[DenysD]

Dear colleagues,
I deal with 3D calculation of axial compressor in FineTurbo. I did 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.
I'd like to ask, does someone else have the same result of calculation?
Perhaps, can someone explain this result or I did something incorrectly?

[gsgt07]

Hi Denys,

Please check whether your simulation is converged.

Regards,
GS

[DenysD]

Hello GS,
Thanks for your reply.
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.

Regards,
Denys

[DenysD]

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?

Regards,
Denys

[Hamidzoka]

Hi,
It does not seem a big issue cause the difference between the green and yellow regions aorund stator blade is mariginal. So, it can be result of numerical errors. One important source of error can be the type of rotor-stator interface. If you have transonic flows or shocks taking place near the rotor-stator interface, mixing plane or pitchwise averaged type does not work well. Try other interface options like 2d domain scaling.


Regards