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    THRUST REVERSER COMPRISING FIXED CASCADES AND A SEALING MEMBRANE
    1.
    发明申请
    THRUST REVERSER COMPRISING FIXED CASCADES AND A SEALING MEMBRANE 有权

    公开(公告)号：US20250101931A1

    公开(公告)日：2025-03-27

    申请号：US18726915

    申请日：2023-01-06

    Applicant: SAFRAN NACELLES

    Inventor： Patrick GONIDEC ,  Loïc CHAPELAIN (Deceased) ,  Patrick André BOILEAU

    IPC: F02K1/72

    Abstract: A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.

    DOOR FOR THRUST REVERSER OF AN AIRCRAFT PROPULSION ASSEMBLY, COMPRISING A FLEXIBLE BAFFLE
    3.
    发明申请
    DOOR FOR THRUST REVERSER OF AN AIRCRAFT PROPULSION ASSEMBLY, COMPRISING A FLEXIBLE BAFFLE 有权

    公开(公告)号：US20220316426A1

    公开(公告)日：2022-10-06

    申请号：US17610580

    申请日：2020-05-05

    Applicant: SAFRAN NACELLES

    Inventor： Patrick GONIDEC ,  Gerard CLERE ,  Alexandre PHI

    IPC: F02K1/70

    Abstract: A door for a thrust reverser of a propulsion assembly, the door being provided with a flexible baffle. The baffle is configured to change state by moving from a folded position to an unfolded position, and vice versa, depending on the configuration of the reverser. When the reverser is in reverse jet configuration, the door is open and the baffle is in an unfolded position in order to direct a flow of gas upstream of the propulsion assembly, thus generating a counter-thrust. When the reverser is in direct jet configuration, the door is closed and the baffle is in a folded position so as to cancel or minimise interference caused by the baffle in the flow of gas passing through the propulsion assembly and thus generating a thrust.

    APPARATUS FOR PROVIDING AN ELECTRICAL CONNECTION
    4.
    发明申请
    APPARATUS FOR PROVIDING AN ELECTRICAL CONNECTION 有权

    公开(公告)号：US20210317798A1

    公开(公告)日：2021-10-14

    申请号：US17271910

    申请日：2019-08-15

    Applicant: Safran Nacelles Limited

    Inventor： James MARQUIS ,  Patrick GONIDEC ,  Stuart HARDYMAN ,  Loic CHAPELAIN

    IPC: F02K1/76 ,  B64D29/08 ,  B64F5/60 ,  H02G11/00 ,  H01R35/04

    Abstract: A structure comprising a nacelle or a thrust reverser, the structure comprising a stationary part and a movable part, the structure comprising: a first guide provided on or in the stationary part of the structure or the movable part of the structure; a first electrical connector attached to the stationary part of the structure; a second electrical connector attached to the movable part of the structure; and a carriage movable along the first guide; wherein the carriage comprises a closed loop electrical cable mounted in or on a carriage body such that the closed loop cable can rotate, wherein the first electrical connector is electrically connected to the closed loop electrical cable and the closed loop electrical cable is electrically connected to the second electrical connector, thereby providing an electrical connection from the stationary part of the structure to the movable part of the structure.

    SYSTEM FOR ACTUATING A PANEL OF A TURBOJET ENGINE NACELLE
    5.
    发明申请
    SYSTEM FOR ACTUATING A PANEL OF A TURBOJET ENGINE NACELLE 审中-公开

    公开(公告)号：US20190170088A1

    公开(公告)日：2019-06-06

    申请号：US16257765

    申请日：2019-01-25

    Applicant: Safran Nacelles

    Inventor： Patrick GONIDEC ,  Loïc CHAPELAIN ,  Faycel BOUABDALLAH

    IPC: F02K1/76 ,  F02K1/70 ,  F02K1/12 ,  B64D29/06

    Abstract: A pod for a turbojet engine includes an outer cowl having a structure with at least one opening and a panel pivotably mounted about an axis between a closed position and an open position, and a system for actuating the panel designed to lock the panel in closed position and to move same between the closed position and the open position thereof. The actuation system includes a lateral connecting rod connected to the panel and to the structure, pivoting relative to the structure about a first pivoting axis and about a second pivoting axis, and a linear actuator attached to the lateral connecting rod. The actuator system is designed to move the lateral connecting rod during the extension of the actuator, and the lateral connecting rod exerts a force on the panel during the movement thereof, pivoting the panel about the axis thereof.

    "> INTEGRATING AN EXTINGUISHER INTO A
    8.
    发明申请
    INTEGRATING AN EXTINGUISHER INTO A "FIRE" ZONE OF A TURBOMACHINE 有权

    公开(公告)号：US20250052200A1

    公开(公告)日：2025-02-13

    申请号：US18722944

    申请日：2022-12-21

    Applicant: Safran Nacelles

    Inventor： Patrick GONIDEC ,  Patrick André BOILEAU

    IPC: F02C7/25 ,  A62C3/08 ,  B64D29/00

    Abstract: An assembly for an aircraft gas turbine engine includes a nacelle extending substantially around a longitudinal axis and including a fixed structure disposed around the aircraft gas turbine engine, the fixed structure including an internal surface suitable for delimiting with an external surface of the gas turbine engine a fire zone of the nacelle, a thermal protection covering the internal surface of the fixed structure of the nacelle at the level of the fire zone of the nacelle, and an extinguisher designed to extinguish a fire in the fire zone of the nacelle, the extinguisher including a tank suitable for containing an extinguishing agent. The tank is located between the thermal protection and the internal surface of the fixed structure of the nacelle.

    DEVICE AND METHOD FOR DATA COMMUNICATION IN AN AIRCRAFT SUBASSEMBLY
    9.
    发明申请
    DEVICE AND METHOD FOR DATA COMMUNICATION IN AN AIRCRAFT SUBASSEMBLY 有权

    公开(公告)号：US20210285382A1

    公开(公告)日：2021-09-16

    申请号：US17126257

    申请日：2020-12-18

    Applicant: Safran Nacelles

    Inventor： Patrick GONIDEC ,  Jean-Paul RAMI

    IPC: F02C9/16 ,  H04B10/116 ,  B64D31/02 ,  B64D47/02

    Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

    TURBINE ENGINE NACELLE COMPRISING A COOLING DEVICE
    10.
    发明申请
    TURBINE ENGINE NACELLE COMPRISING A COOLING DEVICE 审中-公开

    公开(公告)号：US20190153947A1

    公开(公告)日：2019-05-23

    申请号：US16253352

    申请日：2019-01-22

    Applicant: Safran Nacelles

    Inventor： Vincent PEYRON ,  Patrick GONIDEC ,  Nicolas BOUCHOUT

    IPC: F02C7/14 ,  F02C7/16 ,  F02K3/115 ,  B64D29/06 ,  B64D33/08

    Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.

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