Abstract: A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.

Abstract: A fan case for a gas turbine engine includes a composite fan containment case that includes an outer surface. The composite fan containment case includes multiple composite layers that define a generally cylindrical case. An attachment flange extends radially outward from the cylindrical case. The attachment flange comprises a portion of the composite layers. A metallic backing ring is secured to the attachment flange by rivets.

Abstract: A disclosed fan containment case includes a fan case fabricated from a plurality of non-metallic composite layers with an attachment flange formed of both a composite portion and a metallic backing. The disclosed metallic backing is mounted on a rearward facing surface of a composite portion of the attachment flange.

Abstract: A disclosed fan containment case includes a mount ring that supports a portion of the engine core. The mount ring includes openings and features that define a mounting location for the gas turbine engine. The example fan containment case includes a generally cylindrically shaped fan case that extends between an open front end and an open rear end. The mount ring is secured onto an outer surface of the fan case and includes a mounting lug and a plurality of openings for attachment of gas turbine engine components.

Abstract: A composite fan case includes a composite fan case body having an outer surface. A bolt attachment is attached to the outer surface of the fan case and has an internal composite boss with at least one threaded metallic insert. The boss is attached to the outer surface of the fan case with a combination of fiber reinforced ply and adhesive. A bolt attachment and a method of attaching components to the outer periphery of the composite fan case are also disclosed.

Abstract: A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case.

Abstract: A gas turbine engine fan section includes first and second composite layers providing a generally cylindrical case. Axially spaced apart rings are arranged between the first and second composite layers and form reinforcing ribs that provide a fan containment area axially between the rings. A belt is arranged over and spans the fan containment area between the reinforcing ribs. A fan blade has a tip in proximity to the first composite layer without any intervening structural support between the tip and the first composite layer, which provides a fan blade rub resistant surface. A method of manufacturing a fan containment case includes wrapping at least one first composite layer around a mandrel. Axially spaced apart rings are arranged circumferentially about the first composite layer. At least one second composite layer is wrapped around the rings and first composite layer to provide reinforcing ribs at the rings.

Abstract: A hollow article includes a metallic hollow article formed from a having a first major surface, an internal cavity with an opening in the first major surface, and a socket around the opening; a cover of composite material received in the socket and covering the opening; and a filler material of foam in the internal cavity.

Abstract: An example composite fan case assembly includes a composite fan case body disposed on an axis. The fan case body has a radially inner surface and a radially outer surface. There is at least one mounting attachment to receive a threaded member. The at least one mounting attachment includes a base component and a spool component. The base component extends through an opening in the fan case body from the radially outer surface and toward the radially inner surface of the fan case body. The base component including a base portion, a boss having a non-cylindrical profile, and a cylindrical portion. The mounting attachment also includes a spool component disposed on the radially outer surface and attached to the base component. The spool component receives at least a portion of the base component. An outer surface of the cylindrical portion and an inner surface of the spool component are threaded and correspondingly mate to lock the spool component relative to the base component.

Abstract: A preform sheet for a composite component comprises a body section and a flange section. The preform body section includes a plurality of axial tows braided with at least a plurality of first bias tows and a plurality of second bias tows. The preform flange section includes a first braided flange layer and a second braided flange layer. The first braided flange layer is defined by the first and second braided bias tows of the preform body section extending into the flange section. Neither the first nor second braided flange layers have axial tows.

Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.

Abstract: A fan containment case for a gas turbine engine includes a first inner layer and a second layer outside the first inner layer, where the second layer is made of a first material having a first fabric architecture. The fan containment case also includes a third layer outside of the second layer, where the third layer is made of a second material having a second fabric architecture, and at least one of the first material and the first fabric architecture of the second layer is different from the second material and the second architecture, respectively, of the third layer. A fourth outer layer is located outside of the third layer.

Abstract: A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.

Abstract: 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.

Abstract: A fan section of a gas turbine engine includes a fan case structure having a first coefficient of thermal expansion. A fan blade is arranged within the fan case structure and has a second coefficient thermal expansion. A continuous ring-shaped liner surrounds the fan blade and includes a third coefficient of thermal expansion that is substantially similar to the second coefficient of thermal expansion and substantially different than the first coefficient of thermal expansion. An elastomeric adhesive operatively connects the liner to the fan case structure. The adhesive is configured to accommodate diametrical change in the liner and maintain a desired radial tip clearance throughout various fan section operating temperatures.

Abstract: An example composite fan case assembly includes a composite fan case body disposed on an axis. The fan case body has a radially inner surface and a radially outer surface. There is at least one mounting attachment to receive a threaded member. The at least one mounting attachment includes a base component and a spool component. The base component extends through an opening in the fan case body from the radially outer surface and toward the radially inner surface of the fan case body. The base component including a base portion, a boss having a non-cylindrical profile, and a cylindrical portion. The mounting attachment also includes a spool component disposed on the radially outer surface and attached to the base component. The spool component receives at least a portion of the base component. An outer surface of the cylindrical portion and an inner surface of the spool component are threaded and correspondingly mate to lock the spool component relative to the base component.

Abstract: A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case.

Abstract: A composite fan case includes a composite fan case body having an outer surface. A bolt attachment is attached to the outer surface of the fan case and has an internal composite boss with at least one threaded metallic insert. The boss is attached to the outer surface of the fan case with a combination of fiber reinforced ply and adhesive. A bolt attachment and a method of attaching components to the outer periphery of the composite fan case are also disclosed.

Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.

Abstract: A disclosed fan containment case includes a mount ring that supports a portion of the engine core. The mount ring includes openings and features that define a mounting location for the gas turbine engine. The example fan containment case includes a generally cylindrically shaped fan case that extends between an open front end and an open rear end. The mount ring is secured onto an outer surface of the fan case and includes a mounting lug and a plurality of openings for attachment of gas turbine engine components.