Details
| Originalsprache | Englisch |
|---|---|
| Titel des Sammelwerks | Turbomachinery |
| Untertitel | Turbomachinery Technical Conference and Exposition |
| ISBN (elektronisch) | 9780791849712 |
| Publikationsstatus | Veröffentlicht - 2016 |
Publikationsreihe
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Band | 2C-2016 |
Abstract
The state of the art design of turbomachinery components is based on RANS solutions. RANS solvers model the effects of turbulence and boundary layer transition and therefore allow for a rapid prediction of the aerodynamic behavior. The only drawback is that modeling errors are introduced to the solution. Researchers and CFD developers are working on reducing these errors by improved model calibrations which are based on experimental data. These experiments do not typically, however, offer detailed insight into three-dimensional flow fields and the evolution of model quantities in an actual machine. This can be achieved through a direct step-by-step comparison of model quantities between RANS and DNS. In the present work, the experimentally obtained model correlations are be recomputed based on DNS of the same turbine profile simulated by RANS. The actual local values are compared to the modeled RANS results, providing information about the source of model deficits. The focus is on the transition process on the blade suction side and on evaluating the development of turbulent flow structures in the blades wake. It is shown that the source of disagreement between RANS and DNS can be traced back to three major deficiencies that should be the focus of further model improvements.
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Turbomachinery: Turbomachinery Technical Conference and Exposition. 2016. (Proceedings of the ASME Turbo Expo; Band 2C-2016).
Publikation: Beitrag in Buch/Bericht/Sammelwerk/Konferenzband › Aufsatz in Konferenzband › Forschung › Peer-Review
}
TY - GEN
T1 - DNS-Based Analysis of RANS Predictions of a Low-Pressure Turbine Cascade
AU - Mueller, Christoph
AU - Baier, Ralf-D.
AU - Seume, Joerg R.
AU - Herbst, Florian
N1 - Publisher Copyright: Copyright © 2016 by ASME Copyright: Copyright 2017 Elsevier B.V., All rights reserved.
PY - 2016
Y1 - 2016
N2 - The state of the art design of turbomachinery components is based on RANS solutions. RANS solvers model the effects of turbulence and boundary layer transition and therefore allow for a rapid prediction of the aerodynamic behavior. The only drawback is that modeling errors are introduced to the solution. Researchers and CFD developers are working on reducing these errors by improved model calibrations which are based on experimental data. These experiments do not typically, however, offer detailed insight into three-dimensional flow fields and the evolution of model quantities in an actual machine. This can be achieved through a direct step-by-step comparison of model quantities between RANS and DNS. In the present work, the experimentally obtained model correlations are be recomputed based on DNS of the same turbine profile simulated by RANS. The actual local values are compared to the modeled RANS results, providing information about the source of model deficits. The focus is on the transition process on the blade suction side and on evaluating the development of turbulent flow structures in the blades wake. It is shown that the source of disagreement between RANS and DNS can be traced back to three major deficiencies that should be the focus of further model improvements.
AB - The state of the art design of turbomachinery components is based on RANS solutions. RANS solvers model the effects of turbulence and boundary layer transition and therefore allow for a rapid prediction of the aerodynamic behavior. The only drawback is that modeling errors are introduced to the solution. Researchers and CFD developers are working on reducing these errors by improved model calibrations which are based on experimental data. These experiments do not typically, however, offer detailed insight into three-dimensional flow fields and the evolution of model quantities in an actual machine. This can be achieved through a direct step-by-step comparison of model quantities between RANS and DNS. In the present work, the experimentally obtained model correlations are be recomputed based on DNS of the same turbine profile simulated by RANS. The actual local values are compared to the modeled RANS results, providing information about the source of model deficits. The focus is on the transition process on the blade suction side and on evaluating the development of turbulent flow structures in the blades wake. It is shown that the source of disagreement between RANS and DNS can be traced back to three major deficiencies that should be the focus of further model improvements.
UR - http://www.scopus.com/inward/record.url?scp=84991735430&partnerID=8YFLogxK
U2 - 10.1115/gt2016-57582
DO - 10.1115/gt2016-57582
M3 - Conference contribution
SN - 978-0-7918-4971-2
T3 - Proceedings of the ASME Turbo Expo
BT - Turbomachinery
ER -