From 0df559607937d699b4c4637dfc1ed5347f959636 Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Fri, 3 Nov 2023 13:47:40 +0100 Subject: [PATCH 01/21] adding 3D mixing-plane Aachen turbine config files --- .../Aachen_turbine/aachen_3D_MP.cfg | 371 ++++++++++++++++++ .../turbomachinery/Aachen_turbine/rotor.cfg | 19 + .../turbomachinery/Aachen_turbine/stator1.cfg | 6 + .../turbomachinery/Aachen_turbine/stator2.cfg | 6 + 4 files changed, 402 insertions(+) create mode 100644 TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg create mode 100644 TestCases/turbomachinery/Aachen_turbine/rotor.cfg create mode 100644 TestCases/turbomachinery/Aachen_turbine/stator1.cfg create mode 100644 TestCases/turbomachinery/Aachen_turbine/stator2.cfg diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg new file mode 100644 index 00000000000..89090f5d9cb --- /dev/null +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.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= 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 (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=30000 +% +% 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= ../Mesh_and_sol/aachen_turbine_3D_41blade.su2 +% +% Mesh input file format (SU2, CGNS, NETCDF_ASCII) +MESH_FORMAT= SU2 +% +% Mesh output file +MESH_OUT_FILENAME= ../Mesh_and_sol/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 diff --git a/TestCases/turbomachinery/Aachen_turbine/rotor.cfg b/TestCases/turbomachinery/Aachen_turbine/rotor.cfg new file mode 100644 index 00000000000..ed7d886a96b --- /dev/null +++ b/TestCases/turbomachinery/Aachen_turbine/rotor.cfg @@ -0,0 +1,19 @@ +% ----------------------- DYNAMIC MESH DEFINITION -----------------------------% +% +% +% Type of dynamic mesh (NONE, ROTATING_FRAME) +GRID_MOVEMENT= ROTATING_FRAME +% +% Motion mach number (non-dimensional). Used for intitializing a viscous flow +% with the Reynolds number and for computing force coeffs. with dynamic meshes. +MACH_MOTION= 0.35 +% +MOTION_ORIGIN= 0.0 0.0 0.0 +% Angular velocity vector (rad/s) about the motion origi. Example 1250 RPM -> 130.89969389957471 rad/s 7508.3 +ROTATION_RATE= 0.0 0.0 -366.52 + +% Specify ramp option fr rotating frame (YES, NO) default NO +RAMP_ROTATING_FRAME= NO +% +% Parameters of the rotating frame ramp (starting rotational speed, updating-iteration-frequency, total number of iteration for the ramp) +RAMP_ROTATING_FRAME_COEFF= (0.0, 39.0, 500) diff --git a/TestCases/turbomachinery/Aachen_turbine/stator1.cfg b/TestCases/turbomachinery/Aachen_turbine/stator1.cfg new file mode 100644 index 00000000000..8c4f1def0c3 --- /dev/null +++ b/TestCases/turbomachinery/Aachen_turbine/stator1.cfg @@ -0,0 +1,6 @@ +% ----------------------- DYNAMIC MESH DEFINITION -----------------------------% +% +% +% Type of dynamic mesh (NONE, ROTATING_FRAME) +GRID_MOVEMENT= ROTATING_FRAME +% \ No newline at end of file diff --git a/TestCases/turbomachinery/Aachen_turbine/stator2.cfg b/TestCases/turbomachinery/Aachen_turbine/stator2.cfg new file mode 100644 index 00000000000..8c4f1def0c3 --- /dev/null +++ b/TestCases/turbomachinery/Aachen_turbine/stator2.cfg @@ -0,0 +1,6 @@ +% ----------------------- DYNAMIC MESH DEFINITION -----------------------------% +% +% +% Type of dynamic mesh (NONE, ROTATING_FRAME) +GRID_MOVEMENT= ROTATING_FRAME +% \ No newline at end of file From e138511b16cccb665130c2d90a7c20a45af3da89 Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Fri, 3 Nov 2023 13:53:08 +0100 Subject: [PATCH 02/21] path to mesh file changed --- TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg | 4 ++-- 1 file changed, 2 insertions(+), 2 deletions(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg index 89090f5d9cb..e0cda3a343f 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg @@ -322,13 +322,13 @@ OUTPUT_FILES= (TECPLOT_ASCII, SURFACE_TECPLOT_ASCII, RESTART) % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % % Mesh input file -MESH_FILENAME= ../Mesh_and_sol/aachen_turbine_3D_41blade.su2 +MESH_FILENAME= aachen_turbine_3D_41blade.su2 % % Mesh input file format (SU2, CGNS, NETCDF_ASCII) MESH_FORMAT= SU2 % % Mesh output file -MESH_OUT_FILENAME= ../Mesh_and_sol/aachen_turbine_3D_41blade.su2 +MESH_OUT_FILENAME= aachen_turbine_3D_41blade.su2 % % Restart flow input file SOLUTION_FILENAME= restart_flow.dat From 00ce99fed24b5779b880517d62586cbd1760aa90 Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Mon, 6 Nov 2023 15:01:56 +0100 Subject: [PATCH 03/21] adding Aachen turbine to parallel_regression --- TestCases/parallel_regression.py | 8 ++++++++ 1 file changed, 8 insertions(+) diff --git a/TestCases/parallel_regression.py b/TestCases/parallel_regression.py index f26049592b8..992470f5dd6 100644 --- a/TestCases/parallel_regression.py +++ b/TestCases/parallel_regression.py @@ -1034,6 +1034,14 @@ 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 = [-13.373601, -12.292596, -14.478385, -11.684489, -11.338515, -7.903908] + 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" From 65f8388d950a5ef124fc611ad20f95ef32bcd856 Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Mon, 6 Nov 2023 15:03:03 +0100 Subject: [PATCH 04/21] adding Aachen turbine to serial_regression --- TestCases/serial_regression.py | 9 +++++++++ 1 file changed, 9 insertions(+) diff --git a/TestCases/serial_regression.py b/TestCases/serial_regression.py index a8486bc11ea..d542e07f211 100644 --- a/TestCases/serial_regression.py +++ b/TestCases/serial_regression.py @@ -852,6 +852,15 @@ 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 = [-13.373601, -12.292596, -14.478385, -11.684489, -11.338515, -7.903908] + Aachen_3D_restart.tol = 0.0001 + 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" From b87c5bfcc062daa1f544b47a6351e276a0b1130b Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Mon, 6 Nov 2023 15:05:52 +0100 Subject: [PATCH 05/21] 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 From b3c2389c8b62cbaa0b46478f95466f10298af9e9 Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Fri, 10 Nov 2023 13:54:18 +0100 Subject: [PATCH 06/21] mesh file name in configs updated --- TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg | 4 ++-- .../turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg | 4 ++-- 2 files changed, 4 insertions(+), 4 deletions(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg index e0cda3a343f..c9e64ab5345 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg @@ -322,13 +322,13 @@ OUTPUT_FILES= (TECPLOT_ASCII, SURFACE_TECPLOT_ASCII, RESTART) % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % % Mesh input file -MESH_FILENAME= aachen_turbine_3D_41blade.su2 +MESH_FILENAME= Aachen_3D_41_blade_coarse.su2 % % Mesh input file format (SU2, CGNS, NETCDF_ASCII) MESH_FORMAT= SU2 % % Mesh output file -MESH_OUT_FILENAME= aachen_turbine_3D_41blade.su2 +MESH_OUT_FILENAME= Aachen_3D_41_blade_coarse.su2 % % Restart flow input file SOLUTION_FILENAME= restart_flow.dat diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg index 0e23e13699d..5acf0eb8531 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -322,13 +322,13 @@ OUTPUT_FILES= (TECPLOT_ASCII, SURFACE_TECPLOT_ASCII, RESTART) % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % % Mesh input file -MESH_FILENAME= aachen_turbine_3D_41blade.su2 +MESH_FILENAME= Aachen_3D_41_blade_coarse.su2 % % Mesh input file format (SU2, CGNS, NETCDF_ASCII) MESH_FORMAT= SU2 % % Mesh output file -MESH_OUT_FILENAME= aachen_turbine_3D_41blade.su2 +MESH_OUT_FILENAME= Aachen_3D_41_blade_coarse.su2 % % Restart flow input file SOLUTION_FILENAME= restart_flow.dat From 9cef1888566113f5005798300af1cf81daa978b4 Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Tue, 28 Nov 2023 17:05:24 +0100 Subject: [PATCH 07/21] fixing the iteration number --- .../turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg index 5acf0eb8531..482c7955c16 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -287,7 +287,7 @@ DV_VALUE= 0.01 % --------------------------- CONVERGENCE PARAMETERS --------------------------% % % Number of total iterations -OUTER_ITER=5 +OUTER_ITER=10 % % Convergence criteria (CAUCHY, RESIDUAL) CONV_FIELD=RMS_ENERGY[0] From 55bc78597040051c109a799671be125e3cb4e974 Mon Sep 17 00:00:00 2001 From: A Cappiello Date: Wed, 29 Nov 2023 14:27:38 +0100 Subject: [PATCH 08/21] fixing test values in regression tests --- TestCases/parallel_regression.py | 2 +- TestCases/serial_regression.py | 2 +- 2 files changed, 2 insertions(+), 2 deletions(-) diff --git a/TestCases/parallel_regression.py b/TestCases/parallel_regression.py index 992470f5dd6..03a00216132 100644 --- a/TestCases/parallel_regression.py +++ b/TestCases/parallel_regression.py @@ -1039,7 +1039,7 @@ def main(): 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 = [-13.373601, -12.292596, -14.478385, -11.684489, -11.338515, -7.903908] + Aachen_3D_restart.test_vals = [-15.164439, -14.403106, -15.080788, -13.555608, -12.719007, -9.746760] test_list.append(Aachen_3D_restart) # Jones APU Turbocharger restart diff --git a/TestCases/serial_regression.py b/TestCases/serial_regression.py index d542e07f211..110bb3d8885 100644 --- a/TestCases/serial_regression.py +++ b/TestCases/serial_regression.py @@ -857,7 +857,7 @@ def main(): 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 = [-13.373601, -12.292596, -14.478385, -11.684489, -11.338515, -7.903908] + Aachen_3D_restart.test_vals = [-15.227701, -14.551669, -15.080787, -13.635771, -12.721746, -9.826153] Aachen_3D_restart.tol = 0.0001 test_list.append(Aachen_3D_restart) From dadedf4ea288ad89d734ce7b52cea126398e54f7 Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Wed, 29 Nov 2023 15:12:46 +0100 Subject: [PATCH 09/21] Update TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg Adding supporting comment to TURBO_PERF_KIND keyword Co-authored-by: Josh Kelly <81244680+joshkellyjak@users.noreply.github.com> --- TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg | 2 ++ 1 file changed, 2 insertions(+) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg index c9e64ab5345..56535397c54 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg @@ -159,6 +159,8 @@ MARKER_SHROUD= (SHROUD1, SHROUD2, SHROUD3) TURBOMACHINERY_KIND= AXIAL AXIAL AXIAL % % Uncomment to work with new_turbo_outputs +% Specify the machine architecture for performance analysis (TURBINE, COMPRESSOR, PROPELLOR) +% %TURBO_PERF_KIND= (TURBINE, TURBINE, TURBINE) % % Specify kind of interpolation for the mixing-plane (LINEAR_INTERPOLATION, NEAREST_SPAN, MATCHING) From cd68e3b8b5cf71e72031d79697e87d48f8d8210f Mon Sep 17 00:00:00 2001 From: Josh Kelly <81244680+joshkellyjak@users.noreply.github.com> Date: Tue, 12 Mar 2024 14:56:51 +0000 Subject: [PATCH 10/21] Update aachen_3D_MP.cfg --- TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg index 56535397c54..01c4e31069e 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg @@ -161,7 +161,7 @@ TURBOMACHINERY_KIND= AXIAL AXIAL AXIAL % Uncomment to work with new_turbo_outputs % Specify the machine architecture for performance analysis (TURBINE, COMPRESSOR, PROPELLOR) % -%TURBO_PERF_KIND= (TURBINE, TURBINE, TURBINE) +TURBO_PERF_KIND= (TURBINE, TURBINE, TURBINE) % % Specify kind of interpolation for the mixing-plane (LINEAR_INTERPOLATION, NEAREST_SPAN, MATCHING) MIXINGPLANE_INTERFACE_KIND= LINEAR_INTERPOLATION From 6bc54d28d5c4cab759ec7bc4b43a5979820a75f7 Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Tue, 12 Mar 2024 16:33:44 +0100 Subject: [PATCH 11/21] Update aachen_3D_MP_restart.cfg adding TURBO_PERF_KIND --- .../turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg index 482c7955c16..ce76e8a6472 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -159,7 +159,7 @@ MARKER_SHROUD= (SHROUD1, SHROUD2, SHROUD3) TURBOMACHINERY_KIND= AXIAL AXIAL AXIAL % % Uncomment to work with new_turbo_outputs -%TURBO_PERF_KIND= (TURBINE, TURBINE, TURBINE) +TURBO_PERF_KIND= (TURBINE, TURBINE, TURBINE) % % Specify kind of interpolation for the mixing-plane (LINEAR_INTERPOLATION, NEAREST_SPAN, MATCHING) MIXINGPLANE_INTERFACE_KIND= LINEAR_INTERPOLATION From 5d2a61e4efba3a6148cd15803853f379a3db1ece Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Wed, 13 Mar 2024 09:17:20 +0100 Subject: [PATCH 12/21] Update serial_regression.py Update residuals in serial regression --- TestCases/serial_regression.py | 3 +-- 1 file changed, 1 insertion(+), 2 deletions(-) diff --git a/TestCases/serial_regression.py b/TestCases/serial_regression.py index 31dcd2f5ce5..dab5dd1256f 100644 --- a/TestCases/serial_regression.py +++ b/TestCases/serial_regression.py @@ -857,8 +857,7 @@ def main(): 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 = [-15.227701, -14.551669, -15.080787, -13.635771, -12.721746, -9.826153] - Aachen_3D_restart.tol = 0.0001 + 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 From d9c7a7c0b65e13239660ad0d03bdb780c9816c8a Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Wed, 13 Mar 2024 09:19:38 +0100 Subject: [PATCH 13/21] Update parallel_regression.py Update residual values in parallel regression test --- TestCases/parallel_regression.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/TestCases/parallel_regression.py b/TestCases/parallel_regression.py index 06aaecf59c2..51b18e48741 100644 --- a/TestCases/parallel_regression.py +++ b/TestCases/parallel_regression.py @@ -1049,7 +1049,7 @@ def main(): 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 = [-15.164439, -14.403106, -15.080788, -13.555608, -12.719007, -9.746760] + 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 From 501e0b67132d2cb45b665b3a210e2adf1ea4df51 Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Wed, 13 Mar 2024 13:10:34 +0100 Subject: [PATCH 14/21] Update parallel_regression.py fix residual values --- TestCases/parallel_regression.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/TestCases/parallel_regression.py b/TestCases/parallel_regression.py index 51b18e48741..d8a28db6a8e 100644 --- a/TestCases/parallel_regression.py +++ b/TestCases/parallel_regression.py @@ -1049,7 +1049,7 @@ def main(): 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] + Aachen_3D_restart.test_vals = [-15.063514, -14.406005, -15.078886, -13.390427, -12.718131, -9.631495] test_list.append(Aachen_3D_restart) # Jones APU Turbocharger restart From 4efad8b623823ddb4e09a3734ab7c9cb6d926264 Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Thu, 14 Mar 2024 11:06:35 +0100 Subject: [PATCH 15/21] Update parallel_regression.py --- TestCases/parallel_regression.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/TestCases/parallel_regression.py b/TestCases/parallel_regression.py index d8a28db6a8e..51b18e48741 100644 --- a/TestCases/parallel_regression.py +++ b/TestCases/parallel_regression.py @@ -1049,7 +1049,7 @@ def main(): 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 = [-15.063514, -14.406005, -15.078886, -13.390427, -12.718131, -9.631495] + 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 From 53f9b2a7073247945dfaf17c67276a4e5c12fa57 Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Thu, 14 Mar 2024 14:26:50 +0100 Subject: [PATCH 16/21] Update aachen_3D_MP_restart.cfg removing unused chauchy criterion --- .../Aachen_turbine/aachen_3D_MP_restart.cfg | 10 ---------- 1 file changed, 10 deletions(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg index ce76e8a6472..97deb468167 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -298,16 +298,6 @@ 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]) % From 3d78a44b2375b579a825a17dfe6fda5b2b0104ac Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Thu, 14 Mar 2024 15:06:30 +0100 Subject: [PATCH 17/21] Update aachen_3D_MP.cfg Removing unused Cauchy convergence criterion --- .../turbomachinery/Aachen_turbine/aachen_3D_MP.cfg | 10 ---------- 1 file changed, 10 deletions(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg index 01c4e31069e..ded976c2abd 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg @@ -300,16 +300,6 @@ 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]) % From a0a7fc64636003de1a337d30fefc3c478c9db7c3 Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Fri, 15 Mar 2024 13:24:49 +0100 Subject: [PATCH 18/21] Delete TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg Removing duplicate config --- .../Aachen_turbine/aachen_3D_MP.cfg | 363 ------------------ 1 file changed, 363 deletions(-) delete mode 100644 TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg deleted file mode 100644 index ded976c2abd..00000000000 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP.cfg +++ /dev/null @@ -1,363 +0,0 @@ -%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% -% % -% 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= 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 (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 -% Specify the machine architecture for performance analysis (TURBINE, COMPRESSOR, PROPELLOR) -% -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=30000 -% -% 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 ' 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_3D_41_blade_coarse.su2 -% -% Mesh input file format (SU2, CGNS, NETCDF_ASCII) -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 (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 From a4030aa5f0b3037c91aa61c4c6144a60e9d3b465 Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Fri, 15 Mar 2024 13:29:18 +0100 Subject: [PATCH 19/21] Update aachen_3D_MP_restart.cfg leaner config file --- .../Aachen_turbine/aachen_3D_MP_restart.cfg | 20 ++++++++----------- 1 file changed, 8 insertions(+), 12 deletions(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg index 97deb468167..b1096952f78 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -12,9 +12,7 @@ % % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% % -% Physical governing equations (EULER, NAVIER_STOKES, -% WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY, -% POISSON_EQUATION) +% Physical governing equations SOLVER= RANS % % Specify turbulent model (NONE, SA, SST) @@ -71,8 +69,7 @@ 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) +% Flow non-dimensionalization REF_DIMENSIONALIZATION= DIMENSIONAL % % @@ -211,7 +208,7 @@ 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 or smoother for implicit formulations LINEAR_SOLVER= FGMRES % % Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI) @@ -233,13 +230,12 @@ LIMITER_ITER= 999999 % % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% % -% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, -% TURKEL_PREC, MSW) +% Convective numerical method 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) +% Spatial numerical order integration MUSCL_FLOW= NO % % Slope limiter (VENKATAKRISHNAN, VAN_ALBADA) @@ -254,7 +250,7 @@ TIME_DISCRE_FLOW= EULER_IMPLICIT % Convective numerical method (SCALAR_UPWIND) CONV_NUM_METHOD_TURB= SCALAR_UPWIND % -% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER) +% Spatial numerical order integration MUSCL_TURB= NO % % Slope limiter (VENKATAKRISHNAN, MINMOD) @@ -314,7 +310,7 @@ OUTPUT_FILES= (TECPLOT_ASCII, SURFACE_TECPLOT_ASCII, RESTART) % Mesh input file MESH_FILENAME= Aachen_3D_41_blade_coarse.su2 % -% Mesh input file format (SU2, CGNS, NETCDF_ASCII) +% Mesh input file format MESH_FORMAT= SU2 % % Mesh output file @@ -326,7 +322,7 @@ SOLUTION_FILENAME= restart_flow.dat % Restart adjoint input file SOLUTION_ADJ_FILENAME= restart_adj.dat % -% Output file format (PARAVIEW, TECPLOT, STL) +% Output file format TABULAR_FORMAT= TECPLOT % % Output file convergence history (w/o extension) From f33b3addba4d929c55b02e4fbfe024233c54d93a Mon Sep 17 00:00:00 2001 From: alecappiello <149589647+alecappiello@users.noreply.github.com> Date: Fri, 15 Mar 2024 13:57:31 +0100 Subject: [PATCH 20/21] Update aachen_3D_MP_restart.cfg Removing file version from config --- .../turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg | 3 +-- 1 file changed, 1 insertion(+), 2 deletions(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg index b1096952f78..9d96f859684 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -4,8 +4,7 @@ % Case description: AACHEN turbine 3D % % Author: S. Vitale, A. Cappiello % % Institution: Delft University of Technology % -% Date: Oct 20th, 2023 % -% File Version 8.0 develop % +% Date: Oct 20th, 2023 % % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % From 8b039ab044eaff2264af73926482d4505a051865 Mon Sep 17 00:00:00 2001 From: Pedro Gomes <38071223+pcarruscag@users.noreply.github.com> Date: Fri, 15 Mar 2024 18:07:42 +0000 Subject: [PATCH 21/21] Update TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg --- .../turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg index 9d96f859684..2f4eb415a16 100644 --- a/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg +++ b/TestCases/turbomachinery/Aachen_turbine/aachen_3D_MP_restart.cfg @@ -4,7 +4,7 @@ % Case description: AACHEN turbine 3D % % Author: S. Vitale, A. Cappiello % % Institution: Delft University of Technology % -% Date: Oct 20th, 2023 % % +% Date: Oct 20th, 2023 % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %