A propulsion assembly for an aircraft includes a pylon, a turbofan including a structure fixed to the pylon, and at least one thrust reverser, each having a top beam extending parallel to a longitudinal direction and mobile in rotation on the structure around a rotation axis parallel to the longitudinal direction. For each thrust reverser, an actuator is provided, a first end of which is articulated on the pylon and a second end of which is articulated on the top beam of the thrust reverser and the articulation axis of the actuator on the top beam is not coaxial with the rotation axis. Such assembly allows a positioning of the actuator in the upper part of the turbofan between the top beam of the thrust reverser and the pylon to free some space.

A propulsion assembly for an aircraft includes a pylon, a turbofan including a structure fixed to the pylon, and at least one thrust reverser, each having a top beam extending parallel to a longitudinal direction and mobile in rotation on the structure around a rotation axis parallel to the longitudinal direction. For each thrust reverser, an actuator is provided, a first end of which is articulated on the pylon and a second end of which is articulated on the top beam of the thrust reverser and the articulation axis of the actuator on the top beam is not coaxial with the rotation axis. Such assembly allows a positioning of the actuator in the upper part of the turbofan between the top beam of the thrust reverser and the pylon to free some space.

An internal structure of a primary exhaust duct of a turbomachine, the internal structure comprising a primary wall comprising a surface of revolution about a longitudinal axis, allowing the air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin comprising a surface of revolution about the longitudinal axis, arranged inside the primary wall, an upstream flange and a downstream flange which attach the interior skin to the interior of the primary wall, at least one separator which is attached to the interior skin and which extends from the interior skin towards the primary wall, the, or each, separator extends in a plane generally parallel to the longitudinal axis, between the two flanges, and the, or each, separator is not attached to the primary wall.

An internal structure of a primary exhaust duct of a turbomachine, the internal structure comprising a primary wall comprising a surface of revolution about a longitudinal axis, allowing the air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin comprising a surface of revolution about the longitudinal axis, arranged inside the primary wall, an upstream flange and a downstream flange which attach the interior skin to the interior of the primary wall, at least one separator which is attached to the interior skin and which extends from the interior skin towards the primary wall, the, or each, separator extends in a plane generally parallel to the longitudinal axis, between the two flanges, and the, or each, separator is not attached to the primary wall.

An exhaust duct for an engine includes an outer exhaust duct and a nested exhaust duct capable of having at least two configurations. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a first length of the nested exhaust duct in a first configuration. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a second length of the nested exhaust duct in a second configuration, which is less than the first length.

An exhaust duct for an engine includes an outer exhaust duct and a nested exhaust duct capable of having at least two configurations. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a first length of the nested exhaust duct in a first configuration. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a second length of the nested exhaust duct in a second configuration, which is less than the first length.

The invention relates to an assembly for an aircraft turbomachine, comprising a central element (1) for the ejection of gas, and a connecting flange (9) interposed between, upstream, a gas outlet (22a) made of metal for a turbomachine, and, at the downstream end, the central element (1). The connecting flange comprises an annular portion (9a) and flexible tabs (11) having axially: a first end (111a) where the tab is connected to the said annular portion, and a second free end (111b), projecting radially inwardly with respect to the first end and to which said tab is attached with the central element (1).

The invention relates to an assembly for an aircraft turbomachine, comprising a central element (1) for the ejection of gas, and a connecting flange (9) interposed between, upstream, a gas outlet (22a) made of metal for a turbomachine, and, at the downstream end, the central element (1). The connecting flange comprises an annular portion (9a) and flexible tabs (11) having axially: a first end (111a) where the tab is connected to the said annular portion, and a second free end (111b), projecting radially inwardly with respect to the first end and to which said tab is attached with the central element (1).

A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.

A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.