Please use this identifier to cite or link to this item: http://dx.doi.org/10.14279/depositonce-38
Main Title: Review: Active Control of Shock-associated Unsteady Flow Phenomena in Aeroengines - Suppression Techniques for Transonic Cascade Flutter and Supersonic Jet Noise -
Author(s): Watanabe, Toshinori
Type: Preprint
Language Code: en
Abstract: Active control techniques for cascade flutter suppression and supersonic jet noise reduction were studied in the University of Tokyo. For flutter suppression, piezoelectric devices were installed on the blade surfaces. The active oscillation of the trailing edge of a blade was found to suppress the flutter instability in the numerical analysis. The effect was qualitatively confirmed in a trial experiment. For jet noise reduction, the technique of microjet injection was experimentally studied. The microjet could provide quite effective reduction of shock associated noise through the suppression of jet oscillation. The present paper briefly intro-duces these studies.
URI: http://depositonce.tu-berlin.de/handle/11303/195
http://dx.doi.org/10.14279/depositonce-38
Issue Date: 10-Sep-2014
Date Available: 7-Oct-2014
Notes: Presented at the Conference Active Flow and Combustion Control 2014, September 10-12 2014, Berlin, Germany
Appears in Collections:Technische Universität Berlin » Disziplinübergreifende Projekte (SFB, TR etc.) » SFB 1029 - Turbin » Proceedings of the Conference "Active Flow and Combustion Control 2014"

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