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A Low Speed Compressor Test Rig for Flutter Investigations
Zitatschlüssel 2016_malzacher_asme
Autor Malzacher, L. and Geist, S. and Peitsch, D. and Hennings, H.
Seiten GT2016-57960
Jahr 2016
ISBN 978-0-7918-4984-2
DOI 10.1115/GT2016-57960
Ort Seoul, South Korea
Journal ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
Jahrgang Volume 7B: Structures and Dynamics
Monat 06
Notiz V07BT34A027,
Technische Universität Berlin:
L. Malzacher, S. Geist, D. Peitsch
Deutsches Zentrum für Luft und Raumfahrt (DLR), Göttingen:
H. Hennings
Herausgeber ASME
Serie Turbo Expo: Power for Land, Sea, and Air
Zusammenfassung A test facility for aereolastic investigations has been installed at the chair of Aero Engines at the Technische Universität Berlin. The test rig provides data for tool and code validation and is used for basic aeroelastic experiments. It is a low speed wind tunnel which allows free and controlled flutter testing. The test section contains a linear cascade with eleven compressor blades. Nine of them are elastically suspended. The paper presents a detailed description of the test facility, results to evaluate the overall flow quality and an aeroelastic model to predict the flutter velocity and critical interblade phase angles. Hot-wire anemometry has been applied to examine the inlet flow for several Mach- and Reynolds numbers. The results show small turbulence intensities. The blade surface pressure distribution and the flow field of the blade’s suction and pressure side has been accessed by oil flow visualization.
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