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Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig

Möller, Daniel and Jüngst, Maximilian and Holzinger, Felix and Brandstetter, Christoph and Schiffer, Heinz-Peter and Leichtfuss, Sebastian (2016):
Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig.
In: ASME Journal of Turbomachinery, ASME, pp. 011002, 139, (1), ISSN 0889-504X,
DOI: 10.1115/1.4034029,
[Article]

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.

Item Type: Article
Erschienen: 2016
Creators: Möller, Daniel and Jüngst, Maximilian and Holzinger, Felix and Brandstetter, Christoph and Schiffer, Heinz-Peter and Leichtfuss, Sebastian
Title: Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig
Language: English
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.

Journal or Publication Title: ASME Journal of Turbomachinery
Volume: 139
Number: 1
Publisher: ASME
Divisions: 16 Department of Mechanical Engineering > Institute of Gas Turbines and Aerospace Propulsion (GLR)
16 Department of Mechanical Engineering
Event Title: Journal of Turbomachinery
Date Deposited: 11 Aug 2016 05:22
DOI: 10.1115/1.4034029
Additional Information:

TURBO-15-1240

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