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Article

Aeroelastic Stability of Combined Plunge-Pitch Mode Shapes in a Linear Compressor Cascade †

1
Rolls-Royce Vibration UTC, Imperial College London, London SW7 2AZ, UK
2
Chair of Aero Engines, TU Berlin, 10587 Berlin, Germany
3
Rolls-Royce Deutschland Ltd. & Co. KG, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany
*
Author to whom correspondence should be addressed.
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.
Int. J. Turbomach. Propuls. Power 2022, 7(1), 7; https://doi.org/10.3390/ijtpp7010007
Received: 8 December 2021 / Revised: 5 February 2022 / Accepted: 8 February 2022 / Published: 14 February 2022
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. View Full-Text
Keywords: flutter; aeroelasticity; aerodynamic damping; linear cascade; 1F mode shape flutter; aeroelasticity; aerodynamic damping; linear cascade; 1F mode shape
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MDPI and ACS Style

Hill, G.; Gambel, J.; Schneider, S.; Peitsch, D.; Stapelfeldt, S. Aeroelastic Stability of Combined Plunge-Pitch Mode Shapes in a Linear Compressor Cascade. Int. J. Turbomach. Propuls. Power 2022, 7, 7. https://doi.org/10.3390/ijtpp7010007

AMA Style

Hill G, Gambel J, Schneider S, Peitsch D, Stapelfeldt S. Aeroelastic Stability of Combined Plunge-Pitch Mode Shapes in a Linear Compressor Cascade. International Journal of Turbomachinery, Propulsion and Power. 2022; 7(1):7. https://doi.org/10.3390/ijtpp7010007

Chicago/Turabian Style

Hill, George, Julian Gambel, Sabine Schneider, Dieter Peitsch, and Sina Stapelfeldt. 2022. "Aeroelastic Stability of Combined Plunge-Pitch Mode Shapes in a Linear Compressor Cascade" International Journal of Turbomachinery, Propulsion and Power 7, no. 1: 7. https://doi.org/10.3390/ijtpp7010007

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