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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
申请人： Safran Nacelles
摘要： 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：US11840352B2
公开(公告)日：2023-12-12
申请号：US17510643
申请日：2021-10-26
申请人： Safran Nacelles
发明人： Gina Ferrier , Patrick Boileau , Pierre Caruel
CPC分类号： B64D33/02 , B64D29/06 , F02C7/04 , B64D2033/0206 , B64D2033/0273 , B64D2033/0286 , F05D2230/60
摘要： An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.
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公开(公告)号：US10239227B2
公开(公告)日：2019-03-26
申请号：US16008208
申请日：2018-06-14
申请人： Safran Nacelles
发明人： Pierre Caruel , Hervé Hurlin
IPC分类号： B32B3/12 , B64C7/02 , B32B37/14 , C04B35/80 , B28B1/00 , B28B11/00 , B32B18/00 , C04B38/00 , C04B35/628 , F02K1/82 , B28B1/30 , B28B1/52 , C04B111/00 , B64D29/00
摘要： The present disclosure provides a method of manufacturing a composite sandwich panel having a core formed of a plurality of cells extending vertically between a first skin and a second skin. The method includes creating at least one first strip and a second strip from a temporary material, each strip having at least one cavity having a succession of aligned half-cells, lining the cavity of the first strip with a fibrous ply, assembling the first strip and the second strip by interlocking the cavity of the first strip with the cavity of the second strip and trapping the fibrous ply therebetween, and trimming excess temporary material of the entirety of the strips formed during the preceding assembly step so as to form a new cavity which forms a succession of aligned half-cells.
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公开(公告)号：US11965474B2
公开(公告)日：2024-04-23
申请号：US17402961
申请日：2021-08-16
申请人： Safran Nacelles
IPC分类号： F02K1/76
摘要： A control system includes an actuator, a locking/unlock device, a central control valve, first and second control valves, and a spool control valve. The actuator is arranged so as to move a door of a thrust reverser between direct jet and reverse jet positions. The locking/unlocking device unlockable under load allowing locking and/or unlocking of the door. The locking/unlocking device is movable between a closure position in which it holds the door in the direct jet position and an opening position in which the door is released. The first and second control valves each fed by the central control valve. The spool control valve fed at least by the first and second control valves. The spool control valve is configured so that a pressure difference between two inlets of the first and second control valves provides a displacement of the spool control valve between first and second stable positions.
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公开(公告)号：US11767808B2
公开(公告)日：2023-09-26
申请号：US16933179
申请日：2020-07-20
申请人： Safran Nacelles
发明人： Pierre Caruel , Loïc Grall , Alexis Heau , Olivier Kerbler , Mélody Seriset
CPC分类号： F02K1/72 , F02K1/763 , B64D29/06 , F02K3/06 , F05D2220/323 , F05D2240/129
摘要： A nacelle rear assembly of a nacelle of a turbojet engine of an aircraft extends along a longitudinal central axis (A) and includes a sliding cascade thrust reverser. The cascade thrust reverser includes at least one sliding cowl, a deflection cascade including a plurality of rows of vanes that each extend around the longitudinal central axis (A) and that are longitudinally arranged from a first front row of vanes up to a last rear row of vanes, each row of vanes including at least one deflection vane for deflecting the airflow toward the outside of the rear assembly of the nacelle, the deflection cascade being movably integral with the sliding cowl, wherein the deflection cascade includes at least one additional neutral row of vanes that is interposed between the last row of vanes and the sliding cowl and that includes at least one neutral vane.
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公开(公告)号：US11549462B2
公开(公告)日：2023-01-10
申请号：US16884948
申请日：2020-05-27
发明人： Sébastien Michel Thierry Guillemant , Pierre Caruel , Olivier Kerbler , Alexis Heau , Mathieu Lerouvreur , Antoine Elie Hellegouarch
摘要： A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.
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公开(公告)号：US11136939B2
公开(公告)日：2021-10-05
申请号：US16730572
申请日：2019-12-30
申请人： Safran Nacelles
发明人： Pierre Caruel
IPC分类号： F02K1/72
摘要： A nacelle for a turbojet includes a thrust reverser having cascades, movable cowls adjacent to the cascades in a closed position, linkage systems for connecting the cowls and the cascades, and tilting closure flaps. Each linkage system is arranged radially outside the cascades, and includes, in a tangential plane, a lever, connecting rods, and pivots allowing a movement substantially in this plane. The pivots include a fixed pivot connected to a fixed element of the nacelle, a pivot connected to the cascades and a pivot connected to the cowls. The lever, termed first lever, includes two arms forming a “V,” and two connecting rods are fixed to the end of an arm by a pivot.
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公开(公告)号：US11767807B2
公开(公告)日：2023-09-26
申请号：US17402041
申请日：2021-08-13
申请人： Safran Nacelles
发明人： Pierre Caruel , Alexandre Descamps
摘要： A closing system that includes a closing actuator for doors of a thrust reverser, two sliding members, and a detection device. The closing actuator includes two first connecting rods. Each first connecting rod is configured to be connected to a first lateral edge of each door. The closing actuator is arranged to move each door at least towards the direct jet position. Each sliding member carries a second connecting rod configured to be connected to a second lateral edge of each door. The second connecting rods are arranged to be driven by the doors when the closing actuator moves the doors towards the direct jet position so as to displace the two sliding members. The detection device detects a defect of one of the first and second connecting rods. The detection device is configured to detect the relative position of the two sliding members in the direct jet position.
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公开(公告)号：US11454194B2
公开(公告)日：2022-09-27
申请号：US16907900
申请日：2020-06-22
申请人： Safran Nacelles
发明人： Patrick Boileau , Pierre Caruel
摘要： 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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公开(公告)号：US11286880B2
公开(公告)日：2022-03-29
申请号：US16394128
申请日：2019-04-25
申请人： Safran Nacelles
发明人： Pierre Caruel , Regis Giard , Denis Guillois , Philippe Vancon
摘要： A thrust reverser includes two thrust reverser elements movable between a retracted position in which the thrust reverser is inactive and a deployed position in which the thrust reverser is active, a cylinder for deploying the thrust reverser elements, and a single-acting cylinder for retracting the thrust reverser elements.
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