Tabbed nozzle for jet noise suppression
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United States of America Patent
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Nov 13, 2001
Grant Date -
N/A
app pub date -
Sep 4, 1998
filing date -
Sep 4, 1998
priority date (Note) -
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Abstract
The present invention relates to a gas turbine engine exhaust nozzle for suppressing jet noise. The nozzle has an arrangement of tabs 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. In addition, various construction details are developed for the tab arrangement including tabs that are directed radially inwardly and outwardly, and tabs that are continuous with the nozzle duct therebetween.
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