Validation of NASA rotor 67 with openFOAM's transonic density-based solver

Dissertação para obtenção do Grau de Mestre em Engenharia Mecânica

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.