Patent ID: 9422887
Filing Date: 2016-08-23
CPC Classification: F02K,F05D

Claim Text:
1. A gas exhaust nozzle for aircraft propulsion, comprising: at least a downstream part with a trailing edge of chevron type, formed of chevrons distributed along a periphery of the nozzle, the nozzle having a longitudinal axis, each chevron extending downstream and being entirely delimited between an upstream transverse plane and a downstream transverse plane, the upstream transverse plane being perpendicular to the longitudinal axis, said trailing edge defined by a plurality of free edges and each chevron including a first free edge and a second free edge, each chevron being rigidly connected to the nozzle via a fixed edge situated. in the upstream transverse plane, the first free edge and the second free edge of each chevron converging towards each other while extending from the fixed edge to the downstream transverse plane, each chevron including a first plane defining an intersection of the first free edge with the fixed edge, and a second plane defining an intersection of the second free edge with the fixed edge, the first plane and the second plane being perpendicular to the upstream transverse plane, the chevrons generating vortices at a boundary of a main jet emitted by the nozzle; and an injection device which injects auxiliary gas jets upstream of said free edges of the chevrons in the main jet through orifices separate from the chevrons, the orifices being placed adjacent to and upstream of said upstream plane in such a way as to discharge upstream of said upstream plane of th, chevrons to generate said vortices upstream of the free edges of the chevrons, wherein, for each respective chevron, one or two orifices are disposed circumferentially between the first plane and the second plane of the respective chevron.