Patent ID: 8037687

Claim:
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.