Details
| Original language | English |
|---|---|
| Title of host publication | AIAA Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc. (AIAA) |
| Edition | 210059 |
| ISBN (print) | 9781624105241 |
| Publication status | Published - 7 Jan 2018 |
| Event | AIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States Duration: 8 Jan 2018 → 12 Jan 2018 |
Publication series
| Name | 2018 AIAA Aerospace Sciences Meeting |
|---|
Abstract
The surface structure of real turbo machinery blades that have worn in time can be quite complex. The characteristics of the surface roughness on compressor and turbine blades vary along the blade geometry. During the past decades, research has increasingly focussed on the effects of complex roughness structures on the flow and the aerodynamic losses. Following up on past research, the objective of this experimental investigation is to analyse how combinations of a localised surface roughness region on the suction and on the pressure side affect the loss behaviour of a compressor blade profile. Experiments have been conducted in a cascade wind tunnel and include stereoscopic velocity field measurements in the wake flow of a roughened compressor blade. The surface roughness is added by sand grains with a specific size in span-wise bands of 12 mm wide. The effect of a single localised roughnesses on respectively the pressure side and the suction side as well as the situation in which roughness is applied to both sides are analysed. The resulting loss coefficient for the combined roughness application is compared to the individual contributions. For roughnesses applied in the front half of the chord, the losses can be predicted by summation of the losses attributed to the individual roughnesses. For roughnesses applied in the aft half of the chord, there is more interaction and the combined effect is no longer simply the sum of the individual contributions. In this region the combination of roughnesses yield smaller losses than the summation of the losses due to the single roughnesses on the same positions would imply. The analysis of the anisotropy in the wake based on anisotropy invariant maps indicate that the state of the turbulence varies with the chord-wise position of the roughness. Furthermore, the type of turbulence observed depends strongly on the spatial location in the wake itself.
ASJC Scopus subject areas
- Engineering(all)
- Aerospace Engineering
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AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2018. (2018 AIAA Aerospace Sciences Meeting).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Analysis of local roughness combinations on the aerodynamic properties of a compressor blade
AU - Gilge, P.
AU - Seume, J. R.
AU - Mulleners, K.
PY - 2018/1/7
Y1 - 2018/1/7
N2 - The surface structure of real turbo machinery blades that have worn in time can be quite complex. The characteristics of the surface roughness on compressor and turbine blades vary along the blade geometry. During the past decades, research has increasingly focussed on the effects of complex roughness structures on the flow and the aerodynamic losses. Following up on past research, the objective of this experimental investigation is to analyse how combinations of a localised surface roughness region on the suction and on the pressure side affect the loss behaviour of a compressor blade profile. Experiments have been conducted in a cascade wind tunnel and include stereoscopic velocity field measurements in the wake flow of a roughened compressor blade. The surface roughness is added by sand grains with a specific size in span-wise bands of 12 mm wide. The effect of a single localised roughnesses on respectively the pressure side and the suction side as well as the situation in which roughness is applied to both sides are analysed. The resulting loss coefficient for the combined roughness application is compared to the individual contributions. For roughnesses applied in the front half of the chord, the losses can be predicted by summation of the losses attributed to the individual roughnesses. For roughnesses applied in the aft half of the chord, there is more interaction and the combined effect is no longer simply the sum of the individual contributions. In this region the combination of roughnesses yield smaller losses than the summation of the losses due to the single roughnesses on the same positions would imply. The analysis of the anisotropy in the wake based on anisotropy invariant maps indicate that the state of the turbulence varies with the chord-wise position of the roughness. Furthermore, the type of turbulence observed depends strongly on the spatial location in the wake itself.
AB - The surface structure of real turbo machinery blades that have worn in time can be quite complex. The characteristics of the surface roughness on compressor and turbine blades vary along the blade geometry. During the past decades, research has increasingly focussed on the effects of complex roughness structures on the flow and the aerodynamic losses. Following up on past research, the objective of this experimental investigation is to analyse how combinations of a localised surface roughness region on the suction and on the pressure side affect the loss behaviour of a compressor blade profile. Experiments have been conducted in a cascade wind tunnel and include stereoscopic velocity field measurements in the wake flow of a roughened compressor blade. The surface roughness is added by sand grains with a specific size in span-wise bands of 12 mm wide. The effect of a single localised roughnesses on respectively the pressure side and the suction side as well as the situation in which roughness is applied to both sides are analysed. The resulting loss coefficient for the combined roughness application is compared to the individual contributions. For roughnesses applied in the front half of the chord, the losses can be predicted by summation of the losses attributed to the individual roughnesses. For roughnesses applied in the aft half of the chord, there is more interaction and the combined effect is no longer simply the sum of the individual contributions. In this region the combination of roughnesses yield smaller losses than the summation of the losses due to the single roughnesses on the same positions would imply. The analysis of the anisotropy in the wake based on anisotropy invariant maps indicate that the state of the turbulence varies with the chord-wise position of the roughness. Furthermore, the type of turbulence observed depends strongly on the spatial location in the wake itself.
UR - http://www.scopus.com/inward/record.url?scp=85141584568&partnerID=8YFLogxK
U2 - 10.2514/6.2018-0345
DO - 10.2514/6.2018-0345
M3 - Conference contribution
SN - 9781624105241
T3 - 2018 AIAA Aerospace Sciences Meeting
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -