Air outlet for a nacelle for an aircraft bypass turbojet engine comprising a guiding device to favor a reverse thrust phase

An aircraft propulsion assembly comprising:

• an aircraft bypass turbojet engine comprising a primary radially inner flow path and a secondary radially outer flow path in which a secondary air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a reverse thrust phase, wherein a plurality of guide vanes extend radially into the secondary flow path, a nacelle mounted on the turbojet engine and extending around the longitudinal axis of said turbojet engine, said nacelle comprising an air outlet at a downstream end, said air outlet comprising a downstream inner wall and a downstream outer wall opposite to the downstream inner wall and configured to guide an outer air flow circulating from upstream to downstream, said downstream inner wall and said downstream outer wall both connected downstream to a trailing edge,
• a plurality of radial through apertures spread out on a circumference of said air outlet, each radial through aperture comprising an inner open face defined by an upstream edge and a downstream edge formed in said downstream inner wall and an outer open face defined by an upstream edge and a downstream edge formed in said downstream outer wall, wherein each radial through aperture is axially positioned at a location between said guide vanes and said trailing edge, and
• each radial through aperture having a guiding device comprising an inner moveable member having a single pivot point at said inner open face adjacent the upstream edge or the downstream edge and an outer moveable member having a single pivot point at said outer open face adjacent the upstream edge or the downstream edge, said guiding device movable between:
• a closed position in which the inner moveable member closes off said inner open face of said downstream inner wall and the outer moveable member closes off said outer open face of said downstream outer wall, said radial through aperture defining a cavity delimited by said inner moveable member and said outer moveable member to conserve performances in the thrust phase,
• an open position in which said inner moveable member and said outer moveable member are configured to allow said outer air flow in said radial through aperture from said outer open face to said inner open face to increase the reverse air flow admitted into the secondary flow path to favor a reverse thrust phase;
• and
• wherein said guiding device comprises a displacement member for displacing the inner moveable member and the outer moveable member between the closed position and the open position.

An aircraft propulsion assembly comprising:

• an aircraft bypass turbojet engine comprising a primary radially inner flow path and a secondary radially outer flow path in which a secondary air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a reverse thrust phase, wherein a plurality of guide vanes extend radially into the secondary flow path,
• a nacelle mounted on the turbojet engine and extending around the longitudinal axis of said turbojet engine, said nacelle comprising an air outlet at a downstream end, said air outlet comprising a downstream inner wall and a downstream outer wall opposite to the downstream inner wall and configured to guide an outer air flow circulating from upstream to downstream, said downstream inner wall and said downstream outer wall both connected downstream to a trailing edge,
• a plurality of radial through apertures spread out on a circumference of said air outlet, each radial through aperture comprising an inner open face defined by an upstream edge and a downstream edge formed in said downstream inner wall and an outer open face defined by an upstream edge and a downstream edge formed in said downstream outer wall, wherein each radial through aperture is axially positioned at a location between said guide vanes and said trailing edge, and
• each radial through aperture having a guiding device comprising an inner moveable member having a single pivot point at said inner open face adjacent the upstream edge or the downstream edge and an outer moveable member having a single pivot point at said outer open face adjacent the upstream edge or the downstream edge, said guiding device movable between:
• a closed position in which the inner moveable member closes off said inner open face of said downstream inner wall and the outer moveable member closes off said outer open face of said downstream outer wall, said radial through aperture defining a cavity delimited by said inner moveable member and said outer moveable member to conserve performances in the thrust phase,
• an open position in which said inner moveable member and said outer moveable member are configured to allow said outer air flow in said radial through aperture from said outer open face to said inner open face to increase the reverse air flow admitted into the secondary flow path to favor a reverse thrust phase,
• wherein said guiding device comprises a displacement member for displacing the inner moveable member and the outer moveable member between the closed position and the open position, and
• wherein the displacement member is positioned upstream of the upstream edges of the inner open face and the outer open face.