Tabbed nozzle for jet noise suppression
AssigneeUnited Technologies Corporation
InventorsDouglas C. Mathews, John K. C. Low
Life of this patent
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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.
Claims6
An exhaust nozzle system in a gas turbine engine for suppressing jet noise, the engine having a longitudinally extending central axis, concentric inner and outer flow paths for carrying inner and outer fluid flow streams through the engine, an inner and outer nozzle to discharge the inner and outer flow streams to ambient, at least one of the nozzles comprising:
- an arrangement of tabs disposed circumferentially about the nozzle, the arrangement of tabs comprising a repeated sequence of tabs, wherein the sequence includes tabs directed radially outward from the exhaust nozzle with respect to said central axis, tabs directed radially inward from the exhaust nozzle with respect to said central axis, and continuous tabbed extensions of the nozzle therebetween, such that the tabs create vortices which pull into mixing engagement the nozzle flow streams and a portion of ambient air.
Dependencies are inferred from the claim text.