Patent ID: 8925295
Filing Date: 2015-01-06
Classification: B64D,F02K,Y02T

Abstract:
1. An air discharging device for an aircraft double-flow turbine engine, comprising a fixed structure having an internal surface intended to outwardly delimit an annular flow space for a secondary flow of a turbine engine downstream of a fan thereof, as well as an external surface intended for fairing the turbine engine, the device also comprising at least one door displaceable between an open position and a closed position of a corresponding orifice of the fixed structure that passes through the internal and external surfaces of the this fixed structure, each door comprising two valves, an internal one and an external one, which respectively extend said internal and external surfaces of the fixed structure in said closed position, and which delimit between them a conduit intended, in the open position, for guiding a portion the secondary flow outwards in the aftward direction, wherein the internal and external valves of each door are integral with each other and are hinged around a pivot axis remote from the internal valve of the door in a direction going from the external valve toward the internal valve of the door when the door is in the closed position, so that in the open position of the door, the upstream end of said internal valve protrudes from an inner side relative to said internal surface of the fixed structure of the device, the downstream end of said external valve protrudes from an external side relative to said external surface of said fixed structure, and said internal valve is spaced away from said fixed structure so that an air passage exists downstream of said internal valve, between the internal valve and said fixed structure.