초록 ▼

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 th

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.

대표청구항 ▼

The invention claimed is: 1. A mount for an aircraft engine configured to be attached firstly by a mounting beam to an aircraft, and secondly by lateral load transmission elements and a median load transmission element to the aircraft engine, wherein said lateral and median load transmission elemen

The invention claimed is: 1. A mount for an aircraft engine configured to be attached firstly by a mounting beam to an aircraft, and secondly by lateral load transmission elements and a median load transmission element to the aircraft engine, wherein said lateral and median load transmission elements transmit loads from the engine to the aircraft during normal operation of said mount, the mount comprising: said mounting beam; said lateral load transmission element; and an integrated load transmission and failsafe assembly including said median load transmission element, said integrated load transmission and failsafe assembly being configured to ensure continuity of load transmission for said loads transmitted from the engine to the aircraft in the event of failure of one of said lateral and median load transmission elements, wherein the load transmission and failsafe assembly comprises a female clevis with two wings and a projecting failsafe element passing with clearance through the two wings of said female clevis, one of said female clevis and said projecting failsafe element being integral with the aircraft engine or with an intermediate case of said aircraft engine and the other of said female clevis and said projecting failsafe element being integral with the mounting beam, wherein said clearance between said projecting failsafe element and said two wings of said female clevis extends around an entire circumference of said projecting failsafe element. 2. A mount as in claim 1, wherein a portion of said mounting beam is arranged between said two wings of said female clevis and the projecting failsafe element is mounted through said portion of the mounting beam arranged between the two wings of said female clevis. 3. A mount as in claim 1, wherein said median load transmission element is positioned between said two wings of said female clevis, and wherein the female clevis defines a radial housing between said two wings, wherein said radial housing is configured to receive the median load transmission element. 4. A mount as in claim 1, wherein said integrated load transmission and failsafe assembly comprises means for transmitting loads via the two wings of the female clevis, the projecting failsafe element and the mounting beam in the event of failure of one of said lateral load transmission elements. 5. A mount as in claim 1, wherein said integrated load transmission and failsafe assembly comprises means for transmitting vertical loads via the two wings of the female clevis, the projecting failsafe element and the mounting beam in the event of failure of the median load transmission element. 6. A mount as in claim 1, wherein said integrated load transmission and failsafe assembly comprises means for transmitting thrust loads via the two wings of the female clevis and the mounting beam in the event of failure of the median load transmission element. 7. A mount as in claim 1 which is a forward mount attached to said intermediate case of the aircraft engine. 8. A mount as in claim 1, wherein said aircraft engine has an outer fan duct configured to be attached to an aircraft fuselage of said aircraft. 9. A mount as in claim 1, wherein said female clevis is integral with the intermediate case of said aircraft engine such that there is no joint between said female clevis and said aircraft engine, and wherein said projecting failsafe element is integral with the mounting beam. 10. A mount as in claim 1, wherein said projecting failsafe element is integral with the intermediate case of said aircraft engine and said female clevis is integral with the mounting beam. 11. A mount as in claim 1, wherein said two wings of said female clevis extend substantially in planes orthogonal to a thrust axis of said aircraft engine. 12. A mount as in claim 1, wherein said median load transmission element is positioned between said two wings of said female clevis, wherein said median load transmission element includes a transmitting pin connected to and extending away from a central portion of said mounting beam and toward said aircraft engine, said median load transmission element further including a ball joint fixed to said transmission pin. 13. A mount as in claim 12, wherein said ball joint is housed in a ball-joint housing located between the two wings of the female clevis. 14. A mount as in claim 13, wherein said median load transmission element is fixed to said intermediate case of said engine. 15. A mount as in claim 13, wherein said median load transmission element further includes a plate mounted between said ball joint and said central portion of said mounting beam, wherein said plate is screwed to said intermediate case of said aircraft engine. 16. A mount as in claim 1, wherein said median load transmission element includes a spigot that is, during normal operation, integral with a platform on an intermediate case of said engine, and wherein said spigot is further integral, during normal operation, with a central portion of said mounting beam, said central portion being attached to a pylon of said aircraft.