A method for suspending a fan case and a fan case assembly in which a fan case is suspended are disclosed herein. The fan case assembly (46) includes an inner ring (68) encircling an axis. The fan case assembly also includes a first outer ring (70) encircl...

A containment casing is provided comprising a radially outer layer; an intermediate energy absorbing layer, and a retention framework for retaining an aerofoil blade in the event of detachment of whole or part of the blade. The retention framework is distr...

An impactor containment system including a laminate material, the laminate material comprising a face sheet (1), a cellular filling providing a crushable layer (2) one side of which layer is arranged on the face sheet (1), and a stiff backing layer (3) arr...

A containment assembly for a turbo fan engine, comprises a casing (30) arranged in use around a rotatable fan, to form a duct for the fan, the containment assembly comprising at least one liner element (32) disposed on an interior surface between the casin...

A turbomachine casing assembly comprises a first casing portion for at least partially encasing one or more rotating aerofoil structures of a turbomachine and a second casing portion; the first casing portion being movable with respect to the second casing...

The engine has a fan integrated with a drive shaft (5) that is supported by bearings (6, 7). The bearing (7) has an inner ring integrated with the shaft and outer ring fixed on a flange (18) of a fixed structure. A retaining disc (28) is mounted on an annu...

A fan casing (10) for a gas turbine engine is provided which combines the functions of blade containment and noise suppression. The fan casing has an annular metallic inner shell (14) with a plurality of holes (17) are formed therethrough. An acoustic abso...

A joint assembly 80 for limiting an extension of the joint 80 in the direction of a load path derived from an impact comprising a first member 40 having a portion 82 and a second member 50 having a portion 84, the portions 82, 84 overlapping one another an...

A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a transition portion (58) and a blade containment portion (54). The upstream portion (56) has a f...