Abstract: An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.

Abstract: An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.

Abstract: The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising: an exhaust cone (100) comprising an outer annular wall (102) for the flow of a primary airflow and an annular box arranged radially inside said outer annular wall (102), the annular box comprising an inner annular wall (104) arranged radially inside the outer annular wall of the exhaust cone, an exhaust case arranged upstream of the exhaust cone, and a connecting member (106) flexible in a radial direction, interposed longitudinally between the exhaust case and the exhaust cone (100), the connecting member being fastened to the exhaust case and to the inner annular wall (104), and wherein the inner annular wall (104) is connected to the outer annular wall (102) by fastening means (112) configured to enable movements of the inner annular wall (104) in a circumferential direction and a longitudinal direction with respect to the outer annular wall (102).

Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including a mobile annular external structure, a single actuator for controlling the position of this mobile external structure and a device for guiding the mobile external structure when changing its position. The actuator and the guiding device are housed in a fairing of a pylon of the propulsion assembly to a wing or fuselage of the aircraft.

Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.

Abstract: The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising: an exhaust cone (100) comprising an outer annular wall (102) for the flow of a primary airflow and an annular box arranged radially inside said outer annular wall (102), the annular box comprising an inner annular wall (104) arranged radially inside the outer annular wall of the exhaust cone, an exhaust case arranged upstream of the exhaust cone, and a connecting member (106) flexible in a radial direction, interposed longitudinally between the exhaust case and the exhaust cone (100), the connecting member being fastened to the exhaust case and to the inner annular wall (104), and wherein the inner annular wall (104) is connected to the outer annular wall (102) by fastening means (112) configured to enable movements of the inner annular wall (104) in a circumferential direction and a longitudinal direction with respect to the outer annular wall (102).

Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.

Abstract: An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.

Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including a mobile annular external structure, a single actuator for controlling the position of this mobile external structure and a device for guiding the mobile external structure when changing its position. The actuator and the guiding device are housed in a fairing of a pylon of the propulsion assembly to a wing or fuselage of the aircraft.

Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including an outer structure movable between a closed position and an open position of two primary latches configured to lock the movable outer structure in the closed position. The movable outer structure includes an output end that is oblique with respect to the longitudinal central axis so as to orient the thrust laterally. In order to compensate the tilting moment of the movable outer structure, which results from this lateral orientation of the thrust, the primary latches are offset with respect to a median longitudinal plane passing through the longitudinal central axis of the reverser.

Abstract: A thrust reverser for an aircraft propulsion unit, this reverser including a fixed structure and a mobile external structure able to move between a closed position and an open position so as to cause the reverser to transition respectively between a direct-jet configuration and a reverse-jet configuration. The reverser includes, on the one hand, one or more actuators configured to move the mobile external structure between the closed position and the open position. The reverser includes, on the other hand, at least one initiator configured to apply to the mobile external structure a force that initiates a closure travel in which the mobile external structure is moved from the open position towards the closed position.

Abstract: The invention relates to an air intake for an aircraft nacelle that includes a shroud that can be mounted on the fan casing of a turbojet engine. The shroud is sized so as to define a circumferential gap relative to the casing. Punctual linking means between the shroud and the casing are discretely distributed at the periphery of the shroud.

Abstract: The invention relates to an air intake structure (4) for a turbine engine nacelle for directing an air flow towards the fan of the turbine engine, said structure comprising at least one outer panel (40), at least one inner panel (41) and an air intake lip (4a) having an inner wall (70) to be in contact with the air flow flowing into the turbine engine and a partition (45) separating the air intake lip (4a) from the rest of the nacelle, the air intake lip (4a) having an extension (60) that can be fastened onto the inner panel (41) and that extends substantially as a continuation of the inner wall (70) towards the downstream side of the air intake structure over a length (I) at least equal to about the maximum distance (d) between the partition (45) and the air intake lip (4a). The invention also relates to a nacelle for a turbine engine comprising such an air intake structure (4).

Abstract: The invention relates to an air intake for an aircraft nacelle that comprises a shroud (19) that can be mounted on the fan casing (15) of a turbojet engine (1). The shroud (19) is sized so as to define a circumferential gap (J) relative to the casing (15). Punctual linking means (27, 33) between the shroud (19) and the casing (15) are discretely distributed at the periphery of said shroud (19).