Abstract: A cascade-variable area fan nozzle system (the “CVAFN System”) is provided. The CVAFN system may comprise a cascade portion and a variable area fan nozzle (“VAFN”) portion. The VAFN portion may include a VAFN panel. The cascade and VAFN panel may be integrally formed with one another. The CVAFN system may include an actuation system (e.g., a jack screw) that is configured to translate the cascade and VAFN panel forward and aft. The cascade and VAFN panel may be translated aft in response to activation of the thrust reverser and/or CVAFN system.

Abstract: In various embodiments, the thrust vectoring systems described herein create variable reverse thrust during a landing event. The reverse thrust may be varied based on manual inputs, dynamically changing operating events, or a landing duty cycle. In various embodiments, the thrust vectoring systems comprise a movable shelf that is capable of adjusting a directing a fluid flow to create a variable reverse thrust which may reduce the risk of foreign object ingestion in the engine at lower ground speeds.

Abstract: An aircraft propulsion system may include a generally annular fan case defined by a fan configured to be disposed at a forward end thereof and a stator blade array configured to be disposed at an aft end thereof, a thrust reversing assembly comprising at least a portion of the fan case, the fan case comprising a generally annular cascade array, and/or a sleeve situated at least partially about the cascade array, the sleeve configured to deploy to expose the cascade array. The aircraft propulsion system may further comprise a blocker door coupled to at least one of the cascade array and an inner surface of the fan case, the blocker door configured to deploy to redirect airflow through the cascade array.

Abstract: Nacelle air management systems for a high bypass ratio engine are provided. The nacelles air management systems may include an outer cowl and an inner cowl that are configured to provide dual bypass flow channels around an engine core. These systems may be employed to accommodate larger engine fans. The nacelle air management system may also include one or more blocker doors are configured to at least partial obstruct and/or direct air from the dual bypass flow channels to create reverse thrust.

Abstract: A hybrid beam for support of a nacelle panel of a jet engine is disclosed. The beam is comprised of a first longitudinal composite panel and a second longitudinal composite panel, wherein the first longitudinal composite panel is integrally affixed to the second longitudinal composite panel along a longitudinal edge. The composite panels form a composite beam structure that is substantially open with a cross-section that is generally “L-shaped”. A plurality of hinge stations are affixed to a first side of the first longitudinal composite panel and at least one track guide is disposed on a second side of the first longitudinal composite panel. The track guides receive a head portion of a slider that is fixed to the translating jet engine nacelle panel. Each hinge station further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam.

Abstract: A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil.

Abstract: In various embodiments, the thrust vectoring systems described herein create variable reverse thrust during a landing event. The reverse thrust may be varied based on manual inputs, dynamically changing operating events, or a landing duty cycle. In various embodiments, the thrust vectoring systems comprise a movable shelf that is capable of adjusting a directing a fluid flow to create a variable reverse thrust which may reduce the risk of foreign object ingestion in the engine at lower ground speeds.

Abstract: A cascade-variable area fan nozzle system (the “CVAFN System”) is provided. The CVAFN system may comprise a cascade portion and a variable area fan nozzle (“VAFN”) portion. The VAFN portion may include a VAFN panel. The cascade and VAFN panel may be integrally formed with one another. The CVAFN system may include an actuation system (e.g., a jack screw) that is configured to translate the cascade and VAFN panel forward and aft. The cascade and VAFN panel may be translated aft in response to activation of the thrust reverser and/or CVAFN system.

Abstract: The thrust vectoring systems described herein create variable reverse thrust during a landing event. The reverse thrust may be varied based on manual inputs, dynamically changing operating events, or a landing duty cycle. The thrust vectoring systems comprise a movable shelf that is capable of adjusting a directing a fluid flow to create a variable reverse thrust which may reduce the risk of foreign object ingestion M the engine at lower ground speeds.

Abstract: An aircraft propulsion system may include a generally annular fan case defined by a fan configured to be disposed at a forward end thereof and a stator blade array configured to be disposed at an of end thereof, a thrust reversing assembly comprising at least a portion of the fan case, the fan case comprising a generally annular cascade array, and/or a sleeve situated at least partially about the cascade array, the sleeve configured to deploy to expose the cascade array. The aircraft propulsion system may further comprise a blocker door coupled to at least one of the cascade array and an inner surface of the fan case, the blocker door configured to deploy to redirect airflow through the cascade array.

Abstract: In various embodiments, the thrust vectoring systems described herein create variable reverse thrust during a landing event. The reverse thrust may be varied based on manual inputs, dynamically changing operating events, or a landing duty cycle. In various embodiments, the thrust vectoring systems comprise a movable shelf that is capable of adjusting a directing a fluid flow to create a variable reverse thrust which may reduce the risk of foreign object ingestion in the engine at lower ground speeds.

Abstract: Nacelle air management systems for a high bypass ratio engine are provided. The nacelles air management systems may include an outer cowl and an inner cowl that are configured to provide dual bypass flow channels around an engine core. These systems may be employed to accommodate larger engine fans. The nacelle air management system may also include one or more blocker doors are configured to at least partial obstruct and/or direct air from the dual bypass flow channels to create reverse thrust.

Abstract: A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil.

Abstract: A hybrid beam for support of a nacelle panel of a jet engine is disclosed. The beam is comprised of a first longitudinal composite panel and a second longitudinal composite panel, wherein the first longitudinal composite panel is integrally affixed to the second longitudinal composite panel along a longitudinal edge. The composite panels form a composite beam structure that is substantially open with a cross-section that is generally “L-shaped”. A plurality of hinge stations are affixed to a first side of the first longitudinal composite panel and at least one track guide is disposed on a second side of the first longitudinal composite panel. The track guides receive a head portion of a slider that is fixed to the translating jet engine nacelle panel. Each hinge station further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise comprises: (a) a core portion comprising at least one entrance end and at least one exit end for the passage of acoustic energy therethrough; (b) a first member having an exterior face and an interior face, wherein the first member is adjacent to at least a part of the core portion, and the first member has a plurality of openings therein to permit the passage of acoustic energy therethrough; and (c) a second member having an exterior face and an interior face, wherein the interior face of the second member is adjacent to the core portion. The core portion may be a honeycomb acoustic structure, and the first member may be perforated to permit the passage of acoustic energy into and out of the conduit portion.

Abstract: A thrust reverser for a turbofan engine having an air duct defined radially inwardly by a wall around the turbofan engine and radially outwardly in part by a fan cowl of the engine. A bulkhead is adapted to be mounted on the fan cowl having a shaped surface defining an upstream wall. A translating cowl is supported for movement axially between a closed position substantially adjacent the bulkhead and an open position spaced axially apart from the bulkhead so as to form an outlet for discharge of air from the air duct. The translating cowl has a first wall and a kicker plate defining a shaped surface. The kicker plate and/or the bulkhead may have a dimension which varies at different radial locations about a circumference of the translating cowl to selectively control the forward component of velocity of the air discharged from the air duct. A plume control device may extend longitudinally across the outlet to divide the air discharged from the air duct into a plurality of plumes.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise comprises: (a) a core portion comprising at least one entrance end and at least one exit end for the passage of acoustic energy therethrough; (b) a first member having an exterior face and an interior face, wherein the first member is adjacent to at least a part of the core portion, and the first member has a plurality of openings therein to permit the passage of acoustic energy therethrough; and (c) a second member having an exterior face and an interior face, wherein the interior face of the second member is adjacent to the core portion. The core portion may be a honeycomb acoustic structure, and the first member may be perforated to permit the passage of acoustic energy into and out of the conduit portion.

Abstract: A thrust reverser for a turbofan engine having an air duct defined radially inwardly by a wall around the turbofan engine and radially outwardly in part by a fan cowl of the engine. A bulkhead is adapted to be mounted on the fan cowl having a shaped surface defining an upstream wall. A translating cowl is supported for movement axially between a closed position substantially adjacent the bulkhead and an open position spaced axially apart from the bulkhead so as to form an outlet for discharge of air from the air duct. The translating cowl has a first wall and a kicker plate defining a shaped surface. The kicker plate and/or the bulkhead may have a dimension which varies at different radial locations about a circumference of the translating cowl to selectively control the forward component of velocity of the air discharged from the air duct. A plume control device may extend longitudinally across the outlet to divide the air discharged from the air duct into a plurality of plumes.

Abstract: An improvement in the translating cowl of a cascade type thrust reverser for a high bypass aircraft jet engine that provides a novel blocker door frame arrangement for the inner panel of such cowl. A plurality of forwardly opening spaced circumferentially arranged apertures are provided in the inner panel of the translating cowl and an outer edge portion of a one piece imperforate blocker door frame is sealingly inserted in each such opening by extending the edge portion between the facing sheets of the inner panel for bonding thereto. Each blocker door frame is configured to receive a blocker door that is hinged to such frame at the forward portion of the frame and which is connected by a drag link to a core cowl of the aircraft engine. An annular reinforcing section is secured to the inner surfaces of the blocker door frames and to an end slider portion of the translating cowl for longitudinal reciprocal motion.