Abstract: A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.

Abstract: The present disclosure relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle. The hydraulic control system includes devices for actuating and controlling the reverser having hydraulic locks and cylinders, the corresponding hydraulic solenoid valves, and sensors. The turbofan includes a full-authority electronic computer or aircraft having an avionics computer that gives reverse thrust commands. The system further includes an electronic concentration module, different from the computer, which concentrates the data relating to the operation of the reverser actuation and control devices. The module includes internal contact switches for controlling the solenoid valves, a device for monitoring the sensors, a device for analog or digital processing of the data, and a bus for communication with the computer.

Abstract: An aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser includes cascades of mobile deflection vanes connected to cascade rails with a slideway connection that allows the cascades of vanes a translational movement between a cruising-flight position and a reverse-thrust position. The thrust reverser allows the cascade rails to be positioned in a forward position, in which the engine, the cascade rails and the deflection vanes can be removed from the propulsion assembly without the cascade rails colliding with the mobile cowl of the reverser. Dismantling and assembly or reassembly methods allow maintenance operations to be carried out on the engine thus dismantled.

Abstract: An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.

Abstract: A ducted fan turbojet including a nacelle including a fixed structure, a thrust reverser system having a frame, a mobile structure fastened to the frame, inner doors and outer doors hinged at the frame. The frame is mobile in translation on the fixed structure between a forward position and a rear position so as to define a window between the fixed structure and the mobile structure, the window being open between a bypass duct and the exterior of the nacelle. Each door is mobile between a stowed position and a deployed position and the mobile structure is assembled hinged on the frame via at least one hinge whose axis of rotation is globally parallel to a longitudinal axis of the ducted fan turbojet.

Abstract: A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

Abstract: In a structure for cooling a component member of a gas turbine using a working gas, a plurality of heat transfer enhancement ribs having W shapes are provided so as to project from the wall surface of a passage wall facing a cooling medium passage through which a cooling medium flows. In each heat transfer enhancement rib, outside corner portions facing toward the upstream side are formed in an angled shape, and at least any one of inside corner portions and outside corner portions other than the outside corner portion facing toward the upstream side are formed in a curved shape.

Abstract: A turbojet engine comprising an engine, a nacelle comprising a fan case, an intermediate case having a part forming a hub and an outer shroud radially spaced away from the hub by a secondary, or bypass, flow path and fixed to the hub via arms, in which the outer shroud is situated to the rear and in the continuity of the fan case, a fixed structure fixed to the outer shroud, a mobile assembly mounted with the ability to effect translational movement on the fixed structure, and a ramp fixed to the outer shroud and configured to direct the secondary or bypass flow to exit the outer shroud. Such a turbojet engine makes it possible to simplify assembly and among other things, makes it possible to fix the ramp directly to the outer shroud.

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: An aircraft propulsor with a thrust reverser with a pressure relief system is disclosed herein. The aircraft propulsor can include a flow path and a blocker door configured to block the flow path to divert airflow within the flow path to generate reverse thrust. The blocker door can include a main door and a pressure relief door. The pressure relief door can be coupled to the main door and configured to move from a closed position to an open position in response to flow path pressure greater than a threshold pressure. Moving the pressure relief door to the open position can relieve flow path pressure.

Abstract: A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and a deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.

Abstract: A method of producing a cascade array and a cascade array is provided. The method includes: forming a plurality of strongbacks from a first thermoplastic material; forming a plurality of comb subassemblies, each said comb subassembly including one of the plurality of strongbacks and a plurality of vanes comprising a second thermoplastic material extending outwardly from the respective one of the plurality strongbacks; and attaching the plurality of comb subassemblies into a unitary structure to produce the cascade array.

Abstract: A nacelle having a window open between a secondary jet and the outside of the nacelle and comprising a fixed structure and a thrust-reversing system having a frame and outer doors articulated on the frame. The frame is translationally mobile on the fixed structure between an advanced position and a retracted position. Each outer door is mobile between a stowed position and a deployed position. The nacelle comprises at least one anti-vibration system which comprises a chock fixed to the fixed structure and having a hole, and a finger fixed to the outer door. The finger and the hole are configured so that the finger lodges in the hole when the frame is in advanced position. Such a nacelle makes it possible to limit the vibrations of the outer doors when they are in stowed position and before the mobile frame begins to be displaced to the retracted position.

Abstract: An aircraft propulsion assembly, including a turbine engine comprising at least one gas generator configured to generate a main flow, which is supplied by a central jet to at least one power turbine, the central jet being surrounded by an outer fairing, and the power turbine driving, on the periphery thereof, at least one fan rotor. The aircraft propulsion assembly comprises first movable means which are arranged so as to divert at least some of the main flow from the central jet to the outside of the outer fairing and preferably upstream of the turbine engine so as to generate thrust reversal. An aircraft which uses the propulsion assembly, particularly on the rear tip of the fuselage of the aircraft.

Abstract: A gas turbine engine includes an engine core and a fan located upstream of the engine core. The engine core includes: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection. The first flange connection is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor. A fan diameter ratio of: first ? ? flange ? ? radius fan ? ? diameter is equal to or greater than 0.125.

Abstract: A thrust reverser pivot door may comprise a support structure configured to pivot between a stowed position and a deployed position, and a pivot door outer skin coupled to the support structure, wherein a forward lip of the pivot door outer skin is configured to extend forward of a torque box and overlap the fan case to advantageously increase the overall size or area of the pivot door.

Abstract: A nacelle comprising a fixed structure, a fixed cowl, a mobile cowl, and a motor arrangement to translationally displace the mobile cowl from a closed to an open position on the fixed structure. The nacelle comprises a window delimited between the fixed and mobile cowls and open between a secondary turbojet and the outside, a thrust-reversing door rotationally mobile about a rotational axis between retracted and active positions, and a driving mechanism which coordinates and defers the switch from the retracted to the active position with the switch from the closed to the open position. The driving mechanism comprises two connecting rods rotationally mobilely mounted on the fixed structure and bearing a wheel, a mobile cowl groove which slidingly receives the wheel, a guide integral to the thrust-reversing door, and a runner rotationally mobilely mounted between the connecting rods, as well as mounted to slide along the guide.

Abstract: A method and apparatus for a turbine engine having a compressor section, combustion section, and a turbine section in an axial flow arrangement with a cooling circuit in fluid communication with at least one of the compressor section, combustion section, or turbine section. The method and apparatus further including separating particles from a cooling air that flows through the cooling circuit.

Abstract: A nacelle for a jet engine having a selectively operated reverse thruster which redirects air flow to a cascade during a reverse thrust operation, the nacelle including a fancowl panel configured as a stationary partial cover for a jet engine; and a translating cowl panel configured to move transversely during a reverse thrust operation so as to expose a cascade for emitting reverse thrust airflow. In exemplary embodiments, a moveable automatic translating panel, or a rotatable hinge panel, or an extension portion of the fancowl is used to preserve clearance with an aircraft wing in a nacelle clearance area.

Abstract: A thrust reverser is described that comprises a new type of locking means for locking an actuator in position so that maintenance can be performed on the machine. The locking means comprises a removable locking device for preventing movement of an actuator. The locking means may also function in one configuration as an end cap. An actuator is also described comprising a removable torque limiting device for limiting torque of the actuator.