Abstract
With future gas turbine designs seeking increased overall pressure ratios, blade heights in the rear stages of high-pressure compressors are expected to decrease. As this will lead to an increase of relative tip clearance height, a detailed knowledge of the associated rotor tip leakage flows becomes increasingly important. In particular, the development of blockage due to large tip leakage flows can be an key component leading to an understanding of stage matching for multistage machines. To assess blockage related to increased tip clearance, a series of measurements are presented here from a three-stage compressor at two loading conditions on the 100% corrected speedline. These data correspond to three tip clearance configurations, up to 4% span. Initially, three-component velocities measured using hot-wire anemometry are analyzed. Following these initial calculations, a blockage definition technique related to gradient identification is introduced, by which the tip leakage flow size downstream of the rotors is directly related to the blockage in the tip region of the compressor. Further, steady pressures are used to calculate an approximate blockage downstream of the stators. Ultimately, these simplified pressure-based blockage calculation techniques reveal results which compare well with the velocity-based results, within three percent or better.
| Original language | English (US) |
|---|---|
| Title of host publication | 54th AIAA Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| ISBN (Print) | 9781624103933 |
| State | Published - Jan 1 2016 |
| Event | 54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States Duration: Jan 4 2016 → Jan 8 2016 |
Publication series
| Name | 54th AIAA Aerospace Sciences Meeting |
|---|
Other
| Other | 54th AIAA Aerospace Sciences Meeting, 2016 |
|---|---|
| Country | United States |
| City | San Diego |
| Period | 1/4/16 → 1/8/16 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
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Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements. / Berdanier, Reid Adam; Key, Nicole L.
54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (54th AIAA Aerospace Sciences Meeting).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
TY - GEN
T1 - Quantifying blockage in a multistage compressor for different tip clearances using steady and unsteady pressure measurements
AU - Berdanier, Reid Adam
AU - Key, Nicole L.
PY - 2016/1/1
Y1 - 2016/1/1
N2 - With future gas turbine designs seeking increased overall pressure ratios, blade heights in the rear stages of high-pressure compressors are expected to decrease. As this will lead to an increase of relative tip clearance height, a detailed knowledge of the associated rotor tip leakage flows becomes increasingly important. In particular, the development of blockage due to large tip leakage flows can be an key component leading to an understanding of stage matching for multistage machines. To assess blockage related to increased tip clearance, a series of measurements are presented here from a three-stage compressor at two loading conditions on the 100% corrected speedline. These data correspond to three tip clearance configurations, up to 4% span. Initially, three-component velocities measured using hot-wire anemometry are analyzed. Following these initial calculations, a blockage definition technique related to gradient identification is introduced, by which the tip leakage flow size downstream of the rotors is directly related to the blockage in the tip region of the compressor. Further, steady pressures are used to calculate an approximate blockage downstream of the stators. Ultimately, these simplified pressure-based blockage calculation techniques reveal results which compare well with the velocity-based results, within three percent or better.
AB - With future gas turbine designs seeking increased overall pressure ratios, blade heights in the rear stages of high-pressure compressors are expected to decrease. As this will lead to an increase of relative tip clearance height, a detailed knowledge of the associated rotor tip leakage flows becomes increasingly important. In particular, the development of blockage due to large tip leakage flows can be an key component leading to an understanding of stage matching for multistage machines. To assess blockage related to increased tip clearance, a series of measurements are presented here from a three-stage compressor at two loading conditions on the 100% corrected speedline. These data correspond to three tip clearance configurations, up to 4% span. Initially, three-component velocities measured using hot-wire anemometry are analyzed. Following these initial calculations, a blockage definition technique related to gradient identification is introduced, by which the tip leakage flow size downstream of the rotors is directly related to the blockage in the tip region of the compressor. Further, steady pressures are used to calculate an approximate blockage downstream of the stators. Ultimately, these simplified pressure-based blockage calculation techniques reveal results which compare well with the velocity-based results, within three percent or better.
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M3 - Conference contribution
AN - SCOPUS:85007579639
SN - 9781624103933
T3 - 54th AIAA Aerospace Sciences Meeting
BT - 54th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
ER -