Dear colleagues,I deal with 3D calculation of axial compressor in FineTurbo. I have done steady state calculation.I have encoutered with such issue. On the stator blade, on the suction side I have zone with increased Total Pressure.It doesn't corresponds to written in books about aerodynamics of compressor. I atteched one picture and added values of parameter in different places of section of stator blade.
Perhaps, can someone explain this result or I did something incorrectly?
This question has also been asked in the CFD online forum. The contours of the compressor can't be like that. Check whether the computation is converged.
My calculation was convergied. I don't remember reached level of convergience.Disbalance of mass flow between inlet and outlet equals 0.02%. And it looks like horizontal line.
Have you ever checked result calculation at different parameter scales? You need to try to check your results of calculation at different parameter scales.
Hello,To continue our conversation. I did calculation according to TUTORIAL 5. MULTISTAGE AXIAL COMPRESSOR from documentation platform. For first calculation I set up Current Grid Level = <1 1 1>, for second calculation I set up Current Grid Level = <0 0 0>. When both calculations reached convergence I opened result of calculation in CFView and created a blade to blade surface at mid-span. I could see in domain of stator blade near suction side zone with increased Total Pressure.Could someone explain this result of calculation?
Please confirm that you are solving Tutorial No. 5 (1.5-stage axial compressor, 2 stators, and one rotor) or that you are solving another axial compressor configuration like a 2-stage or any other. Some points I am mentioning below need to be checked.
1. Check your machine's characteristics, like selecting the stator as a stator and not as a rotor.
2. Check your definition of rotating machinery.
3. Check your BCs and also which turbulence model you are using: a one-equation or two-equation model. If you are using the 2-equation model, then how are you calculating K and dissipation?
4. How you are setting your Initial conditions for turbomachinery, (Rotation direction).
5. Check whether you have modelled suction and pressure surfaces correctly.
I am solving Tutorial No. 5 (1.5-stage axial compressor, 2 stators, and one rotor). I created mesh and set up of calculation according to documentation platform. I used Spalart Allmaras as turbulence model. I set initial conditions according to documentation.
In CFView I created a blade to blade surface at mid-span and selected Total Pressure. And result of these actions you can see in my previous reply.
If you have this documentation and .geomturbo files of 2 stators and 1 rotor, you can repeat these actions. After, in CFView you can create a blade to blade surface at mid-span, select Total Pressure and set range 119500 - 132500 Pa and you can see these strange result in domain of stator blade near suction side zone with increased Total Pressure.