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Aachen Turbine Tutorial #56

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Aachen Turbine Tutorial #56

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392c7c7
mesh and config files
alecappiello Dec 6, 2024
5291cac
right config files
alecappiello Dec 6, 2024
c6b9200
right mesh file name
alecappiello Dec 6, 2024
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365 changes: 365 additions & 0 deletions compressible_flow/Aachen_Turbine/Aachen_Turbine.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 %
% %
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Can you add the version this works for?

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%
%
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations
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= NO
%
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
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
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I don't think this does anything so maybe best to remove it to avoid confusing between this and MU_REF

%
% 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)
%
% ------------------------ WALL FUNCTION DEFINITION --------------------------%
%
MARKER_WALL_FUNCTIONS= ( BLADE1, STANDARD_WALL_FUNCTION , BLADE2, STANDARD_WALL_FUNCTION , BLADE3, STANDARD_WALL_FUNCTION , HUB1, STANDARD_WALL_FUNCTION , SHROUD1, STANDARD_WALL_FUNCTION , HUB2, STANDARD_WALL_FUNCTION , SHROUD2, STANDARD_WALL_FUNCTION , HUB3, STANDARD_WALL_FUNCTION , SHROUD3, STANDARD_WALL_FUNCTION )
WALLMODEL_KAPPA= 0.41
WALLMODEL_B= 5.5
WALLMODEL_MINYPLUS= 5.0
WALLMODEL_MAXITER= 200
WALLMODEL_RELFAC= 0.5

% 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)
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Move to surface identification section for consistency with config_template

% 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= YES
%
% 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, 150.0, 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= 2
%
% 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
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
CONV_NUM_METHOD_FLOW= JST
ENTROPY_FIX_COEFF= 0.3
%
JST_SENSOR_COEFF= ( 0.5, 0.25 )
% Spatial numerical order integration
MUSCL_FLOW= NO
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I would remove this option too

%
% 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
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 --------------------------%
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Don't think this whole section is necessary, let's save it for the turbo adjoint tutorial

%
% 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=20000
%
% 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
%
% 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-X[1], RMS_MOMENTUM-X[2], RMS_MOMENTUM-Y[0], RMS_MOMENTUM-Y[1], RMS_MOMENTUM-Y[2], RMS_MOMENTUM-Z[0], RMS_MOMENTUM-Z[1], RMS_MOMENTUM-Z[2], RMS_ENERGY[0], RMS_ENERGY[1], RMS_ENERGY[2])
%
% 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.su2
%
% Mesh input file format
MESH_FORMAT= SU2
%
% Mesh output file
MESH_OUT_FILENAME= Aachen_Turbine.su2
%
% Restart flow input file
SOLUTION_FILENAME= solution_flow.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Output file format
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= 1000
%
% Writing convergence history frequency
HISTORY_WRT_FREQ_OUTER= 1
WRT_ZONE_HIST = YES
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