Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

Abstract: A capacitance probe monitors the distance between a blade tip and a fan, compressor or turbine case. The capacitance probe may be attached to a liner, and may travel with the liner as it radially expands due to thermal changes. The capacitance probe may include a circuit board sensor with a metallic plate, and one or more capacitors. The metallic plate may be encapsulated within an insulating material. A plurality of soft leads may be in electrical communication with the circuit board sensor, allowing a lower lead weight, reduced size and increased flexibility. The soft leads may also be embedded in the liner. In this way, the capacitance probe can record more accurate distance measurements and promote a gas turbine engine's continued and efficient operation.

Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

Abstract: The present disclosure relates to methods of manufacturing ice panel segments for turbofan engines. An ice panel material may be wrapped around a mandrel. The ice panel material may include an inner fiberglass layer, a plurality of KEVLAR® layers, and an outer fiberglass layer. The ice panel material may be bagged and cured into a rigid molded cylinder. The rigid molded cylinder may be radially cut into ice panel cylinders. The ice panel cylinders may be axially cut into ice panel segments. The ice panel segments may be bonded to an inner surface of a fan case.

Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.

Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.

Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades.

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 blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.

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 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 gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.

Abstract: An in situ fan case rub strip machining tool mounts to a LPT/fan rotor shaft assembly of a gas turbine engine. After a fan is removed therefrom such that the machining tool is rotatable about an engine axis of rotation in conjunction with rotation of the LPT/fan rotor shaft assembly. The machining tool permits machining of a rub strip within the fan case of the gas turbine engine without disassembly of the fan case from the core engine as heretofore required. As the machining tool is mounted to the LPT/fan rotor shaft assembly, the cutting tool is accurately locatable relative the engine axis of rotation such that the rub strip is evenly and precisely machined to be concentric with the engine axis to assure proper fan blade tip to rub strip interface.

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 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 turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades.

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 gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor.

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 fan section of a gas turbine engine having an axially extending centerline is provided. The fan section includes a fan assembly, a fan containment case, and a plurality of structural exit guide vanes. The fan assembly includes a fan rotor hub centered on and rotatable about the centerline, and a plurality of fan blades that are attached to and extend radially out from the fan rotor hub. The fan containment case is disposed radially outside of and circumferentially around the fan assembly. The fan containment case includes a shell and an integral flange ring that extends around the circumference of the shell, a circumferentially extending blade outer air seal disposed between the fan blades and the shell. The structural exit guide vanes are mechanically attached to the fan containment case at a position aligned with the integral flange ring.