Abstract: A lip of an air inlet of a turbojet pod intended to be fastened to an air inlet downstream structure includes at least one electric heating element for defrosting. The electric heating element being fitted with at least one electrical connector able to be connected to at least one corresponding electricity supply connector of the downstream structure. The lip breaks down into at least two identical structures set end-to-end on a periphery of the air inlet.

Abstract: This nacelle (201) for an aircraft turbojet includes an internal downstream structure (13) and an external downstream structure (15) delimiting an interior flow channel (14) for a secondary flow generated by the turbojet, the external downstream channel comprising at least one distribution line (18, 19a, 19b, 20) terminating at the outlet of the turbojet and being intended to be connected to a sound-reducing fluid supply source arranged upstream from the external downstream structure. This external downstream structure (15) is equipped with a thrust reversal device. The distribution line includes at least one supply line (19a, 19b) capable of ensuring the passage of said fluid from said supply source towards the outlet of the turbojet at least when said reversal device is in its off position.

Abstract: This invention relates to a nacelle for bypass engine with a high bypass ratio comprising an interior flow channel for a secondary flow generated by the bypass engine and having an external structure provided with a reverse thrust device capable of alternately shifting from a closed position in which it enables circulation of the direct-jet secondary flow inside the interior channel, to an open position in which it uncovers an opening in the external structure so as to enable reorientation of the secondary flow in an angled flow via activation of the reverse thrust means; in open position, the reverse thrust device partially blocks the interior channel so as to provide a leakage section therein, enabling circulation of a controlled leakage flow, said nacelle being characterized in that, when the thrust reversal device is in open position and has an angled-jet reversal section and a leakage section through the interior channel the sum of which is substantially equal to a direct-jet secondary flow discharge sec

Abstract: The invention relates to a method of producing and checking a double-resonator honeycomb acoustic panel. The aforementioned panel is characterised in that, following the assembly of the two honeycombs and the partition and prior to the assembly of at least one of the two liners, the perforation rate of said partition is checked by scanning same with digital camera. The successive images thus obtained are transmitted to a computer which determines the perforation rate T of the partition by applying formula T=N1/N, wherein N1 is the number of pixels that correspond to the holes and N is the number of pixels in the image.

Abstract: A bypass turbojet-engine thrust reverser comprises at least one hollow, pivoting door (3) with an inner conduit (10), defined between an outer structure (4) of the door (3) and an inner structure (5) of the door (3), which guides flow through the door (3) when the door (3) is in a reverse thrust position. At least a downstream part of the outer structure (4) of the door (3) is independent of and displaceable relative to the inner structure (5) of the door (3) and is driven in a centrifugal direction relative to the inner structure (5) by a mechanical drive system such that a downstream exhaust cross-section (S2) of the inner conduit (10), which is less than an intake cross-section (S1) of the inner conduit (10) when the door (3) is in a forward thrust position, is at least equal to the intake cross-section (S1) when the door (3) is in the reverse thrust position.

Abstract: A thrust reverser for a turbo-fan type turbojet-engine includes hollow, scoop-type pivoting doors (3) which, in the forward-thrust mode, are integrated into the engine and fan cowling and which, in the reversed-thrust mode, constitute scoop type flow deflecting baffles. A movable upstream visor (23), when in the forward-thrust mode, is situated between the upstream edge of the door (3) and the fixed upstream structure (6) covering the downstream structure of the forward frame (8) of the thrust reverser. The control-driven upstream visor (23) pivots about a pivot mounted on the fixed thrust reverser structure and, in the thrust-reversal mode, uncovers the downstream edge of the structure of the forward frame structure (8) and presents an aerodynamic surface to guide the reverse-thrust flow.

Abstract: The invention relates to a bypass turbojet engine having pivoting, hollow thrust reverser doors which, in the forward thrust configuration, are integrated into the external engine cowling and which, in the reverse thrust configuration, constitute scoop baffles that deflect exhaust air flow. A movable deflector baffle cooperates with each door such that, when the door is opened towards a thrust reversing direction, the baffle moves above an outer surface of the outer panel of the door in such a way that undesired interference between the exhaust flow moving through the door and the flow deflected by the outer surface of the door is minimized or avoided.

Abstract: A thrust reverser is disclosed in which a panel is pivotally attached to the cowling downstream of the movable thrust reverser door and is connected to the door such that movement of the thrust reverser door causes the panel to pivot about its attachment to the cowling. When the door is in its forward thrust position, the inner wall of the door and an inner wall of the panel form a portion of the boundary of the duct through which pass pressurized gases. The pressurized gases exert forces on the inner wall of the door and the inner surface of the panel such that the forces urge the thrust reverser door toward its forward thrust position. Thus, the thrust reverser door is prevented from being inadvertently deployed toward its reverse thrust position even upon failure or malfunction of the door locking or latching mechanisms.