| 摘要 |
Aircraft engine comprising a pod comprising, in sequence from front to back, an air inlet structure (6), fan cowls (7), thrust inverter cowls (8), and a nozzle (9), additional stiffening means are placed either in the air inlet structure (6) or between the fan cowls (7) and the thrust inverter cowls (8). This arrangement limits the clearance between fan cowls (7) and thrust inverter cowls (8), despite the pressure differences applied in flight on the air inlet structure (6), due to the aerodynamic air flow. This avoids the formation of an excessive parasite drag that would increase engine fuel consumption.
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