Abstract: A thrust reverser system includes two thrust reversal cascades, of which the first cascade is entrained by an actuator, and which are configured to adopt a retracted position in which they are housed in a space located outside the duct. The action of the actuator brings about: rearward displacement of the first cascade in the direction of a nacelle opening; and during part of the rearward displacement of the second cascade, simultaneous pivoting of this second cascade under the action of a control lever, the interaction of which with a fixed guide rail forces the front end of the lever to move radially inwards while the lever is entrained rearwards by the second cascade.

Abstract: A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.

Abstract: An engine assembly for an aircraft rigid structure comprising a mounting pylon comprising a central box and a box extension connected to a reducing gear case of the turboreactor. The box extension includes two parts bearing the front engine attachments, these pieces each comprising a structure forming a reinforcing rib of the central box, as well as two parts of horseshoe shape surrounding the reducing gear case.

Abstract: To reduce flexural deformations of an engine, an engine assembly comprises a device for attaching the engine onto a structure of an aircraft, the attachment device including a primary structure, an attachment device for attaching the engine onto the primary structure of the attachment pylon, and a nacelle including thrust reversal cowls, each equipped with an inner structure arranged around a case portion of the engine. The assembly includes flexible devices for transmitting forces, arranged between the case portion and the inner structures of the cowls, each device including an elastically deformable device configured so that in the closed position of the cowl, with the engine at a standstill, it adopts a partial elastic deformation state allowing the device to apply a prestress force on the case portion.

Abstract: A propulsion assembly includes a turbojet incorporating a fan casing and a central casing around a longitudinal axis, a mounting pylon having a rigid structure, a forward engine attachment interposed between a forward extremity of the rigid structure and an upper part of the fan casing, the upper part being in a vertical median plane (P) passing through the longitudinal axis, an aft engine attachment interposed between a median zone of the rigid structure and an upper aft part of the central casing, and a device for absorbing the thrust forces generated by the turbojet, including two links placed either side of the median plane (P) and hinged, on one hand, forward, on a forward part of the central casing, and on the other, aft, directly on the rigid structure. Such an arrangement enables a reduction of the stresses, and the possibility of designing a simplified rigid structure.

Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.

Abstract: In order to optimize the bulk of a primary structure of an aircraft engine attachment pylon, and to favor the installation of the engine as close as possible to the wing element, the disclosure herein provides an aircraft assembly comprising a wing element, a turbofan engine and an engine attachment pylon, the engine comprising a rear part arranged under the wing element equipped with a wing structure, the pylon comprising a primary structure for transmitting loads from the engine to the wing structure, this primary structure comprising a pylon box, and the assembly also comprising an attachment for attaching the primary structure to the engine. According to the disclosure herein, the wing structure comprises two wing boxes that follow one another in a wingspan direction of the wing element, and the pylon box is arranged between these boxes and fixed to each of the latter.

Abstract: In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams.

Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.

Abstract: For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively.

Abstract: In order to reduce the size of the attachment arrangement between an aircraft engine and its attachment device, an engine assembly is provided for which the primary structure of the attachment device includes a central box and two movable structural cowls. Further the arrangement for attaching the engine on the structure comprises a group of main ties laid out in a main transverse plane for absorbing forces crossing a front end of the movable structural cowls, this group comprising three main shearing pins radially oriented and distributed around a longitudinal axis of the engine, each pin crossing a first shearing orifice provided on a fitting secured to the hub of the intermediate case on the one hand, and a second shearing orifice provided on one of the movable cowls or on its connecting structure to the central box on the other hand.

Abstract: In order to reduce congestion of attachments between an aircraft engine and its attachments, an engine assembly is provided, the primary structure of the device of which includes a structural cover surrounding the engine and connected on a central box, the cover including an outer skin interiorly delimiting a secondary vein. A group of main mounts is provided as a group of secondary mounts laid out at the rear of the group of main mounts, the group of main mounts comprising a plurality of bolts distributed around the longitudinal axis of the engine and ensuring the attachment of a front end of the cover to the hub of the intermediate case, and a group of secondary mounts comprising a plurality of secondary mounts distributed around the axis and ensuring attachment of a rear portion of the engine to a rear end of the cover.

Abstract: In order to reduce the width of the attachment between the rear portion of an aircraft engine and its attachment pylon, an engine assembly attachment include an assembly of rear engine attachments comprising a first connecting rod laid out in a longitudinal and median vertical plane, a second connecting rod substantially laid out tangentially to the inter-turbine case, and a rear engine attachment for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods, and comprising a shear pin oriented along a vertical direction of the engine assembly.

Abstract: An engine assembly for an aircraft rigid structure comprising a mounting pylon comprising a central box and a box extension connected to a reducing gear case of the turboreactor. The box extension includes two parts bearing the front engine attachments, these pieces each comprising a structure forming a reinforcing rib of the central box, as well as two parts of horseshoe shape surrounding the reducing gear case.

Abstract: A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.

Abstract: In order to reduce the risks of movable nacelle cowlings opening, the invention provides a nacelle (11) for an aircraft engine assembly (1) comprising a fixed nacelle structure (42) as well as at least one jointed movable cowling (38) on the fixed structure (42), the cowling (38) being jointed at its front end (38a) on the fixed structure so that, upon closing the movable cowling, a rear end (38b) of this cowling moves towards the rear and radially towards the inside.

Abstract: In order to bring a turbofan engine closer to the lower surface of a wing box, the disclosure herein foresees an assembly for an aircraft including a mount for mounting a rigid structure of an engine strut to the wing box, the mount including an upper wing mount including a fitting secured to the upper surface of the wing box.

Abstract: In order to optimize the bulk of a primary structure of an aircraft engine attachment pylon, and to favor the installation of the engine as close as possible to the wing element, the disclosure herein provides an aircraft assembly comprising a wing element, a turbofan engine and an engine attachment pylon, the engine comprising a rear part arranged under the wing element equipped with a wing structure, the pylon comprising a primary structure for transmitting loads from the engine to the wing structure, this primary structure comprising a pylon box, and the assembly also comprising an attachment for attaching the primary structure to the engine. According to the disclosure herein, the wing structure comprises two wing boxes that follow one another in a wingspan direction of the wing element, and the pylon box is arranged between these boxes and fixed to each of the latter.

Abstract: A propulsion assembly includes a turbojet incorporating a fan casing and a central casing around a longitudinal axis, a mounting pylon having a rigid structure, a forward engine attachment interposed between a forward extremity of the rigid structure and an upper part of the fan casing, the upper part being in a vertical median plane (P) passing through the longitudinal axis, an aft engine attachment interposed between a median zone of the rigid structure and an upper aft part of the central casing, and a device for absorbing the thrust forces generated by the turbojet, including two links placed either side of the median plane (P) and hinged, on one hand, forward, on a forward part of the central casing, and on the other, aft, directly on the rigid structure. Such an arrangement enables a reduction of the stresses, and the possibility of designing a simplified rigid structure.

Abstract: In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams.