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Stall Margin Improvement in an Axial Compressor by Continuous and Pulsed Tip Injection

Article dans une revue avec comité de lecture
Author
MOUBOGHA MOUBOGHA, Joseph
531216 Laboratoire de Mécanique des Fluides de Lille – Kampé de Fériet - UMR 9014 [LMFL]
MARGALIDA, Gabriel
531216 Laboratoire de Mécanique des Fluides de Lille – Kampé de Fériet - UMR 9014 [LMFL]
JOSEPH, Pierric
531216 Laboratoire de Mécanique des Fluides de Lille – Kampé de Fériet - UMR 9014 [LMFL]
ROUSSETTE, Olivier
531216 Laboratoire de Mécanique des Fluides de Lille – Kampé de Fériet - UMR 9014 [LMFL]
DAZIN, Antoine
531216 Laboratoire de Mécanique des Fluides de Lille – Kampé de Fériet - UMR 9014 [LMFL]

URI
http://hdl.handle.net/10985/22698
DOI
10.3390/ijtpp7010010
Date
2022-03
Journal
International Journal of Turbomachinery, Propulsion and Power

Abstract

Stall and surge are strong limitations in the operating range of compressors and thus one of the major limits of jet engine performance. A promising way to push the stability limit of compression machines is to inject a small amount of flow at the blade tip to alter the physical mechanism responsible for stall onset. This study focuses on the experimental performance of such a system. To do so, an axial compressor test bench was equipped with 40 actuators connected to an auxiliary pressurised air supply system. They were able to generate high-speed jet blowing just at the tip of the rotor blades. The opening of each actuator was controlled by an electromagnetic valve. This allowed generating continuous or pulsed jets with frequencies up to 500 Hz at different duty cycles. The performance of the control system was investigated for various control strategies, where the injected flow rate, the injection angle, the number of injectors, the jet frequency and the duty cycle were systematically varied. This paper is concluded by a study of the energy balance of the system for various configurations. To the best of the authors’ knowledge, this constitutes a rarely seen analysis in the literature.

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