Abstract: A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.

Abstract: A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.

Abstract: A suspension for suspending of a turbine engine from the structure of an aircraft using a beam with an attachment device which attaches to the structure and at least one link rod articulated via one end to a journal secured to the beam and via the other to a fitting secured to the turbine engine is disclosed. This suspension is one wherein the journal is mounted on the beam via a flexible coupling formed of two preloaded laminated, elastomer and metal, cylinders.

Abstract: A suspension for suspending a turbine engine from the structure of an aircraft is disclosed. The suspension includes a beam with a first element including a first attachment unit which attaches the beam to the structure and a second element including a second attachment unit which attaches to the beam to the turbine engine. The beam further includes a first plate and a second plate. The plates are positioned transversely to the axis of the engine and joined together by a layer of elastomer. The first plate being secured to the first element and the second plate to the second element. This arrangement allows vibration damping between the engine and the structure of the aircraft.

Abstract: A suspension for suspending a jet engine on an aircraft strut includes a beam having a platform provided with fasteners for fastening the beam to the aircraft strut and arranged transversely with respect to a longitudinal axis of the jet engine. The suspension also includes first and second lateral links, the second lateral link being prolonged by a finger housed with clearance in a cavity provided in the beam so as to form a standby safety connection. The suspension further includes a central link. The finger extends between the platform and a pin of the central link in normal operation.

Abstract: A mount for an aircraft engine arranged to be attached firstly by a beam to the aircraft, and secondly by lateral and a median load transmission elements to the engine, the mount having an integrated load transmission and failsafe assembly arranged to ensure the continuity of load transmission in the event of failure of a load transmission element and to perform its failsafe function in unitary, concentrated fashion in the median zone of the mount. The mount is characterized by the fact that the load transmission and failsafe assembly includes an assembly of a female clevis with two wings and of a projecting element passing with clearance through the two wings of clevis, one being integral with the engine and the other with the mounting beam.

Abstract: The present invention relates to a suspension for suspending a turbine engine from the structure of an aircraft, comprising a beam with a first element accepting means of attachment to said structure and a second element accepting means of attachment to the turbine engine. It is one wherein the beam comprises at least a first plate and a second plate, which plates are intended to be positioned transversely with respect to the axis of the engine and joined together by a layer of elastomer, the first plate being secured to the first element and the other plate to the second element. This arrangement allows vibration damping means to be incorporated in between the engine and the structure of the aircraft.

Abstract: The present invention relates to the suspending of a turbine engine from the structure of an aircraft using a beam with means of attachment to said structure and at least one link rod articulated via one end to a journal secured to the beam and via the other to a fitting secured to the turbine engine. This suspension is one wherein the journal is mounted on the beam via a flexible coupling formed of two preloaded laminated, elastomer and metal, cylinders.

Abstract: An aircraft engine includes a mounting attached to an aircraft structure and transmitting forces between an engine casing and the aircraft structure. The mounting includes a fail safe assembly with a safety clevis with two lugs and a tab arranged between the two lugs. Either the clevis or the tab is fixed to an element of the engine casing and the other tab or clevis is fixed to the structure. A safety hinge pin is perpendicular to the axis of the engine and passes through the tab and the clevis, the two lugs and the tab being parallel to the engine axis.

Abstract: The present invention relates to a suspension for suspending a jet engine on an aircraft strut, comprising a beam 10 having a platform 11 provided with means for fastening it to the said strut and arranged transversely with respect to the axis of the engine, first 20 and second 40 lateral links each connected by a first pin 21, 41 to the beam 10 and by a second pin 22, 42 to the engine casing, the second lateral link 40 being prolonged in the region of the first pin by a finger 43 housed with clearance in a cavity provided in the beam so as to form a standby safety connection, and a central link 30 arranged between the two lateral links 20, 40 and connected by a first pin 31 to the beam and by a second pin 32 to the said casing.

Abstract: This invention relates to an aircraft engine comprising means of suspension from an aircraft structure with means of transmitting forces between the engine casing and the aircraft structure, and a fail safe means. The engine is characterised by the fact that the said fail safe means includes an assembly of a safety clevis with two lugs and a tab or other equivalent means arranged between the two lugs, either the clevis or the tab being fixed to an element of the engine casing and the other tab or clevis being fixed to the said structure, a safety hinge pin previously fixed perpendicular to the axis of the engine passing through the tab and the clevis, the two lugs and the tab being parallel to the engine axis.

Abstract: The invention concerns the mount for an aircraft engine arranged to be attached firstly by a beam to the aircraft, and secondly by lateral and a median load transmission elements to the engine, the mount comprising an integrated load transmission and failsafe assembly arranged to ensure the continuity of load transmission in the event of failure of a load transmission element and to perform its failsafe function in unitary, concentrated fashion in the median zone of the mount. The mount is characterized by the fact that the load transmission and failsafe assembly comprises an assembly of a female clevis with two wings and of a projecting element passing with clearance through the two wings of clevis, one being integral with the engine and the other with the mounting beam.