DISPOSITIF POUR ATTENUER LE BRUIT EMIS PAR LE JET D'UN MOTEUR DE PROPULSION D'UN AERONEF.

摘要

A gas exhaust nozzle for aircraft propulsion includes at least a downstream part with a trailing edge of chevron type formed of chevrons distributed along the periphery of the nozzle. Each chevron extends downstream between an upstream transverse plane and a downstream transverse plane with free edges oriented in two converging downstream directions and defining the trailing edge. The chevrons generate vortices at the boundary of the jet emitted by the nozzle. The gas exhaust nozzle includes a device to inject auxiliary gas jets upstream of the free edges of the chevrons in the main jet through orifices placed upstream of the upstream plane in such a way as to discharge upstream of the upstream plane of the chevrons to generate the vortices upstream of the free edges of the chevrons.