An assembly is provided for an aircraft propulsion system. This assembly includes a target-type thrust reverser and a tubular trailing edge body. The target-type thrust reverser includes a plurality of thrust reverser doors. Each of the thrust reverser doors is configured to pivot between a stowed position to a deployed position. The tubular trailing edge body is configured to at least partially form a gas path nozzle for the aircraft propulsion system. The tubular trailing edge body is configured to be displaced when the thrust reverser doors pivot from the stowed position to the deployed position.

A variable vane assembly for a gas turbine engine, the variable vane assembly including: a plurality of vanes arranged into a plurality of stages, each one of the plurality of vanes being configured for rotation about an axis through movement of a vane arm secured to each one of the plurality of vanes at one end and a sync ring of each one of the plurality of stages at another end; and a plurality of bell cranks operably coupling the sync ring of each one of the plurality of stages to a self-retained linkage via a stud of each one of the plurality of bell cranks, the stud of each one of the plurality of bell cranks being rotatably received in a corresponding opening of the self-retained linkage in an alternating fashion such that only a single shear interface is provided between each one of the plurality of bell cranks and the self-retained linkage.

A turbofan having a nacelle comprising a slider being mobile in translation between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one being mobile in rotation on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade. The maneuvering system comprises, for each blade, a shaft being mobile in rotation on the slider and on which the blade is fixed, a toothed sector being fixed to the shaft, a toothed arc being mobile in rotation on the slider, and having a bearing face, a threaded rod mounted fixed on the fixed structure, a cam having a tapped hole screwed onto the threaded rod and mounted fixed in translation with respect to the slider, and a return arrangement that presses the bearing face against the cam outer surface.

A transition piece support structure for a gas turbine combustor, and a method of installing same, reliably prevent leakage at the flange of a lower-side combustor, which is greatly influenced by gravity. The structure supports a rear end portion of a transition piece when fixed to a turbine end and includes a flange provided at a rear end of the transition piece, to be coupled to the end of the turbine, the flange having a shape to fit a periphery of a turbine inlet; a support bracket integrated with an upper surface of a flow sleeve surrounding an outer surface of the transition piece, to face the end of the turbine coupled to the flange; and a connection piece fixed to the end of the turbine and configured to be coupled to the support bracket in a hinged manner allowing the flange to pivotally approach the turbine inlet.

A turbofan engine with a nacelle including a runner translationally mobile between advanced and back-off positions to open a window between a stream and an outside, a plurality of blades, each rotatable on the runner between retracted and deployed positions, and a maneuvering system displacing each blade and comprising, for each blade, a shaft rotatable on the runner and to which the blade is fixed, and a toothed segment on the shaft, and a toothed arc rotatable on the runner about a longitudinal axis, the tooth arc teeth meshing with the toothed segment teeth, a slip translationally mobile on the runner in a plane at right angles to the longitudinal axis between first and second positions, a connecting rod mounted articulated between the slip and the toothed arc, a rib integral to the fixed structure, and a guiding U integral to the slip and which straddles the rib.

A turbofan having a nacelle including a slider mobile in translation between advanced and retracted positions to open a window between a duct and the exterior, a plurality of blades, each being mobile in rotation on the slider between stowed and deployed positions, and a maneuvering system that moves each blade and includes, for each blade, a shaft mobile in rotation on the slider and on which the blade is fixed, an arm having a first end fixed to the shaft and a second end, an arc which is coaxial with the longitudinal axis and is rotatably mounted on the slider, about the longitudinal axis, a lever mounted in articulated fashion between the arc and the second end of the arm, and an actuation system which rotates the arc in one direction and in the other.

A turbofan with a fan casing and a nacelle which comprises a fixed structure, a movable assembly with a movable cowl and a slide, which is translationally movable between an advanced position and a retreated position in which the movable cowl is moved away from the fan casing in order to define a window open between a duct and the outside of the nacelle, a plurality of blades, each being mounted rotatably on the slide, where each blade is movable between a retracted position in which the blade is outside of the duct and a deployed position in which the blade is across the duct, a set of actuators for moving the slide and an operating system configured to move each blade from the retracted position to the deployed position, and vice versa.

An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

A nacelle may comprise an inlet and a fan cowl aft of the inlet. The fan cowl may include a fan cowl panel configured to rotate between an open position and a closed position. The nacelle may further comprise a securement retainer including a first portion coupled to an interior surface of the fan cowl panel and a second portion coupled to an aft inlet flange of the inlet. The first portion of the securement retainer may be configured to engage the second portion.

A turbofan having a nacelle including a slider translationally mobile to open a window between a duct and the exterior, a plurality of blades, each rotationally mobile on the slider, and a maneuvering system moving each blade and comprising for each blade, a shaft rotationally mobile on the slider and onto which the blade is fixed, an arm having a first end fixed to the shaft, an arc coaxial with the longitudinal axis, mounted rotationally mobile on the slider about the longitudinal axis, a rectilinear rod fixed by its base to the arc, the rectilinear rod inserted into a through-bore of a stock, wherein the stock is mounted translationally free relative to the rectilinear rod, and the stock is mounted rotationally free on the arm at its second end about a rocking axis parallel to the rotational axis, and an actuation system producing arc rotation in two opposite directions.