| 摘要 |
A gas turbine engine for powering an aircraft, said engine extending axially from upstream to downstream and comprising a composite component (3), a metal component (2) and a flexible device (4) for fixing said components (2, 3) together, said fixing device (4) comprising: - a flexible connecting element (5) comprising a first fixing part (51) connected to the metal component (2) by an axial connection (B1) and a second fixing part (53) connected to the composite component (3) by an axial connection (B2), the said connecting element (5) comprising a free end (55) that extends axially; and - a rigid locking element (6) comprising a fixing part (61) connected to the metal component (2) by an axial connection (B1) and a free end (63) extending axially, the free end (63) of the locking element (6) being radially aligned with the free end (55) of the connecting element (5) so as to limit the deformation suffered by the connecting element (5) during engine operation. |
