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Validation of NASA rotor 67 with openFOAM's transonic density-based solver
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| 11.73 MB | Adobe PDF |
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A transonic density based solver implemented in OpenFOAM is shown to be robust and presents consistent results, when simulating three dimensional viscid ows in a low
pressure compressor. Towards the validation of the code above, the NASA Rotor 67
geometry has been tested in di erent mesh levels, with and without tip-gap, with grid
independence being suggested.
It is used an odd approach in turbomachinery, to compare experimental with numerical data: BIAS, Root Mean Square Error and Concordance Index compare results in pitch-wise and stream-wise directions, provided a linear interpolation to correct all data.
Several Riemann problems are simulated to test the shock resolution and entropy
conditions due to the transonic nature of the Rotor 67 ow.
Finally, a full compressor stage is assembled with the Mixing Plane method and a
solution to the multi-row problem is achieved, increasing the reliability of OpenFOAM libraries.
Descrição
Dissertação para obtenção do Grau de Mestre em
Engenharia Mecânica