A containment assembly for a turbo fan engine, has a casing arranged in use around a
rotatable fan, to form a duct for the fan and a liner element disposed on an interior surface …

An apparatus includes first, second, and third layers. The first layer includes a plurality of
flanges. The second layer includes a deformable membrane. The second layer is con …

A containment system for a gas turbine engine includes a fan track assembly for use with a
containment case. The fan track assembly includes a body of collapsible material that is …

Gas turbine engine fan blade containment systems are disclosed. An example fan blade
containment system includes a shield to be coupled to an aircraft structure and to at least …

US8061967B2 - Panel for supporting abradable material in a turbomachine - Google
Patents US8061967B2 - Panel for supporting abradable material in a turbomachine …

A fan case for a gas turbine engine includes a fan case surrounding a fan with fan blades. A
liner is disposed between the fan case and the fan and is spaced a radial distance from the …

Gas turbine engine fan blade containment systems are disclosed. An example fan blade
containment system includes a shield to be coupled to an aircraft structure and to at least …

US9789534B2 - Investment technique for solid mold casting of reticulated metal foams -
Google Patents US9789534B2 - Investment technique for solid mold casting of reticulated …

A turbomachine casing assembly includes a first casing element locatable radially outward
of one or more rotating aerofoil elements of a turbomachine, a second casing element …

A fan containment system arranged to be fitted around an array of radially extending fan
blades mounted on a hub in an axial gas turbine engine. Each fan blade has a respective …