| 摘要 |
The invention discloses a confinement structure for a turbojet engine to retain and confine fragments of a rotor blade. The structure has three zones of varying vulnerability to the blade fragments so as to maximize the confinement of such fragments, while minimizing the weight of the structure. A first zone, located in the plane of rotation of the rotor blade wheel confines the small fragments which may impact in this zone. A second zone, adjacent to the first, but located downstream, contains a retention belt structure to absorb the energy generated by contact with the larger blade fragments. Finally, a third zone, downstream of the second zone, defines a containment chamber to retain the larger blade fragments. |
