Hi, friends,

I am running a case regarding gas turbine combustor. The inlet boundary condition is defined to be mass-flow-inlet. The mass flow rate is given. but my problem is how to define the swirl velocity in this inlet bc, e.g., the swirl number is 0.8? I guess, I might choose the cylindrical coordinate system. But I have no idea about defining the different component flow direction.

Thanks a lot for your help.

[juzer_700]

Originally Posted by Ray
;147576

Hi, friends,

I am running a case regarding gas turbine combustor. The inlet boundary condition is defined to be mass-flow-inlet. The mass flow rate is given. but my problem is how to define the swirl velocity in this inlet bc, e.g., the swirl number is 0.8? I guess, I might choose the cylindrical coordinate system. But I have no idea about defining the different component flow direction.

Thanks a lot for your help.

Hey, I'm simulating the combustion chamber of Gas turbine. I mentioned the swirl no. How do I get the swirl velocity? I know the inlet velocity. How to calculate swirl velocity. Please help. Thanks.