rotation turbine darrieus

[gianlucacilenti]

hi I'm a thesis and I'm doing the fluent analysis of a peat darrieus who works at number of low kings... .
But I stuck myself to the initial conditions to be placed in fluent as I have no idea how to put the rotor rotation setting on the remaining domain. . .
Can anyone help me? Thank you.

 

[gianlucacilenti]

I solved that problem but if I launch iterations I find a difference in temperature.
I put you here under the parameters I used:

model solver-------------solverressure based
space 2d
Fastty formulation absolute
gradient options green-gauss cell based
Implied
time unsteady
porous surfacesal velocity

materials--------------

boundary conditions----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
mach number 0.01
x component 1 constant
y component 0 constant
turbolent viscosity ratio 5


What's wrong? ? What do I have to change? ? ?

 

[sail]

I solved that problem but if I launch iterations I find a difference in temperature.
I put you here under the parameters I used:

model solver-------------solverressure based
space 2d
Fastty formulation absolute
gradient options green-gauss cell based
Implied
time unsteady
porous surfacesal velocity

materials--------------

boundary conditions----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
mach number 0.01
x component 1 constant
y component 0 constant
turbolent viscosity ratio 5


What's wrong? ? What do I have to change? ? ?

strange that you have temperature, I would say that in the first approximation those turbines do not produce a heating due to a transonic or supersonic shock.

as boundary conditions do not use pressure far field but velocity inlet and outlet. pressure field does not work well at such low machs.

and remove the energy component from the simulation setup.

Then other reasons of divergence can be a non-good mesh, numerical shcemas, underrelaxation factors too tight, but with the few information given I can't help you more.