PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit
The flow structures in an axial compressor that lead to short-length scale stall inception are investigated using optical measurements in a high-speed one and a half stage compressor. During transient throttling procedures, velocity was measured in a tangential plane at 92% channel height, intersect...
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| Format: | Article |
| Language: | English |
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Global Power and Propulsion Society
2018-01-01
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| Series: | Journal of the Global Power and Propulsion Society |
| Subjects: | |
| Online Access: | https://www.gppsjournal.org/journals/journal-of-the-global-power-and-propulsion-society/piv-measurements-near-stall-in-transonic-compressor/ |
| _version_ | 1818228566743056384 |
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| author | Christoph Brandstetter Heinz-Peter Schiffer |
| author_facet | Christoph Brandstetter Heinz-Peter Schiffer |
| author_sort | Christoph Brandstetter |
| collection | DOAJ |
| description | The flow structures in an axial compressor that lead to short-length scale stall inception are investigated using optical measurements in a high-speed one and a half stage compressor. During transient throttling procedures, velocity was measured in a tangential plane at 92% channel height, intersecting the tip leakage vortex. The results show large scale disturbances of the secondary flow structure, which results from unsteady breakdown of the tip leakage vortex. It was possible to resolve spill forward several revolutions before the occurrence of rotating stall. This effect leads to local flow separations on the blade suction side and the development of radial vortex structures. The vortices are transported to the adjacent blade and cause further separations. Both effects are described in literature but were measured directly for the first time in a transonic compressor in this investigation. They are visualized for several time steps during transient throttling maneuvers and compared to blade vibration amplitudes. During the final phase before rotating stall occurs, asynchronous blade vibrations correlate with axial velocity in the region around the blade leading edge. |
| first_indexed | 2024-12-12T10:04:45Z |
| format | Article |
| id | doaj.art-d8c05380ce024566bf85090f11f79a7c |
| institution | Directory Open Access Journal |
| issn | 2515-3080 2515-3080 |
| language | English |
| last_indexed | 2024-12-12T10:04:45Z |
| publishDate | 2018-01-01 |
| publisher | Global Power and Propulsion Society |
| record_format | Article |
| series | Journal of the Global Power and Propulsion Society |
| spelling | doaj.art-d8c05380ce024566bf85090f11f79a7c2022-12-22T00:27:55ZengGlobal Power and Propulsion SocietyJournal of the Global Power and Propulsion Society2515-30802515-30802018-01-012110.22261/JGPPS.JYVUQDPIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limitChristoph Brandstetter0Heinz-Peter Schiffer1Technische Universität Darmstadt, Institute of Gas Turbines and Aerospace Propulsion, Otto-Berndt-Strasse 2, Darmstadt, 64287, GermanyÉcole Centrale de Lyon, Fluid Mechanics and Acoustics Laboratory, 36 Avenue Guy de Collongue, Ecully Cedex, 69134, FranceThe flow structures in an axial compressor that lead to short-length scale stall inception are investigated using optical measurements in a high-speed one and a half stage compressor. During transient throttling procedures, velocity was measured in a tangential plane at 92% channel height, intersecting the tip leakage vortex. The results show large scale disturbances of the secondary flow structure, which results from unsteady breakdown of the tip leakage vortex. It was possible to resolve spill forward several revolutions before the occurrence of rotating stall. This effect leads to local flow separations on the blade suction side and the development of radial vortex structures. The vortices are transported to the adjacent blade and cause further separations. Both effects are described in literature but were measured directly for the first time in a transonic compressor in this investigation. They are visualized for several time steps during transient throttling maneuvers and compared to blade vibration amplitudes. During the final phase before rotating stall occurs, asynchronous blade vibrations correlate with axial velocity in the region around the blade leading edge.https://www.gppsjournal.org/journals/journal-of-the-global-power-and-propulsion-society/piv-measurements-near-stall-in-transonic-compressor/PIVcompressorstallaeroelasticfluid-structure-interactioninstability |
| spellingShingle | Christoph Brandstetter Heinz-Peter Schiffer PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit Journal of the Global Power and Propulsion Society PIV compressor stall aeroelastic fluid-structure-interaction instability |
| title | PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit |
| title_full | PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit |
| title_fullStr | PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit |
| title_full_unstemmed | PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit |
| title_short | PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit |
| title_sort | piv measurements of the transient flow structure in the tip region of a transonic compressor near stability limit |
| topic | PIV compressor stall aeroelastic fluid-structure-interaction instability |
| url | https://www.gppsjournal.org/journals/journal-of-the-global-power-and-propulsion-society/piv-measurements-near-stall-in-transonic-compressor/ |
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