| 摘要 |
<p>The invention relates to a turbojet engine nacelle comprising a fixed structure comprising a fan casing (4) of said turbojet engine and a front frame (7) designed to be mounted downstream of said fan casing (4) and directly or indirectly supporting at least one flow deflecting means, said front frame being able to collaborate with a thrust reverser cowling (6) sliding between a closed position covering the flow-diverting means and an open position exposing this flow-diverting means allowing a diverted flow, characterized in that it further comprises at least one reinforcing structure (100) designed to transmit load between the fan casing (4) and the front frame (7), said reinforcing structure (100) extending along the longitudinal axis of the nacelle from the fan casing (4) toward the front frame (7) and being designed to support a third line of defence and/or an inhibiting device between the front frame (7) and the thrust reverser cowling (6).</p> |
