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A Novel Stall Warning Indicator: Part I — Applications and Limitations
Citation key 2019_rueckert_asme
Author Rückert, R. and Eck, M. and Lehmann, M. and Peitsch, D.
Pages GT2019-90242
Year 2019
ISBN 978-0-7918-5854-7
DOI 10.1115/GT2019-90242
Location Phoenix, Arizona, USA
Journal ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition
Volume Volume 1: Aircraft Engine; Fans and Blowers; Marine; Honors and Awards
Month 06
Note V001T01A002,
Technische Universität Berlin:
R. Rückert, M. Eck, M. Lehmann, D. Peitsch
Editor ASME
Series Turbo Expo: Power for Land, Sea, and Air
Abstract The present work is the first of two papers investigating the operation principle of stall warning quantities. It discusses the use and implementation of novel stall warning techniques based on experimental tests. Each of the addressed techniques is based upon integral statistical analysis of time-resolved wall pressures in close proximity to the leading edge of a compressor rotor. The experiments were conducted on a low speed axial compressor test rig at the Chair of Aeroengines at the Technische Universität Berlin. The compressor suffers from a specific type of pre-stall instability. The signature within the frequency spectrum of this semi-stable operating point is in itself unique and was observed by many within the scientific community on numerous occasions and various axial compressor types, both low and high speed. Strong evidence has been elaborated which indicate that each of those so called stall warning indicator’s functionality is based upon the existence of this prestall phenomena. The first of two indicators is time-dependent as it evaluates the as-is state against surrounding operating points during transient manoeuvres. Furthermore, the impact of varying geometrical boundary conditions, which are known to regularly arise in flight operations, were taken into account. The functionality of the indicator is assured if the instrumentation is adjusted accordingly. The second indicator is mainly a location-dependent quantity as it evaluates the pressure signature along the axial direction within the rotor passage at various aerodynamic loadings. The latter also gave rise to some fundamental and preliminary understanding of the physics behind so called prestall disturbances.
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