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Supersonic Turbine massflow change in choking area |
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#1 |
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Hi everyone!
I am analizing a supersonic turbine vane (NGV subsonic and rotor supersonic) with ansys CFX. The domain has a subsonic part which is the same in 3 different simulation (so all of them have the same chocking area) and i had some changes far from the choking area. Since i have in all the simulation the same inlet and outlet conditions and the same choking area (I checked I have M=1 always in the same spot), shouldn't i have to find the same massflow in all three of them, no matter what geometric changes i do in the supersonic part? Cause I find 3 different values of massflow (massflow change even about 30%!!!) I am imposing total pressure and static temperature at inlet and pressure at outlet. What am I missing? Thank you! |
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#2 | |
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#3 |
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Thanks for your answer Opaque.
Sincerely I didn't get your answer. I am specifying at inlet the same value of total pressure and static temperature in all 3 cases. So since I have the same boundary conditions (both at inlet and outlet) and the same geometry in the subsonic domain and in choking area, I am expecting to have the same mass flow |
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#4 | |
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I was surprised you did not use "Total Temperature" boundary condition for a highly compressible flow model.
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#5 |
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Thanks for the answer! Ok I am new in this, so I'll try to use total temperature and see what is going on
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Tags |
cfx, chockingarea, massflow, supersonic/subsonic flow, turbine |
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