From b87c5bfcc062daa1f544b47a6351e276a0b1130b Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Mon, 6 Nov 2023 15:05:52 +0100 Subject: [PATCH] adding Aachen restart config --- .../Aachen_turbine/aachen_3D_MP_restart.cfg | 371 ++++++++++++++++++ 1 file changed, 371 insertions(+) create mode 100644 TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg new file mode 100644 index 00000000000..0e23e13699d --- /dev/null +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -0,0 +1,371 @@ +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% +% % +% 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 ' 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 ' to view list of available fields) +HISTORY_OUTPUT= (ITER, RMS_RES, TURBO_PERF) +% +% Volume output fields/groups (use 'SU2_CFD -d ' 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