Boundary condition analysis for turbomachinery
I am working on axial flow fan, its an annular case.
I am using OpenFOAM for my simulation.
I have give the BC, as discribed in the user manual
inlet - massflow or velocity (fixed value)
outlet - fixedValue (0), I know its not wrong, however we are forcing the pressure to zero at outlet face, so I want to say its not an appropriate one.
Then, I have given a try to fixedMeanValue (0) at outlet for pressure, it seems the result which I obtained from this BC is reasonably fine. however I want to check the deviation from the radial equilibrium solution. I am bit confused here to get the analytical solution for radial equilibrium condition. dp/dr = rho *v^2/r
v --> swirl velocity
r --> radius
my question is:
how can I get the swirl velocity?
can you people give a hit to solve the problem?
1) Getting Vx, Vy and Vz in the disk rotor by using a sampleDict* (and also angular position/velocity of the rotor if not steady), and calculating Vr, Vu and Vx by hand in Octave/Matlab/Python whatever...
2) Writing a function Object for defining a coordinate transform tensor which moves Cartesian coordinates to cylindrical within the rotor disk.
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