Chevron exhaust nozzle for a gas turbine engine

The present invention relates generally to gas turbine engines, and, more specifically, to reduction of exhaust noise and infrared (IR) signature. A gas turbine engine exhaust nozzle includes an exhaust duct for channeling a gas jet. A plurality of adjoining chevrons are disposed at an aft end of th...

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Bibliographische Detailangaben
Hauptverfasser: Brausch, John F, Janardan, Bangalore A, Barter, IV, John W, Hoff, Gregory E
Format: Patent
Sprache:eng
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Beschreibung
Zusammenfassung:The present invention relates generally to gas turbine engines, and, more specifically, to reduction of exhaust noise and infrared (IR) signature. A gas turbine engine exhaust nozzle includes an exhaust duct for channeling a gas jet. A plurality of adjoining chevrons are disposed at an aft end of the duct to define an exhaust outlet. Each of the chevrons is triangular in configuration, with a base, apex, side trailing edges converging therebetween, and radially opposite first and second surfaces bounded thereby. The trailing edges of adjacent chevrons are spaced laterally apart to define respective diverging slots disposed in flow communication with the duct. The chevrons have a concave contour axially between the bases and apexes which promotes jet mixing through the slots.