Gas Turbine combustor inlet boundary condtions
Im trying to simulate a gas turbine combustor for which I know inlet conditions (massflow, pressure, temperature) and I want to evaluate efficiency of the combustor based on the outlet conditions.
I have experienced that OF blows up whenever I specify at the inlet (fixedValue BC) either:
a) temperature pressure and velocity (T p U - fixedValue)
b) pressure and massflow (p phi - fixedValue)
c) pressure and velocity (p U - fixedValue)
The other quantities are set to zeroGradient (note for velocity also used pressureInletVelocity). FYI, im using reactingFoam which uses PISO solver for momentum equations.
This is a simulation for my master thesis, so I really need your precious help. Any suggestions?
look here for inspiration
LINK TO THESIS
This is my master thesis, keep in mind we where very new to both CFD and OF moreso at the time. Also its using OF 1.4.1 but you should be able to get some inspiration.
could you please email your thesis for me? your link dose not work anymore
Could you please tell me, if your code, is for dynamic state of combustor?
And do you have ATEC code or any code that maybe I can use to simulate this model?
I have been trying to use ANSYS FLUENT Software to simulate cold flow analysis inside a combustion chamber. But I am having difficulties. It shows reverse flow when I run the calculation. My geometry is in 2D-Axisymmetrical. Also I have taken a swirl facter of 0.7 using K-Epsilon RNG turbulence method.
Velocity- 1m/s, Air at 600K
Pressure Outlet - Gauge pressure=0
Is the reverse flow because I have included the swirl in the flow? Or is it because my domain is small?
I would really appreciate if you can help me figure out the problem. Thanks in advance.
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