Abstract: A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.

Abstract: A control device for controlling a variable section nozzle of an aircraft power plant, the variable section nozzle including one or several movable parts capable of modifying the nozzle section and connected by a mechanical transmission chain to an actuator. The control device includes a system for regulating the power plant connected to a control member configured to control the actuator. The control device includes a single control member, an immobilization unit configured to immobilize all the movable parts which are deactivated only when the regulation system controls the positional change of the movable part or parts and a determination unit configured to determine the actual position of the movable part or parts.

Abstract: A system for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft, that includes first means for heat exchange between lubrication circuits of at least two of the aforementioned apparatuses and a heat-carrier fluid contained in a closed circuit, a second means for heat exchange between the heat-carrier fluid and at least one coolant, the first heat exchange means being arranged locally at each of the aforementioned apparatuses, the second heat exchange means being remote from the aforementioned first means, the closed circuit extending between at least two of the aforementioned apparatuses and the aforementioned second means.

Abstract: An aircraft nacelle in which a power plant is arranged delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can have an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position.

Abstract: A power plant includes a nacelle with a bypass turbojet engine having a ducted fan with a low compression ratio. A secondary flow, drawn in and accelerated by the fan, is channeled through a secondary duct installed in the nacelle between the inner surface of the nacelle and the outer surface of the turbojet, toward a fan nozzle. The power plant has at least two moving parts on either side of a vertical plane of symmetry of the nacelle, at least one moving part being able to adopt one of a discrete number of positions, the moving part containing or releasing a portion of the secondary flow, depending on the moving part's position. A control unit controls a different displacement of each of the moving parts between their possible positions in order to create asymmetry of the moving parts relative to the vertical plane of symmetry.

Abstract: The invention relates to a nacelle for a variable area nozzle propulsion unit comprising a nacelle, hosting a turbofan jet engine, of dual-flow type. The propulsion unit includes: a fixed part, carried by the inboard half-nacelle defined by a vertical plane of symmetry of the nacelle; and a movable part carried by the outboard half-nacelle. The moving part containing or releasing part of the secondary flow, depending on its open or closed position. The moving part being able to move to a discrete number of positions including a closed position, an open position, and one or more intermediate positions so as to provide variable area nozzle configurations for the turbofan engine.

Abstract: A turbojet for an aircraft includes an engine housed in a nacelle and a thermal exchanger that can be traversed by a hot fluid designed to be cooled by thermal exchange with a cold fluid external to the thermal exchanger. The thermal exchanger is disposed in an internal volume of the nacelle, between an internal wall of the nacelle and an external wall of the engine, in such a way as to present two thermal exchange surfaces in the flow of the air stream from the turbojet. The disclosed embodiments also relate to an aircraft equipped with such a jet turbine engine.

Abstract: A turbojet engine for an aircraft that includes an engine provided in a nacelle and at least one heat exchanger for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting the aforementioned partially-cooled hot flow into the aforementioned propulsion system, wherein at least one heat exchanger is a radial heat exchanger extending in the lower portion of the turbojet engine at a lower branching of the turbojet engine.

Abstract: A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening.

Abstract: An articulation device connects a door (46) of an aircraft nacelle (30), the nacelle (30) including an external wall called a fairing including at least one opening (44) adapted to be closed by at least the door (46). The articulation device includes at least one arm (56) connected by a first pivotal axle (58) to the nacelle (30) and by a second pivotal axle (60) to the door (46), the two pivotal axles (58, 60) being substantially parallel.

Abstract: A system for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft, that includes first means for heat exchange between lubrication circuits of at least two of the aforementioned apparatuses and a heat-carrier fluid contained in a closed circuit, a second means for heat exchange between the heat-carrier fluid and at least one coolant, the first heat exchange means being arranged locally at each of the aforementioned apparatuses, the second heat exchange means being remote from the aforementioned first means, the closed circuit extending between at least two of the aforementioned apparatuses and the aforementioned second means.

Abstract: A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening.

Abstract: An aircraft nacelle in which a power plant is arranged and delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position. Each flap includes articulation elements with a first pivoting axis and a second pivoting axis, whereby the pivoting axes are essentially parallel to the vertical median axis of the nacelle.

Abstract: A turbojet for an aircraft includes an engine housed in a nacelle and a thermal exchanger that can be traversed by a hot fluid designed to be cooled by thermal exchange with a cold fluid external to the thermal exchanger. The thermal exchanger is disposed in an internal volume of the nacelle, between an internal wall of the nacelle and an external wall of the engine, in such a way as to present two thermal exchange surfaces in the flow of the air stream from the turbojet. The disclosed embodiments also relate to an aircraft equipped with such a jet turbine engine.

Abstract: The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet.

Abstract: The invention relates to a nacelle, for an aircraft jet engine (10) having a high bypass ratio, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle (12) including a wall (24) concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct (26) for a fluid internal flow having, at the downstream end of the nacelle wall, a flow outlet passage section, characterised in that the nacelle includes displacement means (40) for controllably displacing a portion (24b) of the nacelle wall in order to modify the section of the flow outlet passage, wherein said displacement generates in the nacelle wall at least one longitudinally extending opening (28), the nacelle including a device (30) for forming a fluid barrier (fi) extending along a portion at least of the longitudinal extent of said at least one opening (28) in order to counteract the natural exhaust through said at least one opening of a portion of the so-called trailing flow.

Abstract: According to the invention, the internal wall of the air intake (2) and the housing of the fan (3) form a single tubular piece (30) made from a fibre/resin composite material.

Abstract: The object of the invention is a process whose purpose is to reduce, cancel or reverse the thrust generated by at least one air flow exiting from a propulsion unit of an aircraft by deflecting at least a portion of the flow that is able to assist the thrust, characterized in that it consists in injecting at the level of the propulsion unit a fluid called a thrust reversal fluid to deflect by an entrainment effect, from the inside of the nacelle toward the outside of the nacelle, at least a portion of the flow that is able to assist the thrust.

Abstract: An articulation device connects a door (46) of an aircraft nacelle (30), the nacelle (30) including an external wall called a fairing including at least one opening (44) adapted to be closed by at least the door (46). The articulation device includes at least one arm (56) connected by a first pivotal axle (58) to the nacelle (30) and by a second pivotal axle (60) to the door (46), the two pivotal axles (58, 60) being substantially parallel.

Abstract: The resistance to internal charring of molded styrene-butadiene latex foam rubber when exposed to a lit cigarette is improved by incorporating from about 10 to 30 parts by dry weight, per hundred parts by dry weight of latex of a compound selected from the group consisting of an organic phosphate of the formula ##STR1## wherein R is a C.sub.6-12 alkyl radical or a phenyl radical, which is unsubstituted or substituted by a C.sub.1-4 alkyl radical, butyl benzyl phthalate, and a mixture thereof.