OUTLET NOZZLE PROVIDED WITH CHEVRONS FOR AERONAUTICAL THRUSTER

The invention relates to an outlet nozzle (12') for an aeronautical thruster arranged downstream of at least one stator vane (32) of the thruster, a trailing edge (122') of the outlet nozzle comprising a plurality of chevrons (4) distributed circumferentially around a central axis, said tr...

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Bibliographische Detailangaben
Hauptverfasser:	GEA AGUILERA, Fernando, BODARD, Guillaume, Michel, Marcel, BOITEUX, Jean-Michel, Daniel, Paul
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 invention relates to an outlet nozzle (12') for an aeronautical thruster arranged downstream of at least one stator vane (32) of the thruster, a trailing edge (122') of the outlet nozzle comprising a plurality of chevrons (4) distributed circumferentially around a central axis, said trailing edge (122') comprising a first trailing edge pattern (M1) extending over an angular range AO including the at least one stator vane (32), the first pattern (M1) being a portion of the trailing edge comprising at least one chevron (4) or being a portion of the trailing edge not having a chevron, and a second trailing edge pattern (M2) extending over an angular range AO' not including the at least one stator vane (32), the second pattern (M2) being a portion of the trailing edge comprising at least one chevron (4) or being a portion of the trailing edge not having a chevron (4), and being separate from the first pattern (M1).