Details
| Original language | English |
|---|---|
| Title of host publication | ASME Turbo Expo 2010 |
| Subtitle of host publication | Power for Land, Sea, and Air, GT 2010 |
| Pages | 301-315 |
| Number of pages | 15 |
| Edition | PARTS A, B, AND C |
| Publication status | Published - 22 Dec 2010 |
| Event | ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010 - Glasgow, United Kingdom (UK) Duration: 14 Jun 2010 → 18 Jun 2010 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Number | PARTS A, B, AND C |
| Volume | 7 |
Abstract
Airfoil active flow control has been attempted in the past in order to increase the permissible loading of boundary layers in gas turbine components. The present paper presents a stator with active flow control for a high speed compressor using a Coanda surface near the trailing edge in order to inhibit boundary layer separation. The design intent is to reduce the number of vanes while - in order to ensure a good matching with the downstream rotor - the flow turning angle is kept constant. In a first step, numerical simulations of a linear compressor cascade with circulation control are conducted. The Coanda surface is located behind an injection slot on the airfoil suction side. Small blowing rates lead to a gain in efficiency associated with a rise in static pressure. In a second step, this result is transferred to a 4-stage high speed research compressor, where the circulation control is applied in the first stator. The design method and the first results are based on steady numerical calculations. The analysis of these results shows performance benefits of the concept. For both, the cascade and the research compressor, the pressure gain and efficiency are shown as a function of blowing rate and jet power ratio. The comparison is performed based on a dimen-sionless efficiency which takes into account the change of power loss.
ASJC Scopus subject areas
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ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A, B, AND C. ed. 2010. p. 301-315 (Proceedings of the ASME Turbo Expo; Vol. 7, No. PARTS A, B, AND C).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Numerical Investigations of the Efficiency of Circulation Control in a Compressor Stator
AU - Vorreiter, A.
AU - Fischer, S.
AU - Saathoff, H.
AU - Radespiel, R.
AU - Seume, J. R.
PY - 2010/12/22
Y1 - 2010/12/22
N2 - Airfoil active flow control has been attempted in the past in order to increase the permissible loading of boundary layers in gas turbine components. The present paper presents a stator with active flow control for a high speed compressor using a Coanda surface near the trailing edge in order to inhibit boundary layer separation. The design intent is to reduce the number of vanes while - in order to ensure a good matching with the downstream rotor - the flow turning angle is kept constant. In a first step, numerical simulations of a linear compressor cascade with circulation control are conducted. The Coanda surface is located behind an injection slot on the airfoil suction side. Small blowing rates lead to a gain in efficiency associated with a rise in static pressure. In a second step, this result is transferred to a 4-stage high speed research compressor, where the circulation control is applied in the first stator. The design method and the first results are based on steady numerical calculations. The analysis of these results shows performance benefits of the concept. For both, the cascade and the research compressor, the pressure gain and efficiency are shown as a function of blowing rate and jet power ratio. The comparison is performed based on a dimen-sionless efficiency which takes into account the change of power loss.
AB - Airfoil active flow control has been attempted in the past in order to increase the permissible loading of boundary layers in gas turbine components. The present paper presents a stator with active flow control for a high speed compressor using a Coanda surface near the trailing edge in order to inhibit boundary layer separation. The design intent is to reduce the number of vanes while - in order to ensure a good matching with the downstream rotor - the flow turning angle is kept constant. In a first step, numerical simulations of a linear compressor cascade with circulation control are conducted. The Coanda surface is located behind an injection slot on the airfoil suction side. Small blowing rates lead to a gain in efficiency associated with a rise in static pressure. In a second step, this result is transferred to a 4-stage high speed research compressor, where the circulation control is applied in the first stator. The design method and the first results are based on steady numerical calculations. The analysis of these results shows performance benefits of the concept. For both, the cascade and the research compressor, the pressure gain and efficiency are shown as a function of blowing rate and jet power ratio. The comparison is performed based on a dimen-sionless efficiency which takes into account the change of power loss.
UR - http://www.scopus.com/inward/record.url?scp=82055189684&partnerID=8YFLogxK
U2 - 10.1115/GT2010-22721
DO - 10.1115/GT2010-22721
M3 - Conference contribution
AN - SCOPUS:82055189684
SN - 9780791844021
T3 - Proceedings of the ASME Turbo Expo
SP - 301
EP - 315
BT - ASME Turbo Expo 2010
T2 - ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010
Y2 - 14 June 2010 through 18 June 2010
ER -