Update turbomachinery testcases and regression tests

TestCases/parallel_regression.py

@@ -1044,6 +1044,14 @@ def main():
     ### Turbomachinery                 ###
     ######################################
 
+    # Aachen Turbine restart
+    Aachen_3D_restart           = TestCase('aachen_turbine_restart')
+    Aachen_3D_restart.cfg_dir   = "turbomachinery/Aachen_turbine"
+    Aachen_3D_restart.cfg_file  = "aachen_3D_MP_restart.cfg"
+    Aachen_3D_restart.test_iter = 5
+    Aachen_3D_restart.test_vals = [-15.329206, -15.008622, -15.078888, -13.841072, -12.727840, -9.975729]
+    test_list.append(Aachen_3D_restart)
+
     # Jones APU Turbocharger restart
     Jones_tc_restart           = TestCase('jones_turbocharger_restart')
     Jones_tc_restart.cfg_dir   = "turbomachinery/APU_turbocharger"

TestCases/serial_regression.py

@@ -852,6 +852,14 @@ def main():
     ### Turbomachinery                 ###
     ######################################
 
+    # Aachen Turbine restart
+    Aachen_3D_restart           = TestCase('aachen_turbine_restart')
+    Aachen_3D_restart.cfg_dir   = "turbomachinery/Aachen_turbine"
+    Aachen_3D_restart.cfg_file  = "aachen_3D_MP_restart.cfg"
+    Aachen_3D_restart.test_iter = 5
+    Aachen_3D_restart.test_vals = [-15.137167, -14.551444, -15.078894, -13.486154, -12.724891, -9.717612]
+    test_list.append(Aachen_3D_restart)
+
     # Jones APU Turbocharger restart
     Jones_tc_restart           = TestCase('jones_turbocharger_restart')
     Jones_tc_restart.cfg_dir   = "turbomachinery/APU_turbocharger"

TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg

@@ -0,0 +1,356 @@
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                              %
+% SU2 configuration file                                                       %
+% Case description: AACHEN turbine 3D                                          %
+% Author: S. Vitale, A. Cappiello                                              %
+% Institution: Delft University of Technology                                  %
+% Date: Oct 20th, 2023                                                         %
+%                                                                              %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%
+%
+% ------------- 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= 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 
+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 
+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= ROE
+ENTROPY_FIX_COEFF= 0.001
+%
+JST_SENSOR_COEFF= ( 0.5, 0.25 )
+% Spatial numerical order integration 
+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
+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=10
+%
+% 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-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_3D_41_blade_coarse.su2
+%
+% Mesh input file format
+MESH_FORMAT= SU2
+%
+% Mesh output file
+MESH_OUT_FILENAME= Aachen_3D_41_blade_coarse.su2
+%
+% Restart flow input file
+SOLUTION_FILENAME= restart_flow.dat
+%
+% Restart adjoint input file
+SOLUTION_ADJ_FILENAME= restart_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= 500
+%
+% Writing convergence history frequency
+HISTORY_WRT_FREQ_OUTER= 1
+WRT_ZONE_HIST = YES