Abstract: A propulsive assembly for aircraft comprising an engine, a nacelle arranged around the engine and a pylon supporting the engine, the nacelle including two engine cowls and reversing cowls, each cowl having an internal skin, characterized in that at least one of the cowls of the nacelle comprises at least one box arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. This box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned.

Abstract: An aircraft pylon comprising a box-section primary structure and at least one tank positioned inside the primary structure. To facilitate mounting or demounting the tank, the pylon is equipped with a guide system configured to move the tank from its mounted position toward a through-hole, including a guide rail fastened to the primary structure and positioned above the tank and a guide pin fastened to the tank cooperating with the guide rail so that the tank is supported by the guide rail and is able to slide along the latter. This guide system contributes to simplifying manipulation of the tank when mounting or demounting the tank by at least partly compensating its weight and guiding the tank.

Abstract: An assembly of at least one extinguishing agent tank in the interior of an aircraft strut. The strut has an elongate chamber form extending in a longitudinal direction and includes a plurality of ribs which are spaced apart and arranged in parallel along the strut, each extending orthogonally to the longitudinal direction. The ribs are covered by lateral walls, at least one of the walls comprising a window opening into a space between two consecutive ribs, and via which a spherical extinguishing agent tank is installed in the interior of the strut. The assembly of the tank on the strut includes a frame arranged in the interior of the strut, facing the window and secured on each of the two consecutive ribs. The frame forms a support area on which the tank is supported. A system locks the extinguishing agent tank on the frame.

Abstract: A cold regulating valve for a heat exchanger system of an aircraft propulsion system, where the cold regulating valve includes an open frame which delimits an opening, two shutters with an external convex shape slidably mounted on the open frame between a closed position and an open position, a mechanism linked to the shutters and mobile between a first position and a second position, and wherein the mechanism moves the shutters from the closed position to the open position when it moves from the first position to the second position and vice versa, and an actuator acting on the mechanism to move it from the first position to the second position and vice versa. The specific embodiment of the cold regulating valve generates a low drag when the shutters are in a closed position.

Abstract: An enclosure containing an inerting gas and at least one liquid to be discharged. This enclosure comprises at least one orifice positioned in its lower part and a liquid discharging system positioned at the orifice. This liquid discharging system is configured to take up a closed state and an open state in which the system allows the liquid to flow towards the outside of the enclosure and includes at least one element that is elastically deformable depending on the pressure inside the enclosure and, depending on its deformation, controls the open or closed state of the liquid discharging system. This solution makes it possible to achieve simple and automatic regulation of the volume of the liquid in the enclosure, without a sensor. An aircraft including at least one such enclosure is also provided.

Abstract: An aircraft propulsion assembly having an engine, a nacelle positioned around the engine, an annular duct delimited by the engine and the nacelle for a bypass flow of cold air, at least one bifurcation passing through the annular duct for connecting the engine and the nacelle and having a leading edge and a primary structure of a pylon housed in the bifurcation and configured to connect the engine to an aircraft wing. The propulsion assembly has at least one heat exchange device including a plate heat exchanger, having a hexagonal longitudinal section and positioned in the bifurcation. According to one configuration, the heat exchanger is a countercurrent heat exchanger.

Abstract: A pipeline including at least first and second portions, each comprising outer and inner pipes, at least one coupling system connecting the first and second portions and including at least a downstream flange ring connected to at least one of the outer and inner pipes of the first portion, at least an upstream flange ring connected to at least one of the outer and inner pipes of the second portion, connecting elements connecting the upstream and downstream flange rings, first and second annular seals interposed between the upstream and downstream flange rings and configured to delimit, with the upstream and downstream flange rings, a buffer space containing an atmosphere, the pipeline comprising at least one leak detection system configured to determine at least one characteristic of the atmosphere of the buffer space.

Abstract: An assembly for an aircraft, the assembly including a pylon with a lateral wall pierced by a window, a tank with a neck blocked by a film and carrying a first anchoring arrangement, and a fixing arrangement for fixing at least a part of the tank bearing the neck inside the pylon, a discharge pipe, and a discharge head. The head includes an explosive cartridge and a hole with a second anchoring arrangement in which discharges the discharge pipe. The discharge head is fixed inside the pylon facing the window. The explosive cartridge is designed to generate in the hole a shockwave sufficient to rupture the film. An assembly of this kind enables simple and rapid removal of the tank from and installation thereof inside the pylon.

Abstract: An assembly having a chassis, two supports with a plate and a guide, a nesting system with a bore, a reservoir containing an extinguishing fluid and with two fastening tabs, two bearing tabs and a peg, and a fastener. The reservoir is able to move in translation between a premounting position in which each fastening and bearing tab rests on a plate and each guide guides the fastening and bearing tabs to align the peg and the bore, and a mounting position in which each fastening tab rests on the plate, the peg is introduced into the bore, the bearing tabs no longer rest on the plates and the fastener fastens each fastening tab to the plate. Such an assembly allows the reservoir to be withdrawn and put in place quickly and easily.

Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.

Abstract: A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.

Abstract: An assembly for an aircraft including a pylon having a lateral wall with a window passing through it, at least one reservoir, each reservoir being in the shape of an elongate ellipsoid with three semi-axes. The dimension of the reservoir along a first semi-axis differs from the dimension of the reservoir along at least one other semi-axis. The reservoir extends parallel to the semi-major axis, between a first end and a second end. The reservoir is equipped with a discharge head at the second end. The reservoir is equipped with a fastening arrangement disposed on the side of the second end and fastening the reservoir to the pylon. The reservoir is positioned through the window with the first end housed in the pylon and the second end outside the pylon.

Abstract: An aircraft pylon including a heat exchange device having a heat exchanger which includes a first circuit portion ducting a flow of hot air tapped off an engine of the aircraft and a second circuit portion ducting a flow of cold air, the first and second circuit portions of the heat exchanger being coaxial, separated by at least one partition forming an exchange surface, and positioned, at least partially, in the primary structure of the pylon.

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

Abstract: An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.

Abstract: A propulsive assembly for aircraft comprising an engine, a nacelle arranged around the engine and a pylon supporting the engine, the nacelle including two engine cowls and reversing cowls, each cowl having an internal skin, characterized in that at least one of the cowls of the nacelle comprises at least one box arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. This box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned.

Abstract: A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.

Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.

Abstract: An aircraft has at least one cowling, a fixed structure, and a hinge system connecting the cowling to the fixed structure. The hinge system includes at least two hinges and at least two stops, including a first stop integral with the fixed structure and a second stop integral with the cowling, the first and second stops being configured to be in contact one against the other when the cowling is in the closed position and to ensure an absorption of a part of the loads between the cowling and the fixed structure at least along a direction perpendicular to the pivot axis of the hinge system.