Air discharging device for an aircraft double-flow turbine engine

An air discharging device (20) for an aircraft double-flow turbine engine, comprising a fixed structure (22) having an internal surface (12) intended to outwardly delimit an annular flow space for a secondary flow (76) of a turbine engine downstream of a fan thereof, as well as an external surface (14) intended for fairing the turbine engine, the device also comprising at least one door (24) displaceable between an open position and a closed position of a corresponding orifice (30) of the aforementioned fixed structure (22) that passes through the internal (12) and external (14) surfaces of this fixed structure (22), each door (24) comprising two valves, an internal one (26) and an external one (28), which respectively extend said internal (12) and external (14) surfaces of the fixed structure (22) in said closed position, and which delimit between them a conduit (68) intended, in the open position, for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction,

• wherein the internal (26) and external (28) valves of each door (24) are integral with each other and are hinged around a pivot axis (58) remote from the internal valve (26) of the door (24) in a direction going from the external valve (28) toward the internal valve (26) of the door (24) when the latter is in the closed position, so that in the open position of the door, the upstream end of said internal valve (26) protrudes from the inner side relative to said internal surface (12) of the fixed structure (22) of the device, the downstream end of said external valve (28) protrudes from the external side relative to said external surface (14) of said fixed structure (22), and said internal valve (26) is spaced away from said fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).