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Harmonic balance method for calculating multi-stage turbines

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Old   March 11, 2022, 04:28
Default Harmonic balance method for calculating multi-stage turbines
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ChenYingJie
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Before using the harmonic balance method for turbine calculations, I used the mixing plane for constant calculations, which had gone very well.
After I used the harmonic balance method, I found that I could not use MULTIZONE = YES to define a three-zones su2 grid file, which would result in (Could not find the keyword "NDIME=".) .
Then I tried to use SOLVER= MULTIPHYSICS to assign calculation methods to each of my calculation zones. This allowed my calculations to be calculated, but did not give me the results that the harmonic balance should have. (as shown in the figure below)
I've really tried many times, but I can't always find what the problem is. If it's possible, can anyone take a look, thanks!
Here,I give my sets:

master:

Code:
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
MULTIZONE_MESH= NO
CONFIG_LIST= (zone_S1.cfg,zone_R.cfg,zone_S2.cfg)
%
SOLVER= MULTIPHYSICS
%

% ------------------------------- SOLVER CONTROL ------------------------------%
%
% Maximum number of outer iterations (only for multizone problems)
OUTER_ITER= 2000
%TIME_ITER=200
%
% Min value of the residual (log10 of the residual)
CONV_RESIDUAL_MINVAL= -6
%
% Start convergence criteria at iteration number
CONV_STARTITER= 10
%
% Number of elements to apply the criteria
CONV_CAUCHY_ELEMS= 100
%
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
% Navier-Stokes wall boundary marker(s) (NONE = no marker)
MARKER_HEATFLUX= (S1_BLADE1,0.0,S1_BLADE2,0.0,R_BLADE1,0.0,R_BLADE2,0.0,R_BLADE3,0.0,R_BLADE1_TIPWALL,0.0,R_BLADE2_TIPWALL,0.0,R_BLADE3_TIPWALL,0.0,S2_BLADE1,0.0,S2_BLADE2,0.0,S1_HUB,0.0,S1_SHROUD,0.0,R_HUB,0.0,R_SHROUD,0.0,S2_HUB,0.0,S2_SHROUD,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= (S1_PER2, S1_PER1, 0.0, 0.0, 0.0, 0.0, 0.0, 20, 0.0, 0.0, 0.0, R_PER2, R_PER1, 0.0, 0.0, 0.0, 0.0, 0.0, 20, 0.0, 0.0, 0.0,S2_PER2, S2_PER1, 0.0, 0.0, 0.0, 0.0, 0.0, 20, 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= (S1_INLET,S1_OUTLET,R_INLET,R_OUTLET,S2_INLET,S2_OUTLET)
%
% Mixing-plane interface markers must be specified to activate the transfer of information between zones
MARKER_MIXINGPLANE_INTERFACE= (S1_OUTLET,R_INLET,R_OUTLET,S2_INLET)
%MARKER_ZONE_INTERFACE= (S1_OUTLET,R_INLET,R_OUTLET,S2_INLET)
%MARKER_FLUID_INTERFACE= (S1_OUTLET,R_INLET,R_OUTLET,S2_INLET)
%
MARKER_SHROUD=(R_SHROUD)
% Giles 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= (S1_INLET, TOTAL_CONDITIONS_PT, 140000, 328.15, 1.0, 0.0, 0.0, 1.0, 0.0, S1_OUTLET, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, R_INLET, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, R_OUTLET, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, S2_INLET, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0,S2_OUTLET, STATIC_PRESSURE_1D, 87500, 0.0, 0.0, 0.0, 0.0 , 1.0, 0.0)
%
% 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)
%
%YES Non reflectivity activated, NO the Giles BC behaves as a normal 1D characteristic-based BC
SPATIAL_FOURIER= NO
%---------------------------- TURBOMACHINERY SIMULATION -----------------------------%
%
% Specify kind of architecture (AXIAL, CENTRIPETAL, CENTRIFUGAL, CENTRIPETAL_AXIAL, AXIAL_CENTRIFUGAL)
TURBOMACHINERY_KIND= AXIAL AXIAL AXIAL
%
% 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= (400000.0, 10.0, 500)
%
%
% 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= 0.05
%
%
% ------------------------ SURFACES IDENTIFICATION ----------------------------%
%
% Marker(s) of the surface in the surface flow solution file
MARKER_PLOTTING= (S1_BLADE1, R_BLADE1,S2_BLADE1)
%
zone_rotor
Code:
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Solver type (EULER, NAVIER_STOKES, RANS,
%              INC_EULER, INC_NAVIER_STOKES, INC_RANS,
%              NEMO_EULER, NEMO_NAVIER_STOKES,
%              FEM_EULER, FEM_NAVIER_STOKES, FEM_RANS, FEM_LES,
%              HEAT_EQUATION_FVM, ELASTICITY)
SOLVER= RANS
%
% Specify turbulence model (NONE, SA, SA_NEG, SST, SA_E, SA_COMP, SA_E_COMP, SST_SUST)
KIND_TURB_MODEL= SST
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT, DISCRETE_ADJOINT)
% Defaults to DISCRETE_ADJOINT for the SU2_*_AD codes, and to DIRECT otherwise.
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO
%
% Maximum number of inner iterations
INNER_ITER= 100
% System of measurements (SI, US)
% International system of units (SI): ( meters, kilograms, Kelvins,
%                                       Newtons = kg m/s^2, Pascals = N/m^2,
%                                       Density = kg/m^3, Speed = m/s,
%                                       Equiv. Area = m^2 )
% United States customary units (US): ( inches, slug, Rankines, lbf = slug ft/s^2,
%                                       psf = lbf/ft^2, Density = slug/ft^3,
%                                       Speed = ft/s, Equiv. Area = ft^2 )
SYSTEM_MEASUREMENTS= SI
%
%
% Unsteady simulation (NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER,
%                      DUAL_TIME_STEPPING-2ND_ORDER, HARMONIC_BALANCE)
TIME_MARCHING= HARMONIC_BALANCE
%
%
% Number of time instances (Zones)
TIME_INSTANCES= 3
%
% Precondition harmonic balance source term (NO, YES)
HB_PRECONDITION= YES
%
% Period of Harmonic Balance simulation
HB_PERIOD= 0.0000411522633
%
% List of frequencies to be resolved for harmonic balance method
OMEGA_HB = (0,15268.1274, -15268.1274)
%
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.1
%
% 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= 14000
%
% Free-stream temperature (273.15 K by default)
FREESTREAM_TEMPERATURE= 328.15
%
% Free-stream temperature (1.2886 Kg/m3 by default)
FREESTREAM_DENSITY= 1.47
%
% 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 = 0.05
%
% 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
%
% Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
%                              FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE
%
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation (m or in)
REF_ORIGIN_MOMENT_X = 0.00
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for moment non-dimensional coefficients (m or in)
REF_LENGTH= 1.0
%
% Reference area for non-dimensional force coefficients (0 implies automatic
% calculation) (m^2 or in^2)
REF_AREA= 1.0
%
% Aircraft semi-span (0 implies automatic calculation) (m or in)
SEMI_SPAN= 0.0
% ---- NONEQUILIBRIUM GAS, IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
%
% Fluid model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS,
%              CONSTANT_DENSITY, INC_IDEAL_GAS, INC_IDEAL_GAS_POLY, MUTATIONPP, SU2_NONEQ)
FLUID_MODEL= IDEAL_GAS
%
% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
%
% Type of dynamic mesh (NONE, RIGID_MOTION, ROTATING_FRAME,
%                       STEADY_TRANSLATION, GUST)
GRID_MOVEMENT= ROTATING_FRAME
%
% Motion mach number (non-dimensional). Used for initializing a viscous flow
% with the Reynolds number and for computing force coeffs. with dynamic meshes.
MACH_MOTION= 0.1
%
% Coordinates of the motion origin
MOTION_ORIGIN= 0.0 0.0 0.0
%
% Angular velocity vector (rad/s) about the motion origin
ROTATION_RATE = 0.0 0.0 282.0
%
% Pitching angular freq. (rad/s) about the motion origin
PITCHING_OMEGA= 0.0 0.0 0.0
%
% Pitching amplitude (degrees) about the motion origin
PITCHING_AMPL= 0.0 0.0 0.0
%
% Pitching phase offset (degrees) about the motion origin
PITCHING_PHASE= 0.0 0.0 0.0
%
% Translational velocity (m/s or ft/s) in the x, y, & z directions
TRANSLATION_RATE = 0.0 0.0 0.0
%
% Plunging angular freq. (rad/s) in x, y, & z directions
PLUNGING_OMEGA= 0.0 0.0 0.0
%
% Plunging amplitude (m or ft) in x, y, & z directions
PLUNGING_AMPL= 0.0 0.0 0.0
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY, POLYNOMIAL_VISCOSITY).
VISCOSITY_MODEL= SUTHERLAND
%
% 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 ----------------------%
%
% Laminar Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL,
% POLYNOMIAL_CONDUCTIVITY).
CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
%
%
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= GREEN_GAUSS

% Numerical method for spatial gradients to be used for MUSCL reconstruction
% Options are (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES, LEAST_SQUARES). Default value is
% NONE and the method specified in NUM_METHOD_GRAD is used.
NUM_METHOD_GRAD_RECON = LEAST_SQUARES
%
% CFL number (initial value for the adaptive CFL number)
CFL_NUMBER= 15.0
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= YES
%
% Parameters of the adaptive CFL number (factor-down, factor-up, CFL min value,
%                                        CFL max value, acceptable linear solver convergence)
% Local CFL increases by factor-up until max if the solution rate of change is not limited,
% and acceptable linear convergence is achieved. It is reduced if rate is limited, or if there
% is not enough linear convergence, or if the nonlinear residuals are stagnant and oscillatory.
% It is reset back to min when linear solvers diverge, or if nonlinear residuals increase too much.
CFL_ADAPT_PARAM= ( 0.1, 2,5,100 )
%
% ----------- SLOPE LIMITER AND DISSIPATION SENSOR DEFINITION -----------------%
%
% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations.
%           Required for 2nd order upwind schemes (NO, YES)
MUSCL_FLOW= NO
%
% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
%                BARTH_JESPERSEN, VAN_ALBADA_EDGE)
SLOPE_LIMITER_FLOW= BARTH_JESPERSEN
%
% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations.
%           Required for 2nd order upwind schemes (NO, YES)
MUSCL_TURB= NO
%
% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
%                BARTH_JESPERSEN, VAN_ALBADA_EDGE)
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
%
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
% Linear solver or smoother for implicit formulations:
% BCGSTAB, FGMRES, RESTARTED_FGMRES, CONJUGATE_GRADIENT (self-adjoint problems only), SMOOTHER.
LINEAR_SOLVER= FGMRES
%
% Same for discrete adjoint (smoothers not supported), replaces LINEAR_SOLVER in SU2_*_AD codes.
%DISCADJ_LIN_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver or type of smoother (ILU, LU_SGS, LINELET, JACOBI)
LINEAR_SOLVER_PREC= LU_SGS
%
% Same for discrete adjoint (JACOBI or ILU), replaces LINEAR_SOLVER_PREC in SU2_*_AD codes.
DISCADJ_LIN_PREC= ILU
%
% Linear solver ILU preconditioner fill-in level (0 by default)
LINEAR_SOLVER_ILU_FILL_IN= 0
%
% Minimum error of the linear solver for implicit formulations
LINEAR_SOLVER_ERROR= 1E-4
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 10
%
% Restart frequency for RESTARTED_FGMRES
LINEAR_SOLVER_RESTART_FREQUENCY= 10
%
% Relaxation factor for smoother-type solvers (LINEAR_SOLVER= SMOOTHER)
LINEAR_SOLVER_SMOOTHER_RELAXATION= 1.0
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, JST_KE, JST_MAT, LAX-FRIEDRICH, CUSP, ROE, AUSM,
%                              AUSMPLUSUP, AUSMPLUSUP2, AUSMPWPLUS, HLLC, TURKEL_PREC,
%                              SW, MSW, FDS, SLAU, SLAU2, L2ROE, LMROE)
CONV_NUM_METHOD_FLOW= ROE
%
% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
%
% Time discretization (EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_TURB= EULER_IMPLICIT
%
% Reduction factor of the CFL coefficient in the turbulence problem
CFL_REDUCTION_TURB= 1.0
% ------------------------- SCREEN/HISTORY VOLUME OUTPUT --------------------------%
%
% Screen output fields (use 'SU2_CFD -d <config_file>' to view list of available fields)
SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY)
%
% History output groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
HISTORY_OUTPUT= (ITER, RMS_RES)
%
% Volume output fields/groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
%VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE)
%
% Writing frequency for screen output
SCREEN_WRT_FREQ_INNER= 1
%
SCREEN_WRT_FREQ_OUTER= 1
%
SCREEN_WRT_FREQ_TIME= 1
%
% Writing frequency for history output
HISTORY_WRT_FREQ_INNER= 1
%
HISTORY_WRT_FREQ_OUTER= 1
%
HISTORY_WRT_FREQ_TIME= 1
%
% Writing frequency for volume/surface output
OUTPUT_WRT_FREQ= 100
%
% Output the performance summary to the console at the end of SU2_CFD
WRT_PERFORMANCE= NO
%
% Overwrite or append iteration number to the restart files when saving 
WRT_RESTART_OVERWRITE= YES
%
% Overwrite or append iteration number to the surface files when saving 
WRT_SURFACE_OVERWRITE= YES
%
% Overwrite or append iteration number to the volume files when saving 
WRT_VOLUME_OVERWRITE= YES
%
% ------------------------- INPUT/OUTPUT FILE INFORMATION --------------------------%
%
% Mesh input file
MESH_FILENAME= Rotor.su2
%
% Mesh input file format (SU2, CGNS)
MESH_FORMAT= SU2
%
% Mesh output file
MESH_OUT_FILENAME= mesh_out.su2
%
% Restart flow input file
SOLUTION_FILENAME= solution_flow.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Output tabular file format (TECPLOT, CSV)
TABULAR_FORMAT= CSV
%
% Files to output
% Possible formats : (TECPLOT_ASCII, TECPLOT, SURFACE_TECPLOT_ASCII,
%  SURFACE_TECPLOT, CSV, SURFACE_CSV, PARAVIEW_ASCII, PARAVIEW_LEGACY, SURFACE_PARAVIEW_ASCII,
%  SURFACE_PARAVIEW_LEGACY, PARAVIEW, SURFACE_PARAVIEW, RESTART_ASCII, RESTART, CGNS, SURFACE_CGNS, STL_ASCII, STL_BINARY)
% default : (RESTART, PARAVIEW, SURFACE_PARAVIEW)
OUTPUT_FILES= (RESTART, PARAVIEW, SURFACE_PARAVIEW)
%
% Output file convergence history (w/o extension)
CONV_FILENAME= history
%
% Output file with the forces breakdown
BREAKDOWN_FILENAME= forces_breakdown.dat
%
% 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
VALUE_OBJFUNC_FILENAME= of_eval.dat
%
% 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
%
% Read binary restart files (YES, NO)
READ_BINARY_RESTART= YES
%
% Reorient elements based on potential negative volumes (YES/NO)
REORIENT_ELEMENTS= YES
zone_stator1 and zone_stator is the same as zone _rotor except the mesh file and "GRID_MOVEMENT= NONE"

I used NRBC and mixingplane in the non-constant calculation, does this not work in the harmonic balance calculation? but if I replace it with fluid_interface, the algorithm does not work at all
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Old   April 23, 2022, 06:23
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hi Chen, is there any progress already? Which version of SU2 are you using for HB? Are you using the same version for HB and steady state solution.

It seems like you work with pitch ratio=1 which is good. Do you face any issue with spanwise cell count at interfaces?
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Old   April 24, 2022, 02:31
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Quote:
Originally Posted by koray View Post
hi Chen, is there any progress already? Which version of SU2 are you using for HB? Are you using the same version for HB and steady state solution.

It seems like you work with pitch ratio=1 which is good. Do you face any issue with spanwise cell count at interfaces?
Yes, Prof Pini gave me some help. In the process of 2-dimensional optimization, the constant calculation optimization is done with feature_turbo_ffd Banch,HB with feature_TMZHB_temp Banch. I have tried the 2-dimensional constant and non-constant calculations without problems. The 3D calculation and optimization I see can be done using feature_3D_turbo_aeroelasticity Banch, but I haven't done it yet.
The simulation had reported a different number of spanwise cell count error.After I redraw the grid, there is no more.
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