An airfoil material loss control structure is provided. This structure includes at least one fuse zone that, during impact from a foreign object, fail before the surrounding structure. In a further aspect, a rotary machine is provided. This rotary machine includes a ducted fan gas turbine engine including a composite airfoil with at least one fuse zone.

An air turbine starter includes a support structure and a turbine having a shaft and a rotor that extends away from the shaft in a radial direction. The air turbine starter also includes a mount structure that supports the turbine for rotation relative to the support structure. The mount structure is configured to transfer a force from the turbine to the support structure. The mount structure includes a deformable member that is configured to deform when the force exceeds a predetermined threshold.

An epicyclic gear assembly includes a carrier that includes a first plate axially spaced from a second plate. At least one epicyclic gear set is located between the first plate and the second plate. The first plate is configured to rotate with an output of the epicyclic gear assembly. A first bearing race is attached to the first plate for supporting a first bearing. A second bearing race is attached to the second plate for supporting a second bearing.

A fibrous texture has the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion and in a lateral direction over a determined width between a first lateral edge and a second lateral edge. The fibrous texture has a three-dimensional or multi-layer weaving between a plurality of layers of warp strands extending in the longitudinal direction and a plurality of layers of weft strands extending in the lateral direction, the fibrous texture including first and second longitudinal sections extending over a width from the first or second lateral edge smaller than the determined width of the fibrous texture along the lateral direction. The first and second longitudinal sections each include warp strands and weft strands constituted by carbon fibers. The fibrous texture further includes a third section present between the first and second sections.

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan track liner comprising abradable material layer, and a rear acoustic panel arranged aft of the fan track liner. The fan track liner and the rear acoustic panel are integrated into a single panel structure attached to the fan case inner surface.

A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.

According to one aspect, a clutch mechanism includes a control member. The control member is adapted to receive motive power and includes a first dry clutch member and a first viscous clutch member. The clutch mechanism further includes an output member that includes a second dry clutch member and a second viscous clutch member. The first and second dry clutch members form a dry clutch and the first and second viscous clutch members form a viscous clutch. The clutch mechanism further includes an actuation arm coupled to at least one of the control and output members. The actuation arm is selectively controllable to effect relative movement of the control and output members such that one of the dry and viscous clutches is selectively engaged.

An air turbine starter having a housing, at least one turbine member, and a containment structure. The housing having an interior surface defining an interior. The at least one turbine member rotatably mounted within the interior and having a plurality of circumferentially spaced blades. The containment band having a radially outer surface, a radially inner surface, at least one layer of metal alloy, and at least one layer of shape memory alloy.