Details
| Originalsprache | Englisch |
|---|---|
| Titel des Sammelwerks | ASME Turbo Expo 2013 |
| Untertitel | Turbine Technical Conference and Exposition, GT 2013 |
| Publikationsstatus | Veröffentlicht - 14 Nov. 2013 |
| Veranstaltung | ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013 - San Antonio, Tx, USA / Vereinigte Staaten Dauer: 3 Juni 2013 → 7 Juni 2013 |
Publikationsreihe
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Band | 6 A |
Abstract
The effect on non-uniform surface roughness on the aerodynamics of a turbine blade is investigated. Surface roughness on airfoils has a significant impact on total energy loss due to skin friction and typically leads to an increased thermal loading. In the present research project, investigations are supposed to be carried out experimentally. For this a blade must be designed, which accommodates the contradictory requirements of aerodynamics and manufacturing the sections of surface roughness. A fully automatic design process based on a genetic algorithm is developed and results are shown. The designed blade sufficiently fulfills the given requirements. A numerical study, using a low-Reynolds approach, is performed to investigate the influence of non-uniform roughness applied to different positions on the suction side of a high pressure turbine blade. It is shown that roughness applied at the leading and trailing edge does not significantly influence the flow whereas roughness at 20% cord length and at midchord induce transition. Especially surface roughness at 20% chord length shows a strong correlation to the change of total pressure loss.
ASJC Scopus Sachgebiete
- Ingenieurwesen (insg.)
- Allgemeiner Maschinenbau
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ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013. 2013. (Proceedings of the ASME Turbo Expo; Band 6 A).
Publikation: Beitrag in Buch/Bericht/Sammelwerk/Konferenzband › Aufsatz in Konferenzband › Forschung › Peer-Review
}
TY - GEN
T1 - Aerodynamic Effects of Non-Uniform Surface Roughness on a Turbine Blade
AU - Hohenstein, Sebastian
AU - Aschenbruck, Jens
AU - Seume, Joerg
PY - 2013/11/14
Y1 - 2013/11/14
N2 - The effect on non-uniform surface roughness on the aerodynamics of a turbine blade is investigated. Surface roughness on airfoils has a significant impact on total energy loss due to skin friction and typically leads to an increased thermal loading. In the present research project, investigations are supposed to be carried out experimentally. For this a blade must be designed, which accommodates the contradictory requirements of aerodynamics and manufacturing the sections of surface roughness. A fully automatic design process based on a genetic algorithm is developed and results are shown. The designed blade sufficiently fulfills the given requirements. A numerical study, using a low-Reynolds approach, is performed to investigate the influence of non-uniform roughness applied to different positions on the suction side of a high pressure turbine blade. It is shown that roughness applied at the leading and trailing edge does not significantly influence the flow whereas roughness at 20% cord length and at midchord induce transition. Especially surface roughness at 20% chord length shows a strong correlation to the change of total pressure loss.
AB - The effect on non-uniform surface roughness on the aerodynamics of a turbine blade is investigated. Surface roughness on airfoils has a significant impact on total energy loss due to skin friction and typically leads to an increased thermal loading. In the present research project, investigations are supposed to be carried out experimentally. For this a blade must be designed, which accommodates the contradictory requirements of aerodynamics and manufacturing the sections of surface roughness. A fully automatic design process based on a genetic algorithm is developed and results are shown. The designed blade sufficiently fulfills the given requirements. A numerical study, using a low-Reynolds approach, is performed to investigate the influence of non-uniform roughness applied to different positions on the suction side of a high pressure turbine blade. It is shown that roughness applied at the leading and trailing edge does not significantly influence the flow whereas roughness at 20% cord length and at midchord induce transition. Especially surface roughness at 20% chord length shows a strong correlation to the change of total pressure loss.
UR - http://www.scopus.com/inward/record.url?scp=84890208654&partnerID=8YFLogxK
U2 - 10.1115/GT2013-95433
DO - 10.1115/GT2013-95433
M3 - Conference contribution
AN - SCOPUS:84890208654
SN - 9780791855225
T3 - Proceedings of the ASME Turbo Expo
BT - ASME Turbo Expo 2013
T2 - ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013
Y2 - 3 June 2013 through 7 June 2013
ER -