[TurBoris]

Hello Everyone,

I have been trying to solve 360 degree inlet distortion problem in a centrifugal compressor stage including inlet(stationary), rotor and diffuser domains. Normally, with a uniform total pressure inlet boundary condition, the setup is quite easy. However, I have been facing some problems with the distortion case. Up to now, I have tried several type Fourier Transforms (Rotational Boundary Disturbance, Rotor-Stator), but the results were not satisfying. I'd like to see smooth passing between the domains and 360 degree asymmetric flow distribution in each component when I open data instancing for each component in CFD post. I'd like to know, what kind of Fourier Transforms and how should I use for this problem ?

In the attached file you can take a look on my setup view. Impeller has 13 main and splitter blades. Diffuser has 17 blades. Eventually, I want to observe the effect of the distortion on the surge margin of the stage.

There is only 1 paper published related this model whic is:

https://www.researchgate.net/publica...let_Distortion

This however does not include a diffuser stage after rotor.