S. Fleeter, J.A. Minter

Turbomachine discrete frequency tones are a significant environmental concern. These tones are generated by periodic blade row interactions, with only specific circumferential acoustic modes generated. This research is directed at active control of discrete frequency noise generated by subsonic blade rows through cancellation of the propagating acoustic waves, accomplished by utilizing airfoil surface mounted oscillating actuators to generate additional control propagating pressure waves. These control waves interact with the propagating acoustic waves, thereby canceling the acoustic waves and thus the far field discrete frequency tones. A series of experiments are described directed at investigating the fundamentals of this active discrete frequency noise control technique as well as verifying basic modeling assumptions. These experiments are performed in the Purdue Annular cascade Facility. Both an isolated vane and a three vane row are utilized, with the stator vane actuators including both oscillating flaps and surface pistons.

First Joint CEAS/AIAA Aeroacoustics Conference, München, 1995

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1995, 1995-01, First Joint CEAS/AIAA Aeroacoustics Conference - Proceedings; S.195-204; 1995; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics

Bibliothek

1995