Abstract
Quantifying high freestream turbulence effects on surface heat transfer and on blade boundary layer development is important for improving predictions of the thermal loading and aerodynamic losses for gas turbine blades, vanes, and endwalls. To improve our physical understanding as well as improve CFD capabilities, detailed flow and thermal field data is needed in addition to surface data. This paper discusses the development of a turbulence generator that is capable of generating turbulence intensities as high as 20% and yet allow an independent control on the turbulent length scale. The integral length scale at a turbulence intensity of T1 = 20% ranged from 2.1 cm to 5.5 cm. The development of the turbulence generator took place in a wind tunnel having a large, constant area, test section. After this development, the turbulence generator was placed upstream of a scaled-up turbine vane. This paper also describes the development of the turbine vane test section that has a central first stage stator vane that was scaled up by a factor of nine, Finally, turbulence measurements, turbulent length scales, and energy spectra measured inside the turbine vane passage are presented and compared to measurements that were made in the constant area test section. The results indicate that in the first 40% of the stator vane passage, the turbulence levels rapidly decrease by a factor of four with the integral length scales having a rapid growth.
| Original language | English (US) |
|---|---|
| Title of host publication | Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery |
| Publisher | American Society of Mechanical Engineers (ASME) |
| ISBN (Electronic) | 9780791878682 |
| DOIs | |
| State | Published - Jan 1 1997 |
| Event | ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1997 - Orlando, United States Duration: Jun 2 1997 → Jun 5 1997 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Volume | 1 |
Other
| Other | ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1997 |
|---|---|
| Country | United States |
| City | Orlando |
| Period | 6/2/97 → 6/5/97 |
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All Science Journal Classification (ASJC) codes
- Engineering(all)
Cite this
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High freestream turbulence simulation in a scaled-up turbine vane passage. / Bangert, B. A.; Kohli, A.; Sauer, J. H.; Thole, Karen Ann.
Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. American Society of Mechanical Engineers (ASME), 1997. (Proceedings of the ASME Turbo Expo; Vol. 1).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
TY - GEN
T1 - High freestream turbulence simulation in a scaled-up turbine vane passage
AU - Bangert, B. A.
AU - Kohli, A.
AU - Sauer, J. H.
AU - Thole, Karen Ann
PY - 1997/1/1
Y1 - 1997/1/1
N2 - Quantifying high freestream turbulence effects on surface heat transfer and on blade boundary layer development is important for improving predictions of the thermal loading and aerodynamic losses for gas turbine blades, vanes, and endwalls. To improve our physical understanding as well as improve CFD capabilities, detailed flow and thermal field data is needed in addition to surface data. This paper discusses the development of a turbulence generator that is capable of generating turbulence intensities as high as 20% and yet allow an independent control on the turbulent length scale. The integral length scale at a turbulence intensity of T1 = 20% ranged from 2.1 cm to 5.5 cm. The development of the turbulence generator took place in a wind tunnel having a large, constant area, test section. After this development, the turbulence generator was placed upstream of a scaled-up turbine vane. This paper also describes the development of the turbine vane test section that has a central first stage stator vane that was scaled up by a factor of nine, Finally, turbulence measurements, turbulent length scales, and energy spectra measured inside the turbine vane passage are presented and compared to measurements that were made in the constant area test section. The results indicate that in the first 40% of the stator vane passage, the turbulence levels rapidly decrease by a factor of four with the integral length scales having a rapid growth.
AB - Quantifying high freestream turbulence effects on surface heat transfer and on blade boundary layer development is important for improving predictions of the thermal loading and aerodynamic losses for gas turbine blades, vanes, and endwalls. To improve our physical understanding as well as improve CFD capabilities, detailed flow and thermal field data is needed in addition to surface data. This paper discusses the development of a turbulence generator that is capable of generating turbulence intensities as high as 20% and yet allow an independent control on the turbulent length scale. The integral length scale at a turbulence intensity of T1 = 20% ranged from 2.1 cm to 5.5 cm. The development of the turbulence generator took place in a wind tunnel having a large, constant area, test section. After this development, the turbulence generator was placed upstream of a scaled-up turbine vane. This paper also describes the development of the turbine vane test section that has a central first stage stator vane that was scaled up by a factor of nine, Finally, turbulence measurements, turbulent length scales, and energy spectra measured inside the turbine vane passage are presented and compared to measurements that were made in the constant area test section. The results indicate that in the first 40% of the stator vane passage, the turbulence levels rapidly decrease by a factor of four with the integral length scales having a rapid growth.
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U2 - 10.1115/97-GT-051
DO - 10.1115/97-GT-051
M3 - Conference contribution
AN - SCOPUS:84973637741
T3 - Proceedings of the ASME Turbo Expo
BT - Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
PB - American Society of Mechanical Engineers (ASME)
ER -