公开(公告)号：US20200263633A1

公开(公告)日：2020-08-20

申请号：US16790857

申请日：2020-02-14

Applicant: Safran Nacelles

Inventor： Pierre CARUEL ,  Alexandre DESCAMPS

IPC: F02K1/76 ,  E05B47/00 ,  F02K1/60

Abstract: An active locking system of a movable element for a thrust reverser of an aircraft nacelle includes an active locking device of the movable element, movable between a locking position and an unlocking position, an actuator of the locking device controlled by a command for actuating the locking device, a blocking device for blocking the locking device in the unlocked position, movable between a blocking position and an unblocking position, and a device for displacing the blocking device. The actuation command controls the closure of the movable element, and the device for displacing the blocking device displaces the blocking device in the unblocking position when the movable element is at a predetermined position.

公开(公告)号：US20220120238A1

公开(公告)日：2022-04-21

申请号：US17402041

申请日：2021-08-13

Applicant: Safran Nacelles

Inventor： Pierre CARUEL ,  Alexandre DESCAMPS

IPC: F02K1/60

Abstract: 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.

公开(公告)号：US20210003096A1

公开(公告)日：2021-01-07

申请号：US16884948

申请日：2020-05-27

Applicant: Safran Nacelles ,  Safran Aircraft Engines

Inventor： Sébastien Michel Thierry GUILLEMANT ,  Pierre CARUEL ,  Olivier KERBLER ,  Olivier HEAU ,  Mathieu LEROUVREUR ,  Antoine Elie HELLEGOUARCH

IPC: F02K1/72 ,  F01D9/06

Abstract: 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.

公开(公告)号：US20200325850A1

公开(公告)日：2020-10-15

申请号：US16907900

申请日：2020-06-22

Applicant: Safran Nacelles

Inventor： Patrick BOILEAU ,  Pierre CARUEL

IPC: F02K1/72 ,  B64D29/06 ,  B64D29/08 ,  B64D27/16

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.

公开(公告)号：US20210190005A1

公开(公告)日：2021-06-24

申请号：US17191106

申请日：2021-03-03

Applicant: Safran Nacelles

Inventor： Pierre CARUEL ,  Shwetanjana ANAND ,  Patrick BOILEAU

IPC: F02K1/72 ,  F02K1/76 ,  B64D29/08

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.

公开(公告)号：US20200149495A1

公开(公告)日：2020-05-14

申请号：US16730572

申请日：2019-12-30

Applicant: Safran Nacelles

Inventor： Pierre CARUEL

IPC: F02K1/72

Abstract: 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.

公开(公告)号：US20180290330A1

公开(公告)日：2018-10-11

申请号：US16008208

申请日：2018-06-14

Applicant: Safran Nacelles

Inventor： Pierre CARUEL ,  Hervé HURLIN

IPC: B28B1/00 ,  B28B1/30 ,  B28B1/52 ,  B28B11/00 ,  C04B38/00

CPC classification number: B28B1/002 ,  B28B1/30 ,  B28B1/522 ,  B28B11/005 ,  B32B3/12 ,  B32B5/02 ,  B32B5/26 ,  B32B7/04 ,  B32B18/00 ,  B32B37/146 ,  B32B2250/03 ,  B32B2250/20 ,  B32B2250/40 ,  B32B2260/021 ,  B32B2260/04 ,  B32B2262/105 ,  B32B2305/024 ,  B32B2307/102 ,  B32B2307/306 ,  B32B2307/54 ,  B32B2307/714 ,  B32B2307/718 ,  B32B2315/02 ,  B32B2605/18 ,  B64C7/02 ,  B64D29/00 ,  C04B35/62849 ,  C04B35/62852 ,  C04B35/803 ,  C04B38/0006 ,  C04B38/0083 ,  C04B2111/00612 ,  C04B2111/00982 ,  C04B2235/616 ,  C04B2237/38 ,  F02K1/82 ,  F02K1/822 ,  F02K1/827 ,  F05D2300/603 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/675 ,  Y10T156/108

Abstract: 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.

公开(公告)号：US20220082064A1

公开(公告)日：2022-03-17

申请号：US17536480

申请日：2021-11-29

Applicant: Safran Nacelles ,  SAFRAN AIRCRAFT ENGINES

Inventor： Patrick BOILEAU ,  Pierre CARUEL ,  Gina FERRIER ,  Quentin GARNAUD ,  Guillaume GLEMAREC

IPC: F02K1/68 ,  F02K1/70

Abstract: An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.

公开(公告)号：US20200347801A1

公开(公告)日：2020-11-05

申请号：US16933179

申请日：2020-07-20

Applicant: Safran Nacelles

Inventor： Pierre CARUEL ,  Loïc GRALL ,  Alexis HEAU ,  Olivier KERBLER ,  Mélody SERISET

IPC: F02K1/72 ,  F02K1/76

Abstract: 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.

公开(公告)号：US20200277916A1

公开(公告)日：2020-09-03

申请号：US16876704

申请日：2020-05-18

Applicant: Safran Nacelles

Inventor： Pierre CARUEL ,  Vincent PEYRON

IPC: F02K1/70 ,  F02K1/76 ,  B64D29/06

Abstract: An aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser includes cascades of mobile deflection vanes connected to cascade rails with a slideway connection that allows the cascades of vanes a translational movement between a cruising-flight position and a reverse-thrust position. The thrust reverser allows the cascade rails to be positioned in a forward position, in which the engine, the cascade rails and the deflection vanes can be removed from the propulsion assembly without the cascade rails colliding with the mobile cowl of the reverser. Dismantling and assembly or reassembly methods allow maintenance operations to be carried out on the engine thus dismantled.