Abstract: The subject matter of this specification can be embodied in, among other things, an assembly that includes a piston having a piston inner surface defining a cylindrical cavity and includes a first axial portion, a piston face at a first end of the first axial portion, a second axial portion at a second end of the first axial portion, and a helical piston thread defined upon the piston inner surface, a bushing configured to contact the piston inner surface, and a lock nut configured to engage the piston and the bushing.

Abstract: A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.

Abstract: A ducted fan turbine engine with a nacelle and a duct for a secondary flow. The nacelle comprises a fixed structure. A mobile cowl is able to move between a forward position and a backward position to define an opening between the duct and the outside. A plurality of rollers are mounted to freely rotate on the mobile cowl. For each roller there is a flexible screen with a first edge fixed to the roller and a second edge, in which the screen is able to adopt a furled position, wound around the roller, or a deployed position deployed across the duct. A deployment mechanism is arranged to move each second edge to move the screen from the furled position to the deployed position. A furling mechanism is arranged to drive each roller in rotation to move the associated screen from the deployed position to the furled position.

Abstract: A thrust reverser of a nacelle may include a translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a cowl door movable between a closed position and an open position. The cowl door includes a structural panel and a mount. The structural panel includes an inner skin, an outer skin and a cellular core. The cellular core is connected to and arranged between the inner skin and the outer skin. The mount includes a base and a coupler. The base is connected to and arranged between the inner skin and the outer skin. The coupler projects out from the base.

Abstract: A thrust reverser actuation system for a jet propulsion engine for a vehicle, the thrust reverser actuation system comprising: a plurality of hydraulically-driven thrust reverser actuators for actuating one or more thrust reverser components of the jet propulsion engine, each actuator comprising: a hydraulic circuit; and a bi-directional electrically-driven pump configured to pump hydraulic fluid through the hydraulic circuit, wherein the hydraulic circuit and the pump are configured such that the direction of the pump dictates the direction of the actuation of the actuator.

Abstract: A housing for a gas turbine engine accessory includes an enclosure having a drive end with an opening and a closure. The closure is seated in the opening, defines therethrough a shaft aperture and has a v-band flange extending about a periphery of the closure to limit load carried by the enclosure when the engine accessory is mounted to an accessory gearbox mount in a cantilevered arrangement. Engine accessories for gas turbine engines and mounting arrangements for gas turbine engine accessories are also described.

Abstract: A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.

Abstract: A method for gathering flight load data for a gas turbine engine includes providing a plurality of blocker doors rotatably mounted to a translating sleeve and a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve, wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit; and connecting the data acquisition unit to at least one sensor in communication with the translating sleeve.

Abstract: 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.

Abstract: A translating cowl thrust reverser system with efflux management includes a support structure, a transcowl, a cowl shield, and a single cascade structure. The transcowl and cowl shield are moveable together between a first position, in which the transcowl abuts the support structure, and a second position, in which an aperture is formed between the transcowl and the support structure. The cowl shield has cowl shield turning vanes. The single cascade structure is disposed within the aperture and includes a forward wall, a curved vane, internal turning vanes, and external turning vanes. In the first position, each cowl shield turning vane is disposed between a different pair of external turning vanes. The cowl shield turning vanes, the internal turning vanes, and the external turning vanes turn the airflow so that it is directed substantially perpendicular to, and vertically outboard relative to, a plane of symmetry.

Abstract: Flexible aft cowls are disclosed. In some examples, an aircraft engine having a flexible aft cowl is disclosed. In some examples, the aircraft engine comprises an aft cowl having a flexible portion defining a throat area adjacent an engine core nozzle of the aircraft engine. In some examples, the flexible portion to move radially between a first radial position in response to pressure within a nacelle not exceeding a pressure threshold and a second radial position in response to pressure within the nacelle exceeding the pressure threshold. In some examples, the throat area defined by the flexible portion is greater when the flexible portion is in the second radial position than when the flexible portion is in the first radial position.

Abstract: A bypass turbofan engine comprising a nacelle surrounding a flow path for a secondary flow and comprising a fixed structure, a mobile assembly with a slide capable of translational movement on the fixed structure and bearing a mobile cowl and a frame capable of translational movement on the fixed structure and bearing deflectors. The mobile assembly is able to move between a forward position and a retreated position making it possible to open a passage between the flow path and the outside through the deflectors. A differentiation mechanism ensures a length of travel of the slide that is different from the length of travel of the frame, and actuators providing a translational travel of the slide. Fitting a differentiation mechanism means that the length of travel of the deflectors with respect to the length of travel of the mobile cowl can be regulated.

Abstract: Locking actuators for thrust reverser actuation systems, engines and aircraft including the same, and associated methods. A locking actuator includes an actuator housing, an extension element, and a lock assembly. The extension element is configured to translate along an actuator axis to transition between a retracted state and an extended state. The lock assembly transitions between a locked state and an unlocked state independent of transitioning the extension element between the retracted and extended states. In examples, a thrust reverser actuation system includes an actuator assembly with the locking actuator and a hydraulic control assembly. In examples, an engine includes a thrust generator, a nacelle, a transcowl, and the thrust reverser actuation system. In examples, a method of operating a thrust reverser actuation system includes transitioning a lock assembly from a locked state to an unlocked state and transitioning an extension element from a retracted state to an extended state.

Abstract: Disclosed is an arrangement for coupling a fairing panel to an engine casing. The arrangement includes a pair of rigid brackets having a specific stiffness, wherein the pair of rigid brackets couple a first side of the fairing panel to a first side of the engine casing. The arrangement further includes a pair of flexible brackets comprising a first flexible bracket having a first stiffness and a second flexible bracket having a second stiffness more than the first stiffness. Moreover, the first stiffness and the second stiffness are less than the specific stiffness of the pair of rigid brackets. Furthermore, the pair of flexible brackets couple a second side opposite to the first side of the fairing panel to a second side opposite to the first side of the engine casing.

Abstract: A thrust reverser for an aircraft propulsion assembly includes a movable structure provided with external covers connected to hinges through a pivot connection allowing the external covers to rotate between a closed position and a maintenance position. The hinges are connected to secondary rails rigidly attached to an engine pylon through a sliding connection allowing the external covers to move in translation between a direct thrust position and a reverse thrust position. The hinges and the secondary rails are independent of beams to which the parts of the movable structure other than the external covers are connected. A method for maintaining an aircraft propulsion unit is also disclosed. The method includes positioning of the external covers in maintenance position followed by a placement of the beams and of the parts of the movable structure other than the external covers.

Abstract: 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.

Abstract: A cascade assembly for a thrust reverser of an aircraft engine. The cascade broadly comprises a number of vanes formed of a pliable material and shiftable between a collapsed position when the thrust reverser is in a stowed configuration and a distended position when the thrust reverser is in a deployed configuration to redirect fan duct flow in a reverse thrust flow opening created by the thrust reverser.

Abstract: A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.

Abstract: A valve assembly for a turbine engine includes a valve arranged in an air flow path. The valve has a shaft. The valve is movable between an open position and a closed position. A hydraulic actuator is coupled to the shaft. The hydraulic actuator is configured to utilize fuel as a working fluid. The hydraulic actuator is configured to move the valve between the open position and the closed position.