A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

A turbine comprises a turbine housing defining a turbine inlet upstream of a turbine wheel and a turbine outlet downstream of the turbine wheel; and a wastegate valve assembly comprising at least one movable valve member mounted on a movable support member within a wastegate chamber which communicates with the turbine inlet upstream of the turbine, and has one or more chamber outlets which communicate with an outlet of the turbine. The valve member is permitted to articulate slightly about the support member, with the amount of articulation in respective directions being limited by collisions between a respective limit point on a limit area on a rear surface of a sealing portion of the valve member and a respective limit point on limit area on a front surface of the support member.

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 drive pinion of an air/oil separator of an accessory gearbox of a turbomachine, the air/oil separator being configured to be supplied at the input by an air flow to de-oil and to supply at the output, on the one hand, a de-oiled air flow and, on the other hand, an oil flow by centrifugation, the pinion being configured to drive the separator rotationally along an axis of rotation, the pinion being mounted facing a passage opening of the separator, the pinion comprising at least one guiding opening traversing the web plate defining at least one guiding surface inclined with respect to the axis of rotation in such a way as to guide along the axis an air flow to de-oil into the separator or a de-oiled air flow out of the separator via the guiding opening of the pinion.

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 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.

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.

An air inlet device for an air inlet of an aircraft. The air inlet device has air guide arrangements. An air guide arrangement has an inlet plate, an outlet plate, and pivot plates arranged therebetween. The outlet plate and the pivot plates can be rotated about a central axis of the air inlet device by adjustment rings, so that the air guide arrangement is transitioned from a linear state to a curved state, and vice versa. The air inlet device allows for selective switching between a state with low radar signature and a state with high performance of an engine.

A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.

A turbofan having a nacelle comprising a slider mobile in translation between advanced position and retracted positions to open a window between a duct and the exterior, a plurality of blades, each one being rotatably mobile on the slider between stowed and deployed positions, and a maneuvering system moving each blade and comprising for each blade, a shaft rotatably mobile on the slider and onto which the blade is fixed, for each shaft, a balance beam fixed to the shaft and having first and second ends, for three consecutive balance beams, two connecting rods where the first connecting rod is mounted articulated between the first balance beam and the second balance beam, and where the second connecting rod is mounted articulated between the second balance beam and the third balance beam, and an actuation system rotating one of the connecting rods in one direction and in the other.