| 摘要 |
A duct wall 2 of a fan casing of a gas turbine engine comprises an intake section 4 and a containment casing 6, which are interconnected by bolts 50 at flanges 20, 22. An acoustic flutter damper 28 is provided between the flanges 20, 22 to reduce or eliminate flutter arising in blades 18 of the fan at certain important operating conditions. The damper 28 provides flexibility at the connection between the intake section 4 and the containment casing 6 so that, in the event of detachment of a blade 18 or a bladed fragment, the resulting deflection wave in the containment casing 6 can be accommodated by displacement and/or deformation of the acoustic flutter damper 28, reducing the risk that the bolts 50 will shear to allow the intake section 4 and the containment casing 6 to become detached from each other. The acoustic flutter damper 28 may comprise a circumferential array of separate segments 34 ( Figure 3 ).
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