The instructions are as follows:

To create two meridional slices, one for each fan in TCAE, follow these step-by-step instructions:

1. Load the Simulation Results: Open your TCAE project and load the results of your simulation for the fans.

2. Select the First Fan:

   • In the Pipeline Browser, select the mesh or results corresponding to the first fan.

3. Add a Meridional Average Filter:

   • Go to the Filters menu.
   • Select "Turbomachinery" and then choose "Meridional Average."

I am not presently seeing any geometry in the Pipeline Browser, so, I tried double-clicking the individual STLs making up the component in CFD Mesh, (later realizing selecting multiple elements is not supported) then going to the Filters menu, selecting Turbomachinery,  the option "Meridional Average."  is greyed out, please see image.

I'm still at the beginning setup phase; loading geometry and tweaking types and interfaces. I have no results of any simulation to load. I have not tried to create a mesh yet. Is that (or something else) I need to do first besides read the manual?

Thanks in advance

David

Please see my comments, below, for Fan and Duct Separator info.
Question:  For the case with a closed bottom system inlet,  is the Reference Frame of the Top Fan Open Rim interface, that's the second "surface" boundary that the incoming air encounters on it's way to join the other half; is it static, rotating, or freestream? Shared inlet air flows through it to the inlet of the bottom fan. How about it's type?

Same question for bottom fan except, because it is upside-down compared to the top fan; what is the reference frame of the Bottom Fan Open-Rim Interface? While we're at it, how about the Bottom Fan Shroud Interface? Closed bottom inlet, remember?; are they static, rotating, or freestream? Type?

From the shared inlet at the top of an axi-symmetric radial discharge duct, aka Volute or Hull, one-half of the flow first enters between the Top Fan Shroud  and  Rim, then blade passages, exits the fan, rides a cosine curve down to join the other half geometrically  mirrored about the X-axis, which has become the Bottom Fan discharge, combines radially without colliding too much, then downward smoothly toward axial, but not exactly.

I have an idea for dynamic stability, could be combined with distance between cg and center-of- lift asymmetry.

Closed Bottom Duct Surface and Duct Separator not shown for clarity. No bottom inlet opening for first simulation case. System outlet is a 0.83 [m] outside diameter annulus of appropriate area for combined fan discharge.

The Fans: each identical, one-piece solid poly-surface Boolean union of rim, shroud, and blade array has open rim, no hub, mounted to a 0.315 [m] OD carbon fiber rim bicycle wheel.

Thanks in advance.

David

is it possible with TCAE to make “overmesh” meshes?

Hi,

I have a problem with report at the end?

Program made all 3000 iteration ( about 1.200.000 pcs), but at the end is allways problem with the report: (see picture below).

Thanks.

Hi,

I have a problem with report at the end?

Program made all 3000 iteration ( about 1.200.000 pcs), but at the end is allways problem with the report: (see picture below).

Thanks.

I have been trying to run the the NASA HECC tutorial provided by TCAE. The tutorial has a very dense mesh and takes verylong to run and make a speedline. In order to save computation time I tried two methods:

1. I reduced the mesh and ran the simulation for only one point on the speedline (the one with the highest efficiency). 

2. I ran the whole tutorial as is and just skipped the first two points 

Both methods do not result in convergence at all. I am not sure what is going wrong. I have tried to adjust the relaxation factors annd still nothing works to get convergence.

What can i do to fix this?

Hi,

I'm a new user of TCAE-Lite.

I've setup a pump case and the "check" button says the case has been setup correctly. However it fails to mesh.

The same error occurs when running the f1 tutorial case.

Any advice would be appreciated,

Thanks,

Tom

Hello,

I found you have changed the Spitfire TCFD example few versions ago so as it applies 1.5AoA - or -1.5 It does not matter actually in this scope - by rotating velocity vector and aiming to get it rotated as expected by setting forces axes rotated in Runtime evaluated quantities, so this should apply to the final report. I've simplified the example - to get faster results - and found that in the report forces are never rotated as expected despite that Coefficients are rotated, you can test this by changing the Forces in Runtime evaluated quantities to 0,0,1,1,0,0 in the example and see that only Coefficients are changed in the report.

Tested on TCAE 25.03v1

Hi everyone,

I woud like to export the relative velocity URel magnitude, instead of the absolute velocity U magnitude, in the interfaces files created by TCAE in ../stationnary/postProcessing/interfaceName/0/interfaces.csv. I tried to change the file ./stationnary/system/interfaces. fun by replacing magU by magURel in the list of fields per interface but it did'nt work... How can I do it ?

Thanks in advance !

Zacharie Prigent

TCAE-Lite is designed for those with limited budgets.

Over 50 man-years of consistent development on top of open-source condensed in unlimited software at the cost of a daily cup of coffee. 

https://www.cfdsupport.com/tcae-lite.html

hashtag#CFD hashtag#Simulation hashtag#FluidDynamics hashtag#FlowVisualization

I am looking to simulate the power output of an in pipe axial turbine, I don't have any experience in CFD simulations and I've decided to brake down the project into 3 parts, first I am going to simulate just the pipe in which the turbine is going to be housed, then a static state with the turbine in the pipe, and finally setup the rotation of the turbine.

I've made a quick 3D model of the pipe and I tried copying the setup from the pipe example, I ran into a problem where the mesher consumes all the available RAM on the computer and locks it up, I assume the STL mesh has a hole somewhere but I couldn't find it, I've had issues before with glitches in STL meshes made in Rhinoceros 3D, the modeling program I used, so I decided to recreate the pipe example with the STLs from the example, and that meshed successfully, but I got an error in the TCFD part "TCFD calculation failed. Please consult the chapter 'Rescue list' in the TCAE Manual for possible reasons of the failure.", I couldn't find the Rescue list chapter in the manual online.

Also the TCAE Output gives this error:
"Application decomposePar failed.
For detailed information check error log at: "C:\Users\Name\Desktop\CFD Test\CFD_test\simulationRun1\TCFD\logRun\solve-err-decomposePar-stationary-1.log"".

And in that log file is:
"--> FOAM FATAL IO ERROR:
Cannot find patchField entry for Co1_pipe-wall_wall

file: C:/Users/Name/Desktop/CFD Test/CFD_test/simulationRun1/TCFD/stationary/0/nut/boundaryField from line 32 to line 54.

    From function void Foam::GeometricField<Type, PatchField, GeoMesh>::Boundary::readField(const Foam::DimensionedField<TypeR, GeoMesh>&, const Foam::dictionary&) [with Type = double; PatchField = Foam::fvPatchField; GeoMesh = Foam::volMesh]
    in file /opt/OpenFOAM-dev/src/OpenFOAM/lnInclude/GeometricBoundaryField.C at line 184.

FOAM exiting"

Attached is a rough diagram of how will the setup work.

I don't have an idea what to try next, and would be thankful for any assistance.

I have just installed v24.10 of TCAE-Lite. Initially I installed under Linux, sicne that is where I would really like to use the software. Having downloaded the pipe tutorial I load the case and get this message "Project configuration not fully valid according to TCAE-Lite 24.10 and may have been auto-corrected." When I try to run, I get a message that the caluclation cannot be started, and that the project contains some problems. Upon using the check option, it says that there is no geometry loaded for solid component 1. The stl file does exist in commonData\TMESH\imported and I can load it into ParaView with no issues.

So I then tried installing under Windows. In this case it does not complain about the geometry. However, when I try to run I still get a failure, which is "Failed to execute "netgenSTLMesh" (error 2)." It asks me to check an error log (mesh-err-07-netgenMesh-component1.log), but this file does not exist (there is no netgenmesh log file, and the mesh-err-07 file is called mesh-err-07-mergeMultiMeshes.log.

Can anyone provide details as to why the FEA meshing fails under Windows, and why the geometry does not work under Linux?

Hello, I am very new to CFD and simulations, I am trying to simulate the power output of a kaplan hydro turbine. I have made the geometry, but when I try to mesh it, after 15 minutes it fails. Is there any function in TCAE that I can use to check the mesh, I think it might not be water tight, but I don't know where. Also, the setup check passes without errors.

If you need any more information, please let me know.

Thank you in advance.

Hello,

I tried to run the benchmark cases NACA0012 and now I am at TCAE module. I have noticed that the running time of TCAE is long and I want to accelerate it but I haven't found places to set the number of processors. Is  that means the module cannot be computed in parallel? By the way, no my CPU utilization is low but memory is full. 

Thanks for help.