Abstract: A rear portion of a convergent-divergent nozzle turbojet engine includes a device for controlling the position of a divergent flap relative to that of a convergent flap, including a first connecting rod having a first end portion hinged to the convergent flap and an opposite second end portion, a second connecting rod having a first end portion hinged to the divergent flap and an opposite second end portion, and a third connecting rod having a first end portion hinged to a synchronization ring and an opposite second end portion. The second end portion of the first connecting rod is hinged to the second end portion of the second connecting rod and/or to the second end portion of the third connecting rod, and the second end portion of the third connecting rod is hinged to the second end portion of the second connecting rod.

Abstract: A rear part for a turbojet engine includes a variable-geometry nozzle in which a convergent flap is provided with a lever supporting a bearing roller arranged axially between an upstream bearing wall and a downstream bearing wall, which are rigidly secured to a movable part capable of moving axially on command with respect to an upstream stator structure in such a way that the bearing roller is free to move with respect to the upstream and downstream bearing walls in a radial direction. During a downstream movement of the movable part, the upstream bearing wall pushes the lever to pivot a downstream end of the convergent flap towards the longitudinal axis. Operation of the drive mechanism for moving the movable part can thus be optimized while limiting the size and the mass of the mechanism for controlling the flaps.

Abstract: In a convergent-divergent flap pair for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap and the divergent flap including respective ducts for circulation of cooling air connected to one another to allow cooling of each of the flaps. The duct of the divergent flap includes an impingement cooling cavity defined by two walls of lateral ends provided with air passage orifices through which the impingement cooling cavity opens towards the outside.

Abstract: In a convergent-divergent flap pair for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap and the divergent flap include respective cooling-air ducts connected to one another through air passage openings formed in respective contact surfaces of the convergent flap and of the divergent flap arranged facing one another.

Abstract: In a convergent-divergent flap pair for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap and the divergent flap include respective cooling-air ducts connected to one another through air passage openings formed in respective contact surfaces of the convergent flap and of the divergent flap arranged facing one another.

Abstract: A drive pinion of an air/oil separator of an accessory gearbox of a turbomachine, the air/oil separator being configured to be supplied at the input by an air flow to de-oil and to supply at the output, on the one hand, a de-oiled air flow and, on the other hand, an oil flow by centrifugation, the pinion being configured to drive the separator rotationally along an axis of rotation, the pinion being mounted facing a passage opening of the separator, the pinion comprising at least one guiding opening traversing the web plate defining at least one guiding surface inclined with respect to the axis of rotation in such a way as to guide along the axis an air flow to de-oil into the separator or a de-oiled air flow out of the separator via the guiding opening of the pinion.

Abstract: In a convergent-divergent flap pair for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap and the divergent flap including respective ducts for circulation of cooling air connected to one another to allow cooling of each of the flaps. The duct of the divergent flap includes an impingement cooling cavity defined by two walls of lateral ends provided with air passage orifices through which the impingement cooling cavity opens towards the outside.

Abstract: The invention relates to a lead-through arm (30) for the auxiliaries of a turbomachine, intended to be mounted in a substantially radial direction of the turbomachine. The lead-through arm (30) comprises two fairing walls (32) connected at one of the axial ends thereof by a connecting element (34) and a transverse firewall (38) connecting the two fairing walls (32), characterised in that it comprises a firebreak member (36) disposed in the radial direction, said member (36) being elastically deformable and being inserted axially, and constrained elastically, between an axial end of the firewall (38) and the connecting element (34).

Abstract: A dual-flow turbomachine generally includes a cooling and turbine clearance control system located in a primary air flow path of the turbomachine, supplied a scoop configured to take air from a secondary air flow path arranged around the primary air flow path through an air inlet of the scoop, where the scoop may further include one wall configured to be arranged in the extension of a wall of the secondary flow path, and further where the air inlet may be formed in and flush with the wall.

Abstract: The invention relates to a jet pump collector comprising a convergent duct extending along the longitudinal axis (AX) and comprising an intake opening for a fluid to be withdrawn, this convergent duct having a restriction shape terminated by a reduced end having a smaller cross-section than its intake opening. This convergent duct is equipped with a tube (17) orientated perpendicular to the longitudinal axis longitudinal (AX), this tube (17) comprising an outer portion extending outside of the convergent duct and being terminated by an intake opening (31) for a propulsion fluid, and an inner portion extending in the convergent duct and comprising a plurality of distribution openings (18, 19) for the propulsion fluid which are orientated towards the reduced end.

Abstract: A method for transporting a turbine engine held by a transport kit by a carriage. The transport kit connected to a connection member hoists the engine to connect to an aircraft fuselage. The transport kit is a structure which includes a hoisting interface (328) arranged on a rigid hoisting arm (318) which extends over the turbine engine and is connected to a rigid transport arm (316) which extends over a lateral side of the turbine engine. The transport arm is connected to at least two engine mounts (340) solid with the turbine engine. The transport arm (316), or one of the engine mounts connected to the transport arm, includes a transport interface (324) that can be supported by a bearing element (332) of a truck (326) used for transporting the turbine engine.

Abstract: The invention relates to a lead-through arm (30) for the auxiliaries of a turbomachine, intended to be mounted in a substantially radial direction of the turbomachine. The lead-through arm (30) comprises two fairing walls (32) connected at one of the axial ends thereof by a connecting element (34) and a transverse firewall (38) connecting the two fairing walls (32), characterised in that it comprises a firebreak member (36) disposed in the radial direction, said member (36) being elastically deformable and being inserted axially, and constrained elastically, between an axial end of the firewall (38) and the connecting element (34).

Abstract: A drive pinion of an air/oil separator of an accessory gearbox of a turbomachine, the air/oil separator being configured to be supplied at the input by an air flow to de-oil and to supply at the output, on the one hand, a de-oiled air flow and, on the other hand, an oil flow by centrifugation, the pinion being configured to drive the separator rotationally along an axis of rotation, the pinion being mounted facing a passage opening of the separator, the pinion comprising at least one guiding opening traversing the web plate defining at least one guiding surface inclined with respect to the axis of rotation in such a way as to guide along the axis an air flow to de-oil into the separator or a de-oiled air flow out of the separator via the guiding opening of the pinion.

Abstract: The invention relates to a jet pump collector comprising a convergent duct extending along the longitudinal axis (AX) and comprising an intake opening for a fluid to be withdrawn, this convergent duct having a restriction shape terminated by a reduced end having a smaller cross-section than its intake opening. This convergent duct is equipped with a tube (17) orientated perpendicular to the longitudinal axis longitudinal (AX), this tube (17) comprising an outer portion extending outside of the convergent duct and being terminated by an intake opening (31) for a propulsion fluid, and an inner portion extending in the convergent duct and comprising a plurality of distribution openings (18, 19) for the propulsion fluid which are orientated towards the reduced end.

Abstract: The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings and means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.

Abstract: A dual-flow turbomachine generally includes a cooling and turbine clearance control system located in a primary air flow path of the turbomachine, supplied a scoop configured to take air from a secondary air flow path arranged around the primary air flow path through an air inlet of the scoop, where the scoop may further include one wall configured to be arranged in the extension of a wall of the secondary flow path, and further where the air inlet may be formed in and flush with the wall.

Abstract: An aeronautic engine including: a housing made of electrically insulating material and including at least one metallic piece; a structural piece of the engine including metallic material and connected to the housing; and an equipment fixed to the housing, is provided. The equipment is connected to the structural piece by the metallic piece by an electrically conductive connecting path.

Abstract: The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings and means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.

Abstract: Structure (310) for transporting and hoisting a turbomachine (312), said structure comprising a hoisting interface (328) arranged on a rigid hoisting arm (318) which extends over the turbomachine and is connected to a rigid transport arm (316) which extends over a lateral side of the turbomachine, this transport arm being connected to at least two engine mounts (340) solid with the turbomachine. The transport arm (316), or one of the engine mounts connected to this transport arm, comprises a transport interface (324) that can be supported by a bearing element (332) of a truck (326) used for transporting the turbomachine.

Abstract: An arrangement of a tank of lubrication liquid for an aircraft turbomachine, under a nacelle cowling covering the turbomachine, is provided. The tank is arranged in the volume located between the turbomachine and the nacelle cowling. The nacelle cowling includes an opening for access to the volume. The tank is fastened to an internal face of a panel closing off the opening. The unit formed by the panel and the tank is added onto the nacelle cowling and is able to be mounted and dismounted from the nacelle cowling.