AIRCRAFT PROPELLER ASSEMBLY COMPRISING A TURBOJET ENGINE, A MAST AND MEANS OF ATTACHING THE TURBOJET ENGINE TO THE MAST

The propulsion assembly for aircraft turbojet engines redistributes forces through a pin and pallet assembly, central connecting rods, and a triangular shackle, addressing force management issues in existing systems, improving load distribution and safety.

FR3131734B1Active Publication Date: 2026-04-10AIRBUS OPERATIONS (SAS)
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Patent Information

Application Number
FR2022000109
Authority / Receiving Office
FR · FR
Patent Type
Patents
Current Assignee / Owner
Filing Date
2022-01-07
Publication Date
2026-04-10
Estimated Expiration
2042-01-07

AI Technical Summary

Technical Problem

Existing propulsion systems for aircraft turbojet engines under the wing fail to effectively distribute and manage the various forces generated by the engine, particularly at the front engine attachment and thrust force recovery device, leading to a desire for a different arrangement that enhances force redistribution.

Method used

A propulsion assembly comprising a turbojet engine, a mast, and a hooking device that redistributes forces through a pin and pallet assembly, central connecting rods, and a triangular shackle, allowing force resumption in three different planes with redundant connections for safety, using cylindrical pins, half-pawns, and a sleeve for continuous operation.

Benefits of technology

The new arrangement improves load distribution by compensating bending and torsional moments, ensuring robust force transfer and maintaining connection integrity even in the event of damage, enhancing the safety and efficiency of the propulsion system.

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Abstract

PROPULSION ASSEMBLY FOR AIRCRAFT COMPRISING A TURBOJET ENGINE, A MAST AND MEANS OF ATTACHING THE TURBOJET ENGINE TO THE MAST The invention relates to a propulsion assembly (100) comprising a turbojet engine (102) with a central casing (112), an attachment mast (104) with a front wall (106e), a front engine attachment (152) and a device (156) for taking up thrust forces. The front engine mount (152) comprises a pin (164) integral with the front wall (106e) and at least one pallet (166a-b), each of which has a bore (168) fitted onto the pin (164) and is hinged on either side of a median plane (P) to an upper portion of the central housing (112) via a connection point to a front fitting (153). With this arrangement, the forces are transferred in pairs at different planes. The front mount (152) is more compact, and the forces are reduced in the central connecting rods, known as 'thrust' rods. Fig. 2
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