Möller, Daniel ; Jüngst, Maximilian ; Holzinger, Felix ; Brandstetter, Christoph ; Leichtfuss, Sebastian ; Schiffer, Heinz-Peter (2016)
Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig.
In: ASME Journal of Turbomachinery, 139 (1)
doi: 10.1115/1.4034029
Artikel, Bibliographie
Kurzbeschreibung (Abstract)
This paper presents a numerical study on blade vibration for the transonic compressor rig at the Technische Universit€at Darmstadt (TUD), Darmstadt, Germany. The vibration was experimentally observed for the second eigenmode of the rotor blades at nonsynchronous frequencies and is simulated for two rotational speeds using a time-linearized approach. The numerical simulation results are in close agreement with the experiment in both cases. The vibration phenomenon shows similarities to flutter. Numerical simulations and comparison with the experimental observations showed that vibrations occur near the compressor stability limit due to interaction of the blade movement with a pressure fluctuation pattern originating from the tip clearance flow. The tip clearance flow pattern travels in the backward direction, seen from the rotating frame of reference, and causes a forward traveling structural vibration pattern with the same phase difference between blades. When decreasing the rotor tip gap size, the mechanism causing the vibration is alleviated.
| Typ des Eintrags: | Artikel |
|---|---|
| Erschienen: | 2016 |
| Autor(en): | Möller, Daniel ; Jüngst, Maximilian ; Holzinger, Felix ; Brandstetter, Christoph ; Leichtfuss, Sebastian ; Schiffer, Heinz-Peter |
| Art des Eintrags: | Bibliographie |
| Titel: | Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig |
| Sprache: | Englisch |
| Publikationsjahr: | 2016 |
| Verlag: | ASME |
| Titel der Zeitschrift, Zeitung oder Schriftenreihe: | ASME Journal of Turbomachinery |
| Jahrgang/Volume einer Zeitschrift: | 139 |
| (Heft-)Nummer: | 1 |
| Veranstaltungstitel: | Journal of Turbomachinery |
| DOI: | 10.1115/1.4034029 |
| Kurzbeschreibung (Abstract): | This paper presents a numerical study on blade vibration for the transonic compressor rig at the Technische Universit€at Darmstadt (TUD), Darmstadt, Germany. The vibration was experimentally observed for the second eigenmode of the rotor blades at nonsynchronous frequencies and is simulated for two rotational speeds using a time-linearized approach. The numerical simulation results are in close agreement with the experiment in both cases. The vibration phenomenon shows similarities to flutter. Numerical simulations and comparison with the experimental observations showed that vibrations occur near the compressor stability limit due to interaction of the blade movement with a pressure fluctuation pattern originating from the tip clearance flow. The tip clearance flow pattern travels in the backward direction, seen from the rotating frame of reference, and causes a forward traveling structural vibration pattern with the same phase difference between blades. When decreasing the rotor tip gap size, the mechanism causing the vibration is alleviated. |
| Zusätzliche Informationen: | TURBO-15-1240 |
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet für Gasturbinen, Luft- und Raumfahrtantriebe (GLR) |
| Hinterlegungsdatum: | 11 Aug 2016 05:22 |
| Letzte Änderung: | 11 Mär 2020 08:23 |
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