Help Required on CFD for Turbine Blade Analysis
 

Hi,
i m new here .. nd i m nt familiar with ANSYS flotran.. so can any one help me in doing a turbine blade analysis... i have the same divergent solution error each time ... the solution is not converging
i already use the MIR stability conditions...
i m not sure about the reference conditions will any body explain me how to specify them...
the temperature at the inlet is 900 K and pressure is 1.96 bar.
i m also using artificial Viscosity concept but the results are not with in range and negative temperature error occured..
kindly some one help me ..
thanks in advance for any response......

Hi,

Are you using ANSYS Flotran? That package is very old technology and you really should more to a more modern solver. Things like artificial viscosity are so 1990's.

Glenn Horrocks

thanks for ur reply friend... i know its old but i have my project in tht so i have to do it so if anybody can help me in these i will be thankful...

Hi,

I don't think you will find many people who know Flotran here but the general concepts of CFD are applicable to all solvers. I would check things like convergence, mesh size and quality, time step size (if transient), physical accuracy of the boundary conditions and validity of the modelled physics.

Start with a coarse grid, tight convergence, double precision numerics and lots of upwinding to have a nice stable solution. Once that is running OK then start moving to more accurate but unstable schemes on finer grids, higher order discretisation. You can also check whether you need double precision numerics and determine how tight convergence is required in your case.

Also consider starting at a lower pressure ratio and increasing it. Shoudl make convergence easier.

Glenn Horrocks

Thanks Friend...
so i m going to explain my problem..
wht i have to do is a turbine blade analysis. the pic below will show u the whole domain.. 6 number of turbine blades and a fluid channel.
http://i483.photobucket.com/albums/r...8/123000-2.jpg

the upper side of the domain is the inlet side and the downward side is the exit side...
at inlet the boundary conditions given are:
inlet velocity:
Vx = 31.5
Vy = -43.5
Vz = 0
Pressure = 1.96e5
Temp = 900 K

at exit side the boundary conditions are:
Pressure = 1.932e5

at blade walls the velocity components are zero.
and at the side walls symmetry boundary condition is used.
I will be very thankful to u if u take a look at this.


waiting for ur reply friend.
thanks