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October 19, 2010, 04:47 
Compressible Nozzle Flow

#1 
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Sebastian Saegeler
Join Date: Nov 2009
Location: Munich
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Hi all!
I am trying to perform a steady state simulation of a compressible flow through a nozzle with a development of a jet behind it, using the kepsilon model. I was playing around now for a couple of days and have tested a lot of setups but so far I did not get any solution. Hope any of you experts can help me with that. MY CASE: The flow of my current case is expected to be subsonic (Ma=0.5). But later on I want to observe also transonic flow (Ma=1.3), which I have not tested yet. I am using a total pressure and a total temperature inlet at the inlets. I want to use the standardkepsilon model, as well as the realizable kepsilon model. The case is steady state. THE PROBLEM: After a few hundred iterations, density and pressure start oscillating and then my solution blows up. It seems that the disturbance occurs first at the outlet of the nozzle and than propagates back to the inlets... WHAT I HAVE TRIED SO FAR: First I have tested the incompressible case with simpleFoam. The solution looked pretty okay. Then I switched to the compressible case using rhoSimpleFoam. I have tested first order as well as second order discretization. I also played with the relaxation factors and the relative solver tolarance. I also have tested several meshes. I have calculated the case in Fluent, using the compressible SIMPLE algorithm without any problems. This should be the same as rhoSimpleFoam right? So why the problems in OF? Well, okay maybe OF has a problem with that and rhoSimpleFoam not the adequate solver for that.. I am a little bit lost to be honest. If anybody is interested, I have uploaded my case file. Would be glad to hear some ideas Thanks in advance! Sebastian 

October 19, 2010, 05:10 

#2 
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Felix L.
Join Date: Feb 2010
Location: Hamburg
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Hi, Sebastian,
is checkMesh reporting any kind of troubles regarding your mesh? A picture of the mesh for your case would be helpful. You said, the disturbance seems to first occur at the outlet, so it might be logical to search for the error source at the outlet first. What kind of boundary conditions have you set there? Another thing: have you tried running the case with turbulence switched off? If the simulation still blows up, we may know that it's not (only) the turbulence model, which is causing the problems. Greetings, Felix 

October 19, 2010, 05:56 

#3 
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Sebastian Saegeler
Join Date: Nov 2009
Location: Munich
Posts: 70
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Hello Felix!
Thanks for the quick answer! Yes, the problem is the same without turbulence. checkmesh says everything is okay. Sorry, maybe my explanation was a bit misleading. I didnt mean that the problem occurs at the boundary outlet of my domain. It occurs at some state of the calculation at the exit of the nozzle when the flow enters into the farfield behind the nozzle. I have attached some pics of the whole domain and the nozzle configuration. I also attached of the distribution of the static pressure, a few iterations before the simulation stops. The pressure distribution is not physical. It should be highest at the inlets. The pressure at the nozzle exit should be the same as ambient... Hope this helps to understand the case better! Sebastian 

October 19, 2010, 06:20 

#4 
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Felix L.
Join Date: Feb 2010
Location: Hamburg
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Hi, Sebastian,
at first sight I can't really tell, what's causing the problem. The mesh looks great, I don't see any troublemakers there. Is it the whole domain you're showing in the first picture? If so, it probably might be better if you move the outlet boundary further downstream where the jet has dissipated more. Could you post your BCs, please? (all of them, including velocity) And a velocity or Machnumber plot of the nozzle would be great, as it's a more "natural" way for interpreting the flow. Greetings, Felix. 

October 19, 2010, 07:51 

#5 
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Sebastian Saegeler
Join Date: Nov 2009
Location: Munich
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Hello Felix!
Yes, its the whole domain. I know its small. But for now this should be okay. I think this doesnt cause my problems. Here my BCs. And a plot of the velocitymagnitude. Think for this time of progress of the simulation, the velocity looks good. Max velocity here is ca 110 m/s, maximum Mach number is 0.35. Do you think the rhoSimpleFoam solver should handle this in general? Best regards, Sebastian 

October 19, 2010, 08:26 

#6 
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Felix L.
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Location: Hamburg
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Hey, there,
I had a look at your files and images: to my understanding everything seems to be setup fine. I have to say that I'm not too familiar with compressible simulations in OpenFOAM, but the totalPressure BCs along with zeroGradient velocity seem to be reasonable to me. Also you don't seem to have any backflow issues at the boundaries, so that shouldn't be a problem here. Another thought here: I had a similiar issue with that "choked" pressure distribution one can see in the picture you attached at post #3. That issue was in an incompressible case, though, and was a result of a local mesh issue, if I recall correctly. I was able to solve the problem by setting Code:
gradSchemes { default faceMDLimited Gauss linear 0.5; } Hope that helps, Greetings, Felix. 

October 19, 2010, 08:45 

#7 
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Sebastian Saegeler
Join Date: Nov 2009
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Hi Felix!
Thanks! No, I have not tried that. What exactly happens here if I use that grad scheme? I will give it a try Best regards, Sebastian 

October 19, 2010, 09:00 

#8 
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Felix L.
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Location: Hamburg
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Hey,
it's a limited version of the Gauss linear gradScheme. It assures that the extrapolated face values are within the limits of the neighboring cell values: Code:
Description faceMDLimitedGrad gradient scheme applied to a runTime selected base gradient scheme. The scalar limiter based on limiting the extrapolated face values between the faceneighbour cell values and is applied to the gradient in each face direction separately. Greetings, Felix. 

October 19, 2010, 11:56 

#9 
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Christian Lucas
Join Date: Aug 2009
Location: Braunschweig, Germany
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Hi,
first of all, could you please post the full case (without mesh). Are you using the transonic setting? If not, your pressure equation (at your high velocities) is not correct (as I understand this solver). Regards, Christian 

October 20, 2010, 03:22 

#10 
Member
Sebastian Saegeler
Join Date: Nov 2009
Location: Munich
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Hi!
I have tried the limitation of the gradient now. It seems that the calculation is a bit more stable and it runs a bit longer. But the result is the same  same problem occurs at the exit of my nozzle... @Christian: what do you mean by transonic setting? I have uploaded now the whole case again. So anybody feel free to tell me their ideas about the problem! Thanks! Best regards, Sebastian 

October 20, 2010, 05:51 

#11 
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Sebastian Saegeler
Join Date: Nov 2009
Location: Munich
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Hi!
I think I found the option transonic. So I switched it on by changing fvSolution: Code:
SIMPLE { nNonOrthogonalCorrectors 0; pMin pMin [1 1 2 0 0 0 0] 50000; transonic true; } Time = 1 DILUPBiCG: Solving for Ux, Initial residual = 1, Final residual = 0.00064076898, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 1, Final residual = 0.0011129843, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 1, Final residual = 0.0014193024, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99999977, Final residual = 1.2279612e05, No Iterations 1 GAMG: Solving for p, Initial residual = 1, Final residual = 0.00010163833, No Iterations 1 time step continuity errors : sum local = 5249.3272, global = 5249.2913, cumulative = 5249.2913 rho max/min : 1.4641599 1.2200726 ExecutionTime = 44.24 s ClockTime = 45 s Time = 2 DILUPBiCG: Solving for Ux, Initial residual = 0.063224505, Final residual = 0.0014127685, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.77219605, Final residual = 0.018765348, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.38431967, Final residual = 0.010036484, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.9805994, Final residual = 0.00013796488, No Iterations 1 GAMG: Solving for p, Initial residual = 0.61791917, Final residual = 2.2252849e05, No Iterations 1 time step continuity errors : sum local = 35648.227, global = 35647.963, cumulative = 40897.254 rho max/min : 1.4641542 1.2045404 ExecutionTime = 74.99 s ClockTime = 76 s Time = 3 DILUPBiCG: Solving for Ux, Initial residual = 0.19958378, Final residual = 0.0038654242, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.524207, Final residual = 0.009996843, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.17581458, Final residual = 0.0036239134, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.98209612, Final residual = 0.00020747175, No Iterations 1 GAMG: Solving for p, Initial residual = 0.60087116, Final residual = 1.5788899e05, No Iterations 1 time step continuity errors : sum local = 43254.307, global = 43254.274, cumulative = 84151.528 rho max/min : 1.4641489 1.1446924 ExecutionTime = 105.68 s ClockTime = 106 s Time = 4 DILUPBiCG: Solving for Ux, Initial residual = 0.25990016, Final residual = 0.0059634889, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.32796848, Final residual = 0.0048554188, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.095194627, Final residual = 0.0014654287, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99835796, Final residual = 0.00022092011, No Iterations 1 GAMG: Solving for p, Initial residual = 0.57627831, Final residual = 3.4923119e06, No Iterations 1 time step continuity errors : sum local = 126889.55, global = 126889.52, cumulative = 211041.05 rho max/min : 1.4641441 1.0874578 ExecutionTime = 136.46 s ClockTime = 137 s Time = 5 DILUPBiCG: Solving for Ux, Initial residual = 0.10431322, Final residual = 0.00092621411, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.28540798, Final residual = 0.0043205614, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.049779571, Final residual = 0.00081063858, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99972076, Final residual = 0.00016023754, No Iterations 1 GAMG: Solving for p, Initial residual = 0.4916998, Final residual = 2.2014033e07, No Iterations 1 time step continuity errors : sum local = 1955369.2, global = 1955369.2, cumulative = 2166410.2 rho max/min : 1.4641398 1.033085 ExecutionTime = 167.13 s ClockTime = 168 s Time = 6 DILUPBiCG: Solving for Ux, Initial residual = 0.0086557065, Final residual = 4.4554317e05, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.046355992, Final residual = 0.0004336927, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.01445842, Final residual = 0.00019740974, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99998175, Final residual = 0.0001601321, No Iterations 1 GAMG: Solving for p, Initial residual = 0.41766058, Final residual = 2.0001359e08, No Iterations 1 time step continuity errors : sum local = 22979085, global = 22979085, cumulative = 25145496 rho max/min : 1.4641358 0.98143071 ExecutionTime = 197.77 s ClockTime = 198 s Time = 7 DILUPBiCG: Solving for Ux, Initial residual = 0.0010534608, Final residual = 2.3964112e06, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.010440758, Final residual = 4.4895448e05, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.0029302907, Final residual = 1.7381004e05, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99999912, Final residual = 0.00015988003, No Iterations 1 GAMG: Solving for p, Initial residual = 0.45276891, Final residual = 2.7486885e08, No Iterations 1 time step continuity errors : sum local = 58809550, global = 58809550, cumulative = 83955046 rho max/min : 1.4641322 0.93235917 ExecutionTime = 228.46 s ClockTime = 229 s Time = 8 DILUPBiCG: Solving for Ux, Initial residual = 0.00038112419, Final residual = 5.4734558e06, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.0069200946, Final residual = 7.5209829e05, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.0021328287, Final residual = 2.5482588e05, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99999963, Final residual = 0.00015815714, No Iterations 1 GAMG: Solving for p, Initial residual = 0.52127838, Final residual = 4.6696771e09, No Iterations 1 time step continuity errors : sum local = 65978178, global = 65978178, cumulative = 1.4993322e+08 rho max/min : 1.4641289 0.88574121 ExecutionTime = 259.08 s ClockTime = 260 s Time = 9 DILUPBiCG: Solving for Ux, Initial residual = 0.00023764328, Final residual = 3.953079e07, No Iterations 2 DILUPBiCG: Solving for Uy, Initial residual = 0.0054798111, Final residual = 0.00020048139, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.0025317365, Final residual = 7.6321079e05, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99999965, Final residual = 0.00015632946, No Iterations 1 GAMG: Solving for p, Initial residual = 0.51953995, Final residual = 2.1894755e09, No Iterations 1 time step continuity errors : sum local = 67810556, global = 67810556, cumulative = 2.1774378e+08 rho max/min : 1.464126 0.84145415 ExecutionTime = 290.13 s ClockTime = 291 s Time = 10 DILUPBiCG: Solving for Ux, Initial residual = 0.00021875401, Final residual = 1.5713824e05, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.0042287586, Final residual = 1.0771838e05, No Iterations 2 DILUPBiCG: Solving for Uz, Initial residual = 0.002683303, Final residual = 0.00025108918, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99999967, Final residual = 0.00015442018, No Iterations 1 GAMG: Solving for p, Initial residual = 0.48863879, Final residual = 1.6088557e09, No Iterations 1 time step continuity errors : sum local = 68560890, global = 68560890, cumulative = 2.8630467e+08 rho max/min : 1.4641233 0.79938145 ExecutionTime = 321.16 s ClockTime = 322 s Time = 11 DILUPBiCG: Solving for Ux, Initial residual = 0.00017913139, Final residual = 2.244739e06, No Iterations 1 DILUPBiCG: Solving for Uy, Initial residual = 0.0041400616, Final residual = 8.179217e05, No Iterations 1 DILUPBiCG: Solving for Uz, Initial residual = 0.0027678658, Final residual = 4.9276336e05, No Iterations 1 DILUPBiCG: Solving for h, Initial residual = 0.99999968, Final residual = 0.00015256293, No Iterations 1 [0] [0] [0] Maximum number of iterations exceeded#0 Foam::error:rintStack(Foam::Ostream&) in "/home/sebastian/OpenFOAM/OpenFOAM1.6/lib/linuxGccDPOpt/libOpenFOAM.so" #1 Foam::error::abort() in "/home/sebastian/OpenFOAM/OpenFOAM1.6/lib/linuxGccDPOpt/libOpenFOAM.so" #2 Foam::hPsiThermo<Foam:ureMixture<Foam::constTran sport<Foam::specieThermo<Foam::hConstThermo<Foam:: perfectGas> > > > >::calculate() in "/home/sebastian/OpenFOAM/OpenFOAM1.6/lib/linuxGccDPOpt/libbasicThermophysicalModels.so" #3 Foam::hPsiThermo<Foam:ureMixture<Foam::constTran sport<Foam::specieThermo<Foam::hConstThermo<Foam:: perfectGas> > > > >::correct() in "/home/sebastian/OpenFOAM/OpenFOAM1.6/lib/linuxGccDPOpt/libbasicThermophysicalModels.so" #4 main in "/home/sebastian/OpenFOAM/OpenFOAM1.6/applications/bin/linuxGccDPOpt/rhoSimpleFoam" #5 __libc_start_main in "/lib/tls/libc.so.6" #6 _start at ../sysdeps/i386/elf/start.S:122 [0] [0] [0] From function specieThermo<thermo>::T(scalar f, scalar T0, scalar (specieThermo<thermo>::*F)(const scalar) const, scalar (specieThermo<thermo>::*dFdT)(const scalar) const) const [0] in file /home/dm2/henry/OpenFOAM/OpenFOAM1.6/src/thermophysicalModels/specie/lnInclude/specieThermoI.H at line 68. [0] FOAM parallel run aborting [0]  MPI_ABORT was invoked on rank 0 in communicator MPI_COMM_WORLD with errorcode 1. NOTE: invoking MPI_ABORT causes Open MPI to kill all MPI processes. You may or may not see output from other processes, depending on exactly when Open MPI kills them.   mpirun has exited due to process rank 0 with PID 18347 on node node02 exiting without calling "finalize". This may have caused other processes in the application to be terminated by signals sent by mpirun (as reported here).  

October 20, 2010, 06:59 

#12 
Senior Member
Felix L.
Join Date: Feb 2010
Location: Hamburg
Posts: 165
Rep Power: 9 
Hi, Sebastian,
well, due to my limited experience with the rhoSimpleFoamsolver this case is beginning to give me a headache. I can only guess now and I think that's not the help you're looking for  nevertheless: two more thoughts that came to my mind:  What relaxation factors did you try? Maybe this thread gives you a new kind of inspiration: compressible flow calculation error using rhoSimpleFoam solver  Your initial field is a uniform field, as far as I can see. You might want to try to map the simpleFoam results to your compressible case (which is pretty tough because of the normalized pressure values) or you can try getting a starting field with a short transient calculation and have rhoSimpleFoam start a calculation with the resulting initial values. Sorry about the guesswork, but I'm pretty confident someone else here knows a fine answer. Greetings, Felix. 

October 21, 2010, 03:22 

#13 
Senior Member
Christian Lucas
Join Date: Aug 2009
Location: Braunschweig, Germany
Posts: 198
Rep Power: 7 
Hi,
the reason why the simulation crashes is that either your pressure or your enthalpy is negative, so the Newton solver can't find the correct T for your H. rhoSimpleFoam is not the best solver for high speed steady state simulations (as far as I now). For this kind of simulations, a coupled solver is needed. I would use a transient solver (rhoPisoFoam). This will take some time, but you will get result. Regards, Christian 

October 21, 2010, 05:25 

#14 
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Sebastian Saegeler
Join Date: Nov 2009
Location: Munich
Posts: 70
Rep Power: 7 
Hi Chris!
Thanks for the reply! Whish there was installed a coupled solver here in OpenFoam. Of course I would have used that one instead. I am currently running a transient calculation with the piso solver and it takes me ages. But why is Fluent able to handle the prob with the simple algorithm? Does anybody know that? Or do they just use some fancy numerical tricks? Best regards, Sebastian 

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