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公开(公告)号：US20230132103A1
公开(公告)日：2023-04-27
申请号：US17971680
申请日：2022-10-24
发明人： Lionel CZAPLA , Frédéric PIARD
IPC分类号： B64D29/00
摘要： An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.
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公开(公告)号：US20230061579A1
公开(公告)日：2023-03-02
申请号：US17893555
申请日：2022-08-23
申请人： Woodward, Inc.
发明人： Matthew Polley , Dragan Micic , Kamran Eftekhari Shahroudi , Joseph Thomas Kopecek , James Cale
摘要： The subject matter of this specification can be embodied in, among other things, a system that includes a flexible structure, a power inverter, a first electromechanical device configured to urge movement of a first portion of the flexible structure based on power received from the power inverter, a second electromechanical device configured to urge movement of a second portion of the flexible structure based on power received from the power inverter, a feedback sensor configured to provide a feedback signal indicative of alignment between the first portion and the second portion, and a controller configured to control operation of at least one of the first electromechanical device and the second electromechanical device based on the feedback signal.
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公开(公告)号：US20230058015A1
公开(公告)日：2023-02-23
申请号：US17979393
申请日：2022-11-02
发明人： Gary D. Roberge
摘要： A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.
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公开(公告)号：US20230038787A1
公开(公告)日：2023-02-09
申请号：US17758650
申请日：2021-01-14
摘要： Disclosed is an air outlet of a nacelle for an aircraft turbojet engine, the nacelle forming a solid of revolution about a longitudinal axis, the air outlet having a straightening device having a plurality of flaps mounted circumferentially and protruding, each flap being mounted pivoting around a pivot axis, forming, with respect to the longitudinal axis, an angle of convergence in a radial plane, between a closed position, in which each flap extends along the pivot axis in the aerodynamic prolongation of the trailing edge in order to support a thrust phase and a deployed position, in which each flap extends in a deployed plane forming an angle of deployment with respect to the closed position about the pivot axis, so as to support a reverse thrust phase.
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公开(公告)号：US11560847B2
公开(公告)日：2023-01-24
申请号：US17224514
申请日：2021-04-07
申请人： Rohr, Inc.
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.
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公开(公告)号：US11548652B2
公开(公告)日：2023-01-10
申请号：US17327048
申请日：2021-05-21
摘要： A nacelle may comprise an inlet cowling comprising an inlet cowling aft edge having an aft edge length; a boat tail cowling comprising a boat tail cowling forward edge having a forward edge length, wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be shorter than the aft edge length, forming a step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge. The nacelle may further comprise a transition fairing coupled to the boat tail cowling, wherein the transition fairing comprises a fairing forward edge disposed adjacent to the inlet cowling aft edge and a fairing ramp surface spanning between the inlet cowling aft edge and a boat tail cowling external surface.
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公开(公告)号：US20230002065A1
公开(公告)日：2023-01-05
申请号：US17363424
申请日：2021-06-30
申请人： Rohr, Inc.
摘要： An assembly is provided for an aircraft structure. This aircraft structure assembly includes an acoustic panel and a thermal anti-icing system. The acoustic panel includes an exterior surface. The thermal anti-icing system includes a susceptor and a microwave system. The susceptor is configured with the acoustic panel. The microwave system is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.
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公开(公告)号：US11519295B2
公开(公告)日：2022-12-06
申请号：US16207799
申请日：2018-12-03
发明人： Gary D. Roberge
IPC分类号： F01D25/14 , F01D25/12 , B64D29/00 , B64D33/08 , F28D21/00 , B22F5/00 , F01D25/18 , F02K3/06 , B22F10/20
摘要： A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.
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公开(公告)号：US11512665B2
公开(公告)日：2022-11-29
申请号：US16826092
申请日：2020-03-20
申请人： The Boeing Company
发明人： Sam Miao
摘要： Locking linear actuators, thrust reversers for aircraft that include the locking linear actuators, and methods of manufacturing the locking linear actuators. The disclosed locking linear actuators include an actuator housing that defines a bore housing an actuator piston and a lock sleeve. A portion of the actuator piston defines a lock aperture, housing a locking tab capable of radial movement. When the actuator is retracted, the locking tab engages with a step in the surface of the bore to lock the linear actuator, a distal portion of the lock sleeve extends into a portion of the actuator piston to prevent the locking tab from disengaging from the step in the surface of the bore.
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公开(公告)号：US11434000B2
公开(公告)日：2022-09-06
申请号：US16845262
申请日：2020-04-10
申请人： SAFRAN
摘要： A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section, a downstream end of which forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and wherein the downstream end forming the outlet section has a pneumatic or hydraulic annular actuator extending around the axis of rotation and configured to deform radially under a predetermined control pressure so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.
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