Abstract: An aircraft turbine engine includes a fan and a reduction gear including a plurality of rotary elements and driving the fan. The turbine engine further includes a gearbox and a mechanical power takeoff box driving the gearbox. The turbine engine includes a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and meshing with the first toothed wheel.

Abstract: A modular assembly for a turbine engine has an annular bearing support that is configured to be connected to a first anti-friction bearing, which is configured to be fitted around a first shaft of the turbine engine. The modular assembly further includes a second anti-friction bearing configured to be fitted around a second shaft of the turbine engine, wherein the second shaft is not parallel to said first shaft.

Abstract: A turbojet is suspended by attachments including hinged links. An attachment includes a support including three branches with passages through which a pin passes, the pin being oriented generally parallel to a direction that is tangential to a casing and being hinged to a central branch of the support by a ball joint.

Abstract: An aircraft turbine engine includes a fan and a reduction gear including a plurality of rotary elements and driving the fan. The turbine engine further includes a gearbox and a mechanical power takeoff box driving the gearbox. The turbine engine includes a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and meshing with the first toothed wheel.

Abstract: A modular assembly for a turbine engine has an annular bearing support that is configured to be connected to a first anti-friction bearing, which is configured to be fitted around a first shaft of the turbine engine. The modular assembly further includes a second anti-friction bearing configured to be fitted around a second shaft of the turbine engine, wherein the second shaft is not parallel to said first shaft.

Abstract: An attachment structure for attaching a power plant including unducted propellers to a fuselage of an aircraft, the attachment structure being connected by first and second fasteners to respective front and rear spars penetrating into the fuselage and fastened to a carrier structure of the aircraft, and including a central longitudinal beam secured at its front end to a first frame, arranged in the plane of the front spar, that is secured at its rear end to a second rear frame, cantilevered out and arranged upstream from the unducted propellers, and that is secured to a third intermediate frame, arranged in the plane of the rear spar between the first and second frames. The first, second, and third frames are connected together by force-takeup beams, an assembly as constituted in this way forming a cradle for receiving the power plant via a standard attachment.

Abstract: A hyperstatic truss including connecting rods, used for suspension of a first ring, forming part of an engine case, inside a second ring concentric to the first ring, the connecting rods being secured at one end to the first ring and at the other end to the second ring. The tensile stiffness of the connecting rods is greater than the compressive stiffness thereof. The truss for example can be used for suspension of a ducted-fan turbine engine with an elongate bypass duct.

Abstract: A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.

Abstract: An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow jet engine that is concentric relative to the outer ring of the exhaust casing, and at least one first and second linking arm or rod forming a hyperstatic link by being attached by one end to the outer ring of the exhaust casing and, by the other end, to the structural ring. The link formed by the first linking arm or rod is configured to break when a predetermined load is exceeded, and the second linking arm or rod is configured to form a force-transmission path between the rings when the link is broken.

Abstract: An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Abstract: A turbojet engine nacelle, including an air intake structure for directing an airflow towards a fan of the turbojet engine, a middle structure attached to the air intake structure for surrounding the fan of the turbojet engine, the air intake structure including an inner panel attached to the middle structure and defining a fixed structure with the middle structure, and an outer panel including an air intake lip at the end thereof opposite the middle structure, the outer panel being longitudinally translatably movable relative to the inner panel. The nacelle further includes at least one rod having one end attached onto a flange of the air intake lip and a mechanism rigidly connected to the middle structure for securing and locking the other end of each rod by applying a traction force thereon.

Abstract: An attachment structure for attaching a power plant including unducted propellers to a fuselage of an aircraft, the attachment structure being connected by first and second fasteners to respective front and rear spars penetrating into the fuselage and fastened to a carrier structure of the aircraft, and including a central longitudinal beam secured at its front end to a first frame, arranged in the plane of the front spar, that is secured at its rear end to a second rear frame, cantilevered out and arranged upstream from the unducted propellers, and that is secured to a third intermediate frame, arranged in the plane of the rear spar between the first and second frames. The first, second, and third frames are connected together by force-takeup beams, an assembly as constituted in this way forming a cradle for receiving the power plant via a standard attachment.

Abstract: A turbojet is suspended by attachments including hinged links. An attachment includes a support including three branches with passages through which a pin passes, the pin being oriented generally parallel to a direction that is tangential to a casing and being hinged to a central branch of the support by a ball joint.

Abstract: A hyperstatic truss including connecting rods, used for suspension of a first ring, forming part of an engine case, inside a second ring concentric to the first ring, the connecting rods being secured at one end to the first ring and at the other end to the second ring. The tensile stiffness of the connecting rods is greater than the compressive stiffness thereof. The truss for example can be used for suspension of a ducted-fan turbine engine with an elongate bypass duct.

Abstract: An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow jet engine that is concentric relative to the outer ring of the exhaust casing, and at least one first and second linking arm or rod forming a hyperstatic link by being attached by one end to the outer ring of the exhaust casing and, by the other end, to the structural ring. The link formed by the first linking arm or rod is configured to break when a predetermined load is exceeded, and the second linking arm or rod is configured to form a force-transmission path between the rings when the link is broken.

Abstract: A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.

Abstract: An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Abstract: An adjustable section nozzle having a ring of deformable panels arranged close to its trailing edge is disclosed. Each panel has a dual-strip type structure made up of two materials presenting different coefficients of expansion, together with controlled heater devices that are thermally coupled to the set of panels.

Abstract: A turbojet engine nacelle, including an air intake structure for directing an airflow towards a fan of the turbojet engine, a middle structure attached to the air intake structure for surrounding the fan of the turbojet engine, the air intake structure including an inner panel attached to the middle structure and defining a fixed structure with the middle structure, and an outer panel including an air intake lip at the end thereof opposite the middle structure, the outer panel being longitudinally translatably movable relative to the inner panel. The nacelle further includes at least one rod having one end attached onto a flange of the air intake lip and a mechanism rigidly connected to the middle structure for securing and locking the other end of each rod by applying a traction force thereon.

Abstract: A device for attenuating acoustical noise from an exhaust nozzle of a turbojet is disclosed. The turbojet exhaust nozzle includes a central body defining the inner surface of the primary gas flow path. The central body includes an outer wall defining one, and only one, resonator cavity. The single resonator cavity is in fluid communication with the primary gas flow path via orifices through at least one upstream portion of the outer wall. The single resonator cavity and plurality of orifices compose a Helmholtz resonator.