| 摘要 |
In order to reduce the overall weight of an engine assembly (1) for an aircraft and to increase the aerodynamic performance thereof, the invention proposes a rigid structure (34) of a mounting pylon (4) comprising a central box (36) and a box extension (54) connected to a reducing gear case (26) of the turboreactor (10). The box extension (54) includes two parts (60, 70) bearing the front engine attachments (7a, 7b, 7c), these pieces each comprising a structure (63, 73) forming a reinforcing rib of the central box (36), as well as two parts (32, 72) of horseshoe shape surrounding the reducing gear case (26). |
