United Technologies Corporation

Raytheon Technologies Corporation

Francis R Moon

Daniel Bernard Kupratis

Jeffrey Michael Jacques

Richard W Monahan

Claude I Barnett

Arthur W Utay

John F Corini

Gianfranco D Conti

Lars H Vestergaard

A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.

Reverse core gear turbofan

In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and a door operatively associated with the second and third air ducts of the gas turbine engine. The door may have at least an open position allowing air from the second air duct to flow into the third air duct and a closed position preventing air from flowing between the ducts.

Gas turbine engine with stream diverter

A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.

Variable exhaust mixer and cooler for a three-stream gas turbine engine

A gas turbine engine includes a spool configured to rotate about an axial centerline. The spool includes a fan rotor and a cold turbine rotor. The fan rotor is rotatably driven by the cold turbine rotor. A cold turbine inlet passage is configured to direct an airflow along a radial inward trajectory to the cold turbine rotor.

Gas turbine engine with cold turbine and multiple core flowpaths

The engine () includes a low spool () disposed aft of an air inlet () and a high spool () disposed aft of the low spool (). An intake reverse-duct () is disposed radially outward of the high spool () and reverses direction of low pressure compressed air from the low spool () into a forward-flow high pressure compressor () of the high spool (). A discharge reverse-manifold () directs flow of an exhaust gas stream (} from a forward-flow low pressure turbine () into a rearward-flow direction and into at least one pulse detonation firing tube (). An annular bypass air duct () directs cooling air along the engine ()&#x2014;The at least, one firing tube is positioned radially outward of the high spool (), overlies the high spool () and is also positioned within the bypass air duct ().

Reverse-flow core gas turbine engine with a pulse detonation system

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.

A gas turbine engine includes a bypass flow path. A core flow path has a reverse duct configured to reverse a direction of core flow. The core flow path includes an exhaust duct in fluid communication with the bypass flow path and is configured to introduce core exhaust flow in the core flow path back into the bypass flow path. A splitter is arranged in the bypass flow path and adjoins the exhaust duct.

Gas turbine engine with reverse-flow core having a bypass flow splitter

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.

Turbine engine exhaust nozzle flap

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.

Attachment interface for a gas turbine engine composite duct structure

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.

Threaded flanged bushing for fastening applications

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.

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.

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Granby, CT, United States of America

Francis R Moon