Bypass turbomachine with reduction of jet noise
View Patent ↗In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.
1. A bypass turbomachine having a fan driven by a gas generator, an annular fan channel defined externally by a nacelle, and a primary annular channel for passing a flow of gas coming from the gas generator, the nacelle comprising from upstream to downstream:
a stationary air inlet sleeve;
two semi-cylindrical maintenance covers; and
two semi-cylindrical thrust reverser covers that are movable relative to said stationary air inlet sleeve by sliding in a direction parallel to the longitudinal axis of the turbomachine;
the turbomachine further comprising at least one air takeoff orifice in fluid communication with said annular fan channel, the orifice opening an air takeoff pipe housed inside said stationary air inlet sleeve of the nacelle, the air takeoff pipe opening out directly below a pylon fastening the nacelle under an airplane wing, into two air diffusion pipes, each of said two air diffusion pipes secured to one of each said two semi-cylindrical maintenance covers, each of said air diffusion pipes fluidly connected to an air injection pipe that is secured to one of said respective semi-cylindrical thrust reverser covers, said semi-cylindrical thrust reverser cover opening out towards the outside of the nacelle at the trailing edge thereof, each air injection pipe being capable of uncoupling from the corresponding air diffusion pipe on the corresponding semi-cylindrical thrust reverser cover sliding downstream.
2. A turbomachine according to claim 1 , wherein the semi-cylindrical maintenance covers are movable relative to the stationary air inlet sleeve by pivoting about hinges parallel to the longitudinal axis of the turbomachine and abutting the pylon, each of said two air diffusion pipes being capable of deforming during pivoting of the corresponding semi-cylindrical maintenance cover.
3. A turbomachine according to claim 2 , wherein each of said two air diffusion pipes is made of a flexible material.
4. A turbomachine according to claim 1 , wherein each of said two air injection pipes includes an endpiece at the upstream end of each air injection pipe that is conical.
5. A turbomachine according to claim 1 , further including a control valve mounted on the air takeoff pipe.