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公开(公告)号：US12168964B2
公开(公告)日：2024-12-17
申请号：US18560510
申请日：2022-05-13
Applicant: SAFRAN NACELLES
Inventor： Patrick Boileau , Julien Chandelier , Fabien Jourdan , Philippe Wiertel
Abstract: A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.
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公开(公告)号：US11619191B2
公开(公告)日：2023-04-04
申请号：US17025019
申请日：2020-09-18
Applicant: Safran Nacelles , Safran Aircraft Engines
Inventor： Quentin Garnaud , Guillaume Glemarec , Patrick Boileau , Ludovic Toupet
Abstract: A turbofan propulsion assembly includes a thrust reverser with movable flaps. The propulsion assembly further includes an engine and a nacelle surrounding the engine, and the nacelle includes a thrust reverser with sliding cowls and thrust reverser flaps, and an inner structure. The portion of the inner structure positioned perpendicular to the thrust reverser flaps includes two halves that can open toward the exterior of the nacelle cowls.
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公开(公告)号：US11486333B2
公开(公告)日：2022-11-01
申请号：US17191106
申请日：2021-03-03
Applicant: Safran Nacelles
Inventor： Pierre Caruel , Shwetanjana Anand , Patrick Boileau
Abstract: A thrust reverser for an aircraft propulsion assembly includes a movable structure provided with external covers connected to hinges through a pivot connection allowing the external covers to rotate between a closed position and a maintenance position. The hinges are connected to secondary rails rigidly attached to an engine pylon through a sliding connection allowing the external covers to move in translation between a direct thrust position and a reverse thrust position. The hinges and the secondary rails are independent of beams to which the parts of the movable structure other than the external covers are connected. A method for maintaining an aircraft propulsion unit is also disclosed. The method includes positioning of the external covers in maintenance position followed by a placement of the beams and of the parts of the movable structure other than the external covers.
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公开(公告)号：US11428190B2
公开(公告)日：2022-08-30
申请号：US16914782
申请日：2020-06-29
Applicant: Safran Nacelles
Inventor： Loïc Grall , Alexis Heau , Benjamin Brebion , Sébastien Michel Thierry Guillemant , Mélody Seriset , Patrick Boileau
Abstract: A grid-type thrust reverser for a turbojet engine includes a moving O-shaped thrust reverser body that is generally cylindrical in shape around a longitudinal central axis (A) and includes an inner wall configured to delimit a cold air stream, with an inner structure that surrounds the turbojet engine, the movable thrust reverser body being mounted so as to be able to slide along the longitudinal central axis (A) between a direct jet position in which the outer cowl covers the thrust reverser grids, and a thrust-reversal position in which the outer cowl uncovers the thrust reverser grids. The movable thrust reverser body includes a first half-portion and a second half-portion that are mounted so as to each pivot about a longitudinal pivot axis (B), between a closed position and an open gullwing position for removing the turbojet engine, via the cradle.
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公开(公告)号：US09856826B2
公开(公告)日：2018-01-02
申请号：US15654087
申请日：2017-07-19
Applicant: SAFRAN NACELLES
Inventor： Patrick Boileau
CPC classification number: F02K1/72 , B64D27/10 , B64D27/16 , B64D29/06 , F02C7/20 , F02K1/763 , F05D2220/323 , F05D2260/50
Abstract: The present disclosure provides a rear nacelle assembly for a turbojet having at least one thrust reversal device to redirect air circulating from upstream to downstream in a flow path of a turbojet and a mast that connects the nacelle to a structure of an aircraft. In one form, the thrust reverser device includes a cradle having a first longeron and a second longeron extending longitudinally opposite sides of the mast. The first and second longeron each include a device for slideably guiding the cowl and the cascade. In another form, a rear portion and a front portion of the cradle connects to the mast by a rear connecting device and front connecting device, respectively, such that the cradle is adapted to follow the movements of the turbojet.
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Patent Agency Ranking
16.发明授权公开(公告)号：US12269604B2
公开(公告)日：2025-04-08
申请号：US16991636
申请日：2020-08-12
Applicant: Safran Nacelles
Inventor： Virginie Emmanuelle Anne Marie Digeos , Patrick Boileau
Abstract: A defrosting and acoustic treatment device for an air intake lip of a turbojet engine nacelle includes an embossed acoustic structure that delimits a plurality of acoustic cells, each acoustic cell being delimited by an independent peripheral wall that allows a flow of de-icing air to flow around each acoustic cell.
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公开(公告)号：US12208994B2
公开(公告)日：2025-01-28
申请号：US17188520
申请日：2021-03-01
Applicant: Safran Nacelles
Inventor： Patrick Boileau
Abstract: A handling assembly of a propulsion assembly includes a nacelle and an aircraft turbojet engine. The handling assembly also includes a handling envelope covering at least half of the circumference of an outer wall of an air inlet of the nacelle, when the propulsion assembly is mounted on said handling assembly, and at least two interfaces for attaching slings, the slings being connected to a hoisting system which is external to said handling assembly. A method for handling a propulsion assembly is also disclosed.
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公开(公告)号：US12092026B2
公开(公告)日：2024-09-17
申请号：US17510803
申请日：2021-10-26
Applicant: Safran Nacelles
IPC: F02C7/045
CPC classification number: F02C7/045 , F05D2220/323 , F05D2230/60
Abstract: An air intake for a nacelle for an aircraft engine includes a front lip connecting a substantially cylindrical internal wall and a substantially cylindrical external wall, and at least one acoustic structure including acoustic cells. The acoustic structure is situated in the space delimited by the internal wall, the external wall and the front lip. The acoustic structure is an added part secured to the air intake. The acoustic cells of the acoustic structure are arranged facing a region of the internal wall or of the lip at a predetermined distance so that the acoustic cells of the acoustic structure are not in contact with the internal wall or the lip while providing an acoustic attenuation function.
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公开(公告)号：US11542865B2
公开(公告)日：2023-01-03
申请号：US16901733
申请日：2020-06-15
Applicant: Safran Nacelles
Inventor： Patrick Boileau , Caroline Coat-Lenzotti , Marc Versaevel , Virginie Emmanuelle Anne Marie Digeos , Pierre-François Behaghel
Abstract: An air inflow lip of a nacelle for a turbojet of an aircraft, including a cavity defined by a leading edge of the nacelle and by an annular wall, includes an inner wall, an acoustic treatment device, and a pneumatic de-icing device including a de-icing fluid supply device. The inner wall of the air inflow lip includes acoustic boreholes and the pneumatic de-icing device includes a honeycombed de-icing plate mounted inside the cavity on the inner wall of the air inflow lip. Also included are conduits for the circulation of a de-icing fluid and acoustic wells communicating with the acoustic boreholes.
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20.发明授权公开(公告)号：US11454194B2
公开(公告)日：2022-09-27
申请号：US16907900
申请日：2020-06-22
Applicant: Safran Nacelles
Inventor： Patrick Boileau , Pierre Caruel
Abstract: A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.
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