DEVICE FOR REDUCING THE NOISE OF THE INTERACTION OF THE JET / PILON IN TURBO-REACTIVE ENGINES

摘要

1. An aircraft pylon for holding a two- or three-circuit turbojet engine (1), comprising an upper surface of the connection with the aircraft, two sides and a sole in its lower part, said pylon containing at least one part extending below flow from the nozzle (5) of the cold flow (3) of said turbojet engine and washed by the cold flow, characterized in that in its part passing in the cold flow outside the said nozzle, it contains at least one opening (8) located on one of the lateral sides of the said pylon, through which the air stream is injected into the gas stream or sucked in from the gas stream that circulates along its lateral sides. A pylon according to claim 1, in which the opening (8) is fed through a tube (9) associated with a scoop (1) that takes air in the cold stream (3) of the turbojet engine (1). A pylon according to claim 1, wherein the orifice (8) is fed through a tube (9) associated with an air bleed perforation downstream of the turbojet compressor (1). A pylon according to claim 1, wherein air is injected at a pressure that is at least 15% higher than the total pressure of said gas stream. A pylon according to claim 1, in which air is injected in a direction making up horizontally, at the level of said opening (8), an angle comprised between 30 ° and 90 ° with the axis of flow of the gas stream surrounding the turbojet engine. A pylon according to claim 1, in which air is injected in a direction making up vertically, at the level of said opening (8), an angle comprised between + 60 ° to -60 ° with a direction perpendicular to the lateral