Tabbed nozzle for jet noise suppression

The present invention relates to a gas turbine engine exhaust nozzle for suppressing jet noise. The nozzle 20 has an arrangement of tabs 44, 52 that extend in radially inward and outward directions. The tabs cause the formation of vortices which pull into mixing engagement the exhaust gas streams fr...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	LOW, JOHN K.C, MATHEWS, DOUGLAS C
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	The present invention relates to a gas turbine engine exhaust nozzle for suppressing jet noise. The nozzle 20 has an arrangement of tabs 44, 52 that extend in radially inward and outward directions. The tabs cause the formation of vortices which pull into mixing engagement the exhaust gas streams from the core and fan ducts and the ambient air. Tabs 48 that are continuous with the nozzle duct may be arranged between the angled tabs 44, 52. The tabs 44, 52 extend at an angle of up to 45 DEG , more preferably up to 30 DEG .