In this paper an assessment of the improvement in the prediction of complex turbomachinery flows using a new near-wall Reynolds-stress model is attempted. The turbulence closure used is a near-wall low-turbulence-Reynolds-number Reynolds-stress model, that is independent of the distance-from-the-wall and of the normal-to-the-wall direction. The model takes into account the Coriolis redistribution effect on the Reynolds-stresses. The five mean flow equations and the seven turbulence model equations are solved using an implicit coupled upwind-biased solver. Results are compared with experimental data for three turbomachinery configurations: the NTUA high subsonic annular cascade, the NASA_37 rotor, and the RWTH 1 1/2 stage turbine. A detailed analysis of the flowfield is given. It is seen that the new model that takes into account the Reynolds-stress anisotropy substantially improves the agreement with experimental data, particularily for flows with large separation, while being only 30 percent more expensive than the model (thanks to an efficient implicit implementation). It is believed that further work on advanced turbulence models will substantially enhance the predictive capability of complex turbulent flows in turbomachinery.
Improved Prediction of Turbomachinery Flows Using Near-Wall Reynolds-Stress Model
Contributed by the International Gas Turbine Institute and presented at the 46th International Gas Turbine and Aeroengine Congress and Exhibition, New Orleans, Louisiana, June 4–7, 2001. Manuscript received by the International Gas Turbine Institute February 2001. Paper No. 2001-GT-196. Review Chair: R. Natole.
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Gerolymos , G. A., Neubauer , J., Sharma , V. C., and Vallet , I. (February 1, 2001). "Improved Prediction of Turbomachinery Flows Using Near-Wall Reynolds-Stress Model ." ASME. J. Turbomach. January 2002; 124(1): 86–99. https://doi.org/10.1115/1.1426083
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