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An aircraft engine having a longitudinal axis, including a wall surrounding a gas stream that is ejected at a downstream end of the wall along the longitudinal axis, wherein a plurality of conduits distributed at the periphery of the downstream end of the wall are each capable of ejecting, via an ou

An aircraft engine having a longitudinal axis, including a wall surrounding a gas stream that is ejected at a downstream end of the wall along the longitudinal axis, wherein a plurality of conduits distributed at the periphery of the downstream end of the wall are each capable of ejecting, via an outlet orifice, a fluid jet in the form of a sheet, in such a way that the jets thus ejected each form a fluid perturbation around the ejected gas stream.

대표청구항 ▼

1. An aircraft engine having a longitudinal axis, the aircraft engine comprising: a wall surrounding a gas stream that is ejected at a downstream end of the wall along the longitudinal axis, wherein a plurality of conduits distributed at the periphery of the downstream end of the wall are each capab

1. An aircraft engine having a longitudinal axis, the aircraft engine comprising: a wall surrounding a gas stream that is ejected at a downstream end of the wall along the longitudinal axis, wherein a plurality of conduits distributed at the periphery of the downstream end of the wall are each capable of ejecting, via an outlet orifice, a fluid jet in the form of a sheet, in such a way that the jets thus ejected each form a fluid perturbation around the ejected gas stream, and the outlet orifice is broader than an inlet orifice of the conduit. 2. The engine according to claim 1, wherein the outlet orifice of each conduit possesses an outlet cross section that is broader than it is high, in such a way that a fluid sheet extends perpendicular to the height, the height being considered in radial direction relative to the longitudinal axis. 3. The engine according to claim 1, wherein the downstream end of the wall is provided with a plurality of chevrons distributed at the periphery of the wall in order to form an acoustically attenuating mechanical device. 4. The engine according to claim 3, wherein the conduits are associated with the chevrons, which give the downstream end of the wall a serrated shape including a succession of tips and roots. 5. The engine according to claim 4, wherein outlet orifices of the conduits are disposed at the tips of the chevrons. 6. The engine according to claim 4, wherein outlet orifices of the conduits are disposed in the roots of the chevrons. 7. The engine according to claim 4, wherein outlet orifices of the conduits are disposed in inclined portions of the chevrons each connecting a tip to an adjacent root. 8. The engine according to claim 1, wherein outlet orifices of the conduits are shaped so as to eject fluid jets inclined toward the longitudinal axis at a penetration angle. 9. The engine according to claim 1, wherein outlet orifices of the conduits are shaped so as to eject fluid jets forming what is known as a sliding angle with the longitudinal axis in a view projected onto a plane perpendicular to a transverse plane. 10. An aircraft, including at least one aircraft engine according to claim 1. 11. The engine according to claim 1, wherein the conduit is shaped like a forge blower. 12. The engine according to claim 1, wherein a cross-section of the outlet orifice has a height between 0.2% and 2% of a diameter of the engine. 13. The engine according to claim 12, wherein a width of the outlet orifice is approximately 10 times the height of the outlet orifice.