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公开(公告)号：US12116930B2
公开(公告)日：2024-10-15
申请号：US18254775
申请日：2021-11-24
摘要： A scoop for an aircraft turbine engine, this scoop including a body which is movable between at least two positions, including a first position in which it is configured to capture part of a first air stream flowing in a first direction, wherein the body is movable into a second position in which it is configured to capture part of a second air stream flowing in a second direction which is opposite to the first direction, and wherein the body is mounted to move freely between the at least two positions so as to automatically adopt the first position when the first air stream flows, and to automatically adopt the second position when the second air stream flows.
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2.发明授权公开(公告)号：US11913403B2
公开(公告)日：2024-02-27
申请号：US17758037
申请日：2020-12-18
申请人： SAFRAN NACELLES
摘要： A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.
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公开(公告)号：US11873781B1
公开(公告)日：2024-01-16
申请号：US17878497
申请日：2022-08-01
申请人： Rohr, Inc.
发明人： Julian Winkler , Wentaur E. Chien , Xiaolan Hu , Landy Dong
IPC分类号： F02K1/72 , F02K1/62 , F02K1/32 , F02K1/54 , F02K1/56 , F02K1/60 , F02K1/76 , F02K1/50 , F02K1/64 , F02K1/70
CPC分类号： F02K1/72 , F02K1/32 , F02K1/50 , F02K1/54 , F02K1/56 , F02K1/60 , F02K1/625 , F02K1/64 , F02K1/70 , F02K1/76 , F05D2220/323 , F05D2240/129
摘要： An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes and a wall. The vanes are arranged in a longitudinally extending array along the cascade inner face. The vanes include a first vane and a second vane. The wall is configured to block gas flow radially through the thrust reverser cascade between the first vane and the second vane.
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公开(公告)号：US10077740B2
公开(公告)日：2018-09-18
申请号：US14885284
申请日：2015-10-16
申请人： The Boeing Company
发明人： Ronald Tatsuji Kawai , John Bonet
摘要： Example folding door thrust reversers for aircraft engines are disclosed herein. An example apparatus includes a nacelle of a turbofan engine, where a fan duct is defined between the nacelle and a core of the turbofan engine. The example apparatus includes an opening in the nacelle between an outside of the nacelle and the fan duct and an inner door and an outer door disposed within the opening and pivotably coupled to the nacelle along aft edges thereof. The example inner and outer doors are pivotable between a first position in which the inner door and the outer door are disposed within the opening and oriented substantially parallel to each other, and a second position in which the inner door is disposed in the fan duct and oriented substantially perpendicular to an outer surface of the core and the outer door extends outward from the nacelle.
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公开(公告)号：US10077739B2
公开(公告)日：2018-09-18
申请号：US14261279
申请日：2014-04-24
申请人： ROHR, INC.
发明人： Norman J. James
摘要： 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.
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公开(公告)号：US20180258880A1
公开(公告)日：2018-09-13
申请号：US15980476
申请日：2018-05-15
申请人： The Boeing Company
发明人： David Alan Bakken
CPC分类号： F02K1/1207 , B64C15/02 , F02K1/06 , F02K1/30 , F02K1/70 , F02K1/72 , F02K1/78 , F02K1/805 , F16J15/00 , F16J15/02 , Y02T50/671
摘要： Methods and apparatus for sealing variable area fan nozzles of jet engines are disclosed. An apparatus in accordance with the teachings of this disclosure includes a frame and a seal to be coupled to the frame. The seal to enclose petals of a variable area fan nozzle to substantially prevent airflow between the petals.
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公开(公告)号：US20180230939A1
公开(公告)日：2018-08-16
申请号：US15889778
申请日：2018-02-06
发明人： Eric Haramburu , Patrick Oberle , Eric Masson
CPC分类号： F02K1/70 , B64D27/18 , B64D29/06 , F02K1/72 , F05D2220/323
摘要： A nacelle includes a fixed structure supporting a fixed cowl and a movable cowl, the movable cowl being movable translationally between a closing position and an opening position. A blocker door is movably mounted rotationally on the nacelle between a closed position and an open position. The nacelle includes a drive mechanism of the blocker door and of the movable cowl between the closed/closing position and the open/opening position of the blocker door/movable cowl, respectively, and vice versa, the drive mechanism includes at least one actuator fixed, to the fixed structure of the nacelle and, to a fitting fixed to the movable cowl. The drive mechanism includes, for each actuator, a flexible member having a first end fixed to the fixed structure of the nacelle and a second end fixed to the fitting.
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公开(公告)号：US20180216573A1
公开(公告)日：2018-08-02
申请号：US15423249
申请日：2017-02-02
申请人： Woodward, Inc.
CPC分类号： F02K1/763 , F02K1/12 , F02K1/58 , F02K1/62 , F02K1/70 , F02K1/72 , F05D2260/60 , F05D2270/331 , F05D2270/56 , F05D2270/64
摘要： The present subject matter can be embodied in, among other things, a two-speed thrust reverser actuation system for actuating a thrust reverser element experiencing an assisting load during movement between a stowed and deployed positions. The system includes a hydraulic actuator to move the thrust reverser element between the stowed and deployed positions, and a directional control valve with a regeneration feature including a restrictor and a velocity fuse arranged in parallel with the restrictor. The velocity fuse is configured to close when the assisting load on the thrust reverser element increases the flow rate of hydraulic fluid through the velocity fuse above threshold value. In operation, the system defines a first movement speed when the velocity fuse is open, and a second movement speed when the velocity fuse is closed, thereby decreasing an effective exit orifice size of the hydraulic actuator when the assisting load increases the deploy rate.
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公开(公告)号：US20180187630A1
公开(公告)日：2018-07-05
申请号：US15904671
申请日：2018-02-26
申请人： Safran Nacelles
发明人： Patrick GONIDEC , Hakim MAALIOUNE
CPC分类号： F02K1/763 , B64D27/16 , B64D29/06 , B64D33/04 , B64D2221/00 , F02K1/70 , F05D2220/323
摘要： The present disclosure relates to a nacelle for an aircraft turbofan engine and an aircraft that includes a nacelle that includes a supply device for supplying electric power to an electric actuator system allowing movement of a mobile member for deflecting a stream between a first position parallel or substantially parallel to the flow of the stream and a second position allowing the flow of the stream to be deflected so as to modify the path of the stream in one direction and/or the speed of the stream.
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公开(公告)号：US09970387B2
公开(公告)日：2018-05-15
申请号：US12672565
申请日：2008-08-07
申请人： Joel Hudson Frank , Norman John James , Shunshen Richard Wang , Bryant Lynoel McKleny , David A. Baer , Tony Jones , John H. Harvey , Peter W. Bacon , Mark Hubberstey , Brett J. Wharton , Neil C. Davies , Stephen Michael Roberts , Steven Andrew Wylie
发明人： Joel Hudson Frank , Norman John James , Shunshen Richard Wang , Bryant Lynoel McKleny , David A. Baer , Tony Jones , John H. Harvey , Peter W. Bacon , Mark Hubberstey , Brett J. Wharton , Neil C. Davies , Stephen Michael Roberts , Steven Andrew Wylie
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.
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