| 摘要 |
A turbofan gas turbine engine ( 10 ) comprises a fan rotor ( 32 ) carrying a plurality of radially extending fan blades ( 34 ). A fan blade containment assembly ( 38 ) surrounds the fan blades ( 34 ) and the fan blade containment assembly ( 38 ) comprises a generally cylindrical, or frustoconical, metal casing ( 40 ). The casing ( 40 ) comprises an annular member ( 54 ) positioned axially upstream of the tip ( 37 ) of the fan blade ( 34 ). The annular member ( 54 ) extends in a radially inwardly and axially downstream direction from the metal casing ( 40 ) towards the tip ( 37 ) of the fan blade ( 34 ). A set of acoustic panels ( 72 C) is also provided. A set of acoustic panels ( 72 B) is secured to the metal casing ( 40 ) by resilient fingers ( 80, 84 ) on the upstream and downstream ends ( 82,86 ) of the acoustic panels ( 72 B) which locate on the annular member ( 54 ) and the acoustic panels ( 72 C).
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