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Aeroelastic Stability of Combined Plunge-Pitch Mode Shapes in a Linear Compressor Cascade
Zitatschlüssel 2022_hill_jijtpp
Autor Hill, G. and Gambel, J. and Schneider, S. and Peitsch, D. and Stapelfeldt, S.
Seiten 7
Jahr 2022
ISSN 2504-186X
DOI 10.3390/ijtpp7010007
Ort Basel, Switzerland
Journal International Journal of Turbomachinery, Propulsion and Power
Jahrgang 7
Nummer 1
Monat 02
Notiz This paper is an extended version of our paper published in the Proceedings of the "14th European Turbomachinery Conference", Gdansk, Poland, 12–16 April 2021

Rolls-Royce Vibration UTC, Imperial College London:
G. Hill, S. Stapelfeldt
Technische Universität Berlin:
J. Gambel, D. Peitsch
Rolls-Royce Deutschland:
S. Schneider
Verlag MDPI
Wie herausgegeben MDPI Open Access Information and Policy Creative Common CC BY https://www.mdpi.com/openaccess
Zusammenfassung Modern aeroengine designs strive for peak specific fuel and thermal efficiency. To achieve these goals, engines have more highly loaded compressor stages, thinner aerofoils, and blended titanium integrated disks (blisks) to reduce weight. These configurations promote the occurrence of aeroelastic phenomena such as flutter. Two important parameters known to influence flutter stability are the reduced frequency and the ratio of plunge and pitch components in a combined flap mode shape. These are used as design criteria in the engine development process. However, the limit of these criteria is not fully understood. The following research aims to bridge the gap between semi-analytical models and modern compressors by systematically investigating the flutter stability of a linear compressor cascade. This paper introduces the plunge-to-pitch incidence ratio, which is defined as a function of reduced frequency and pitch axis setback for a first flap (1F) mode shape. Using numerical simulations, in addition to experimental validation, aerodynamic damping is computed for many modes to build stability maps. The results confirm the importance of these two parameters in compressor aeroelastic stability as well as demonstrate the significance of the plunge-to-pitch incidence ratio for predicting the flutter limit.
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