| 摘要 |
The system has a bypass turbojet engine and a nacelle (10) borne by an intermediate case that delimits an annular space for the flow of bypass air around a turbojet (12). A rigid downstream cylindrical part (20) i.e. outer fixed structure, has an upstream end with an annular attachment flange of 180 degrees over an external circumference of a case. The downstream cylindrical part supports and guides the turbojet exhaust case at a downstream end. A longitudinal beam (26) attaches securing members (28) i.e. rods, for securing the engine to parts of the airplane. |
