUCHY_ELEMS= 999 | ||
| % | ||
| % Epsilon to control the series convergence | ||
| CONV_CAUCHY_EPS= 1E-6 | ||
| % | ||
| % Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY, | ||
| % SENS_MACH, DELTA_LIFT, DELTA_DRAG) | ||
| %CAUCHY_FUNC_FLOW= DRAG | ||
| % | ||
| % Screen output fields (use 'SU2_CFD -d <config_file>' to view list of available fields) | ||
| SCREEN_OUTPUT= (OUTER_ITER, RMS_DENSITY[0], RMS_DENSITY[1], RMS_DENSITY[2], RMS_MOMENTUM-X[0], RMS_MOMENTUM-Y[0], RMS_ENERGY[0]) | ||
| % | ||
| % History output groups (use 'SU2_CFD -d <config_file>' to view list of available fields) | ||
| HISTORY_OUTPUT= (ITER, RMS_RES, TURBO_PERF) | ||
| % | ||
| % Volume output fields/groups (use 'SU2_CFD -d <config_file>' to view list of available fields) | ||
| VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, TURBOMACHINERY, RESIDUAL, LIMITER, VORTEX_IDENTIFICATION) | ||
| % | ||
| OUTPUT_FILES= (TECPLOT_ASCII, SURFACE_TECPLOT_ASCII, RESTART) | ||
| % | ||
| % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% | ||
| % | ||
| % Mesh input file | ||
| MESH_FILENAME= aachen_turbine_3D_41blade.su2 | ||
| % | ||
| % Mesh input file format (SU2, CGNS, NETCDF_ASCII) | ||
| MESH_FORMAT= SU2 | ||
| % | ||
| % Mesh output file | ||
| MESH_OUT_FILENAME= aachen_turbine_3D_41blade.su2 | ||
| % | ||
| % Restart flow input file | ||
| SOLUTION_FILENAME= restart_flow.dat | ||
| % | ||
| % Restart adjoint input file | ||
| SOLUTION_ADJ_FILENAME= restart_adj.dat | ||
| % | ||
| % Output file format (PARAVIEW, TECPLOT, STL) | ||
| TABULAR_FORMAT= TECPLOT | ||
| % | ||
| % Output file convergence history (w/o extension) | ||
| CONV_FILENAME= history | ||
| % | ||
| % Output file restart flow | ||
| RESTART_FILENAME= restart_flow.dat | ||
| % | ||
| % Output file restart adjoint | ||
| RESTART_ADJ_FILENAME= restart_adj.dat | ||
| % | ||
| % Output file flow (w/o extension) variables | ||
| VOLUME_FILENAME= flow | ||
| % | ||
| % Output file adjoint (w/o extension) variables | ||
| VOLUME_ADJ_FILENAME= adjoint | ||
| % | ||
| % Output objective function gradient (using continuous adjoint) | ||
| GRAD_OBJFUNC_FILENAME= of_grad.dat | ||
| % | ||
| % Output file surface flow coefficient (w/o extension) | ||
| SURFACE_FILENAME= surface_flow | ||
| % | ||
| % Output file surface adjoint coefficient (w/o extension) | ||
| SURFACE_ADJ_FILENAME= surface_adjoint | ||
| % | ||
| % Writing solution file frequency | ||
| OUTPUT_WRT_FREQ= 500 | ||
| % | ||
| % Writing convergence history frequency | ||
| HISTORY_WRT_FREQ_OUTER= 1 | ||
| WRT_ZONE_HIST = YES |