Abstract: An exhaust nozzle flap for a turbine engine may include an exhaust nozzle flap linkage, an exhaust nozzle flap panel and a mounting pin. The linkage may include a first linkage segment that extends longitudinally from a linkage end to a second linkage segment, and a mounting aperture that extends transversely through the second linkage segment. The panel may include a first panel segment that extends longitudinally from a panel end to a second panel segment. The first panel segment may be pivotally engaged with the first linkage segment. The mounting pin may extend through and move transversely within the mounting aperture, and may be connected to the second panel segment.

Abstract: An exhaust nozzle flap for a turbine engine may include an exhaust nozzle flap linkage, an exhaust nozzle flap panel and a mounting pin. The linkage may include a first linkage segment that extends longitudinally from a linkage end to a second linkage segment, and a mounting aperture that extends transversely through the second linkage segment. The panel may include a first panel segment that extends longitudinally from a panel end to a second panel segment. The first panel segment may be pivotally engaged with the first linkage segment. The mounting pin may extend through and move transversely within the mounting aperture, and may be connected to the second panel segment.

Abstract: A duct includes first and second composite duct sections and first and second metallic support ring sections. The second metallic support ring section is adjacent to the first metallic support ring section.

Abstract: A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.

Abstract: A fastening system includes a first material having a first hole, a second material having a second hole, a bushing, and a threaded bolt. The bushing is located in the second hole and has a first end abutting the first material and a flanged second for securing the bushing to the second material. A threaded bolt extends through the first hole and into the bushing to secure the first material flush against the second material.

Abstract: A fastening system includes a first material having a first hole, a second material having a second hole, a bushing, and a threaded bolt. The bushing is located in the second hole and has a first end abutting the first material and a flanged second for securing the bushing to the second material. A threaded bolt extends through the first hole and into the bushing to secure the first material flush against the second material.

Abstract: A duct includes a first and second composite duct section and a first and second metallic support ring section the second metallic support ring section abuts the first metallic support ring section.

Abstract: A composite gas turbine engine duct receives a support ring that operates as an interface arrangement for attachment of engine system components. The support ring interfaces with the composite duct through a fastener shear load arrangement to provide a structurally sound interface which minimizes the risk of ply delamination.

Abstract: A composite engine case with an axial interface. One configuration includes an alternating mix of full length and partial plies, in order to provide the total thickness needed for the axial overlap. Another configuration provides only full-length structural plies with a flyaway insert adjacent the axial interface.

Abstract: An assembly includes first and second shell members. An anchor plate includes a body portion, first and second arrays of fastener openings, and anchor plate attachment features extending from a first side of the body portion and each having a fastener opening. Inserts are positioned within each fastener opening of the first array and the second array. A first set of fasteners is secured through the first array of fastener openings in the anchor plate, the first shell member and the splice plate and engaged with a corresponding one of the inserts. A second set of fasteners is secured through the second array of fastener openings in the anchor plate, the second shell member and the splice plate and engaged with a corresponding one of the inserts. A third set of fasteners is secured through the fastener openings of the anchor plate attachment features and the first shell member.

Abstract: A fastening system includes a first material having a first hole, a second material having a second hole, a bushing, and a threaded bolt. The bushing is located in the second hole and has a first end abutting the first material and a flanged second for securing the bushing to the second material. A threaded bolt extends through the first hole and into the bushing to secure the first material flush against the second material.

Abstract: A composite engine case with an axial interface. One configuration includes an alternating mix of full length and partial plies, in order to provide the total thickness needed for the axial overlap. Another configuration provides only full-length structural plies with a flyaway insert adjacent the axial interface.

Abstract: A composite gas turbine engine duct receives a support ring that operates as an interface arrangement for attachment of engine system components. The support ring interfaces with the composite duct through a fastener shear load arrangement to provide a structurally sound interface which minimizes the risk of ply delamination.