Unit cell resonator networks for turbomachinery bypass flow structures

An acoustic attenuation structure for a gas turbine engine includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first...

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Bibliographische Detailangaben
Hauptverfasser:	Reimann, Craig Aaron, Winkler, Julian, Mendoza, Jeffrey Michael, Homma, Kenji, Reba, Ramons A
Format:	Patent
Sprache:	eng
Schlagworte:	ACOUSTICS ACOUSTICS NOT OTHERWISE PROVIDED FOR AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING,NOISE OR OTHER ACOUSTIC WAVES IN GENERAL MUSICAL INSTRUMENTS PHYSICS SOUND-PRODUCING DEVICES WEAPONS
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Beschreibung
Zusammenfassung:	An acoustic attenuation structure for a gas turbine engine includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first axial tube, each of the first axial tube and the second axial tube being in fluid communication with one another through the first central body.