Abstract: A device for sealing a space at a juncture between elements of a nacelle, the device being non-flammable by heat, having a predetermined shape, and having a proximal end configured to be inserted into the space to be sealed so as to seal it, and a distal end configured to be fastened to an element of the nacelle at a fire area.

Abstract: The invention relates to a de-icing and/or anti-icing system for the leading edge of an aircraft wing or for the lip (1) of the air intake of an aircraft engine, characterised in that it includes a plurality of infrared emitting members (13) arranged inside said leading edge or said lip (1), power supply means (17) for said emitters (13), and means (27) for controlling said power supply means (17).

Abstract: A lip assembly for an air inlet of a turbojet engine nacelle includes an inner surface, an external surface. A portion of the external surface is covered by an ice-repellent coating. In particular, the ice-repellent coating includes a piezoelectric actuator which vibrates the external surface and is combined into a matrix of the ice-repellent coating.

Abstract: The invention relates to a de-icing and/or anti-icing system for the leading edge of an aircraft wing or for the lip (1) of the air intake of an aircraft engine, characterised in that it includes a plurality of infrared emitting members (13) arranged inside said leading edge or said lip (1), power supply means (17) for said emitters (13), and means (27) for controlling said power supply means (17).

Abstract: The invention relates to a lip assembly (1) for the air inlet of a turbojet engine nacelle, that comprises an inner surface (9), an outer surface (11) and de-icing means, wherein the de-icing means includes an anti-ice coating (13) covering at least a portion of the outer surface (11), said anti-ice coating (13) including one or more piezoelectric actuators within the matrix of said coating (13). The invention also relates to a turbojet engine nacelle that comprises such a lip assembly (1).

Abstract: The invention relates to a dual-flow turbojet engine comprising an engine which is disposed in a nacelle and is provided with case which defines jointly with the said nacelle an annular passage through which a secondary flow supplied by a fan placed upstream of the engine can flow, a primary nozzle which is fixed to the case downstream of the engine, an internal wall for guiding the main hot flow supplied by the engine and an external wall contacting the secondary flow. Said invention is characterized in that sound attenuating means is provided for at least one part of the internal wall and the external wall is provided with means for cooling said internal wall.

Abstract: The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular passage for a secondary flow delivered by a fan, said pod having an air inlet upstream of the engine, thrust-reverser means in its middle section, and a common nozzle for ejecting both the primary flow and the secondary flow, the outlet of the nozzle being situated downstream from the engine, said thrust-reverser means being suitable for taking up an active position in which the secondary flow is diverted outwards and forwards from said pod, said nozzle having an enclosure defined by the inside and outside walls of said nozzle.

Abstract: The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular passage for a secondary flow delivered by a fan, said pod having an air inlet upstream of the engine, thrust-reverser means in its middle section, and a common nozzle for ejecting both the primary flow and the secondary flow, the outlet of the nozzle being situated downstream from the engine, said thrust-reverser means being suitable for taking up an active position in which the secondary flow is diverted outwards and forwards from said pod, said nozzle having an enclosure defined by the inside and outside walls of said nozzle.