NASA Rotor 67 Fluent

peruano2420 · March 29, 2019, 17:53

I am working on a project where I am using Fluent 19.1. I have a NASA Rotor 67 Mesh. I am having trouble finding convergence on my adiabatic efficiency. I am able to attain ~65% adiabatic efficiency. I have tried to set up my model various methods, but seem to be having problems.

I initially ran a mass flow inlet with a pressure outlet. My inlet conditions at 101,325 Pa, 288.15 K, and Mass Flow of 33.25. My outlet conditions are 121600 backflow total pressure, 288.15 K. Both inlet and outlet directions are normal to boundary. I set the problem up as a frame motion, used Steady and Transient time steps, Pressure-Based, and Relative reference frame for the solver. I am Using K-Omega SST. Would you have any recommendations to improve my adiabatic efficiency?

I also have tried to run an inlet pressure and outlet pressure, with target mass flow, using a density solver but having issues with convergence of mass flow. Does Fluent divide the mass flow by the sector angle, or would I need to input the Mass Flow for the individual passage? Any recommendations would be great.

lvincek · April 3, 2019, 10:49

Hi,

Can you please describe how did you set up the rotation and mixing planes?
Could you maybe share the case files?

peruano2420 · April 3, 2019, 11:25

See files and result in the following folder. I also placed an example paper on a similar analysis in CFX. I have been unable to do a Pressure inlet and Outlet.

https://drive.google.com/open?id=15S...4sIG34yspToaxj

lvincek · April 3, 2019, 11:44

Hi,
I just had a quick look and one of the first thins I noticed is that you have huge y+ numbers. So just to see if this is an issue I would run this as pressure based coupled k epsilon with standard wall functions. See if this changes something.
If not, try to refine the mesh around your "shaft" and start from there.

March 29, 2019, 17:53	NASA Rotor 67 Fluent	#1
peruano2420 New Member Carlos Calixtro Join Date: Mar 2019 Posts: 3 Rep Power: 7	I am working on a project where I am using Fluent 19.1. I have a NASA Rotor 67 Mesh. I am having trouble finding convergence on my adiabatic efficiency. I am able to attain ~65% adiabatic efficiency. I have tried to set up my model various methods, but seem to be having problems. I initially ran a mass flow inlet with a pressure outlet. My inlet conditions at 101,325 Pa, 288.15 K, and Mass Flow of 33.25. My outlet conditions are 121600 backflow total pressure, 288.15 K. Both inlet and outlet directions are normal to boundary. I set the problem up as a frame motion, used Steady and Transient time steps, Pressure-Based, and Relative reference frame for the solver. I am Using K-Omega SST. Would you have any recommendations to improve my adiabatic efficiency? I also have tried to run an inlet pressure and outlet pressure, with target mass flow, using a density solver but having issues with convergence of mass flow. Does Fluent divide the mass flow by the sector angle, or would I need to input the Mass Flow for the individual passage? Any recommendations would be great.

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April 3, 2019, 10:49		#2
lvincek New Member Luka Vincekovic Join Date: Mar 2019 Posts: 6 Rep Power: 7	Hi, Can you please describe how did you set up the rotation and mixing planes? Could you maybe share the case files?

April 3, 2019, 11:25		#3
peruano2420 New Member Carlos Calixtro Join Date: Mar 2019 Posts: 3 Rep Power: 7	See files and result in the following folder. I also placed an example paper on a similar analysis in CFX. I have been unable to do a Pressure inlet and Outlet. https://drive.google.com/open?id=15S...4sIG34yspToaxj

April 3, 2019, 11:44		#4
lvincek New Member Luka Vincekovic Join Date: Mar 2019 Posts: 6 Rep Power: 7	Hi, I just had a quick look and one of the first thins I noticed is that you have huge y+ numbers. So just to see if this is an issue I would run this as pressure based coupled k epsilon with standard wall functions. See if this changes something. If not, try to refine the mesh around your "shaft" and start from there.