[aja1345]

Hi dear friends,

I am simulating a axial-flow air turbine, namely, Wells turbine. Flow is steady state.
This turbine have 8 blades((360/8)=45 deg=angle between blades). Due to the circumferential symmetry, only one eight of the annulus has been computed, imposing periodic boundary conditions in the tangential direction. In my model, the computational domain has been restricted in the axial direction to four chord lengths upstream and eight chord lengths downstream of the blade.

Computational domain is as follow:






I am grateful that guide me about this problem.


Thanks,

Best,

Aja