Details
| Original language | English |
|---|---|
| Title of host publication | ASME Turbo Expo 2012 |
| Subtitle of host publication | Turbine Technical Conference and Exposition, GT 2012 |
| Pages | 289-300 |
| Number of pages | 12 |
| Publication status | Published - 9 Jul 2013 |
| Event | ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012 - Copenhagen, Denmark Duration: 11 Jun 2012 → 15 Jun 2012 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Number | PARTS A, B, AND C |
| Volume | 8 |
Abstract
Since Oehlert et al. (2007), significant improvements in the manufacturing processes of riblets by laser-structuring and grinding have been achieved. In the present study, strategies for manufacturing small-scale grooves with a spacing smaller than 40 μm by metal bonded grinding wheels are presented. For the laser-structuring process, significant improvements of the production time by applying diffractive optical elements were achieved. Finally, strategies for evaluating the geometrical quality of the small-scale surface structures are shown and results obtained with two different measuring techniques (SEM and confocal microscope) are compared with each other. The aerodynamic impact of the different manufacturing processes is investigated based upon skin friction reduction data obtained on flat plates as well as the profile-loss reduction of riblet-structured compressor blades measured in a linear cascade wind tunnel. Numerical simulations with MISES embedded in a Monte Carlo Simulation (MCS) were performed in order to calculate the profile-loss reduction of a blade structured by grinding to define further improvements of the riblet-geometry. A numerical as well as experimental study quantifying the relevant geometrical parameters indicate how further improvements from the present 4 % reduction in skin friction can be achieved by an additional decrease of the riblet tip-diameter and a more trapezoidal shape of the groove in order to realize the 8 % potential reduction.
ASJC Scopus subject areas
- Engineering(all)
- General Engineering
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ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. PARTS A, B, AND C. ed. 2013. p. 289-300 (Proceedings of the ASME Turbo Expo; Vol. 8, No. PARTS A, B, AND C).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Recent Advances in Manufacturing of Riblets on Compressor Blades and Their Aerodynamic Impact
AU - Lietmeyer, Christoph
AU - Denkena, Berend
AU - Kling, Rainer
AU - Krawczyk, Thomas
AU - Overmeyer, Ludger
AU - Reithmeier, Eduard
AU - Scheuer, Renke
AU - Vynnyk, Taras
AU - Wojakowski, Bodo
AU - Seume, Joerg R.
PY - 2013/7/9
Y1 - 2013/7/9
N2 - Since Oehlert et al. (2007), significant improvements in the manufacturing processes of riblets by laser-structuring and grinding have been achieved. In the present study, strategies for manufacturing small-scale grooves with a spacing smaller than 40 μm by metal bonded grinding wheels are presented. For the laser-structuring process, significant improvements of the production time by applying diffractive optical elements were achieved. Finally, strategies for evaluating the geometrical quality of the small-scale surface structures are shown and results obtained with two different measuring techniques (SEM and confocal microscope) are compared with each other. The aerodynamic impact of the different manufacturing processes is investigated based upon skin friction reduction data obtained on flat plates as well as the profile-loss reduction of riblet-structured compressor blades measured in a linear cascade wind tunnel. Numerical simulations with MISES embedded in a Monte Carlo Simulation (MCS) were performed in order to calculate the profile-loss reduction of a blade structured by grinding to define further improvements of the riblet-geometry. A numerical as well as experimental study quantifying the relevant geometrical parameters indicate how further improvements from the present 4 % reduction in skin friction can be achieved by an additional decrease of the riblet tip-diameter and a more trapezoidal shape of the groove in order to realize the 8 % potential reduction.
AB - Since Oehlert et al. (2007), significant improvements in the manufacturing processes of riblets by laser-structuring and grinding have been achieved. In the present study, strategies for manufacturing small-scale grooves with a spacing smaller than 40 μm by metal bonded grinding wheels are presented. For the laser-structuring process, significant improvements of the production time by applying diffractive optical elements were achieved. Finally, strategies for evaluating the geometrical quality of the small-scale surface structures are shown and results obtained with two different measuring techniques (SEM and confocal microscope) are compared with each other. The aerodynamic impact of the different manufacturing processes is investigated based upon skin friction reduction data obtained on flat plates as well as the profile-loss reduction of riblet-structured compressor blades measured in a linear cascade wind tunnel. Numerical simulations with MISES embedded in a Monte Carlo Simulation (MCS) were performed in order to calculate the profile-loss reduction of a blade structured by grinding to define further improvements of the riblet-geometry. A numerical as well as experimental study quantifying the relevant geometrical parameters indicate how further improvements from the present 4 % reduction in skin friction can be achieved by an additional decrease of the riblet tip-diameter and a more trapezoidal shape of the groove in order to realize the 8 % potential reduction.
UR - http://www.scopus.com/inward/record.url?scp=84881145065&partnerID=8YFLogxK
U2 - 10.1115/GT2012-69067
DO - 10.1115/GT2012-69067
M3 - Conference contribution
AN - SCOPUS:84881145065
SN - 9780791844748
T3 - Proceedings of the ASME Turbo Expo
SP - 289
EP - 300
BT - ASME Turbo Expo 2012
T2 - ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012
Y2 - 11 June 2012 through 15 June 2012
ER -