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    AIR INTAKE LIP OF A TURBOMACHINE NACELLE COMPRISING AN ACOUSTIC DEVICE AND METHOD FOR PRODUCING SUCH A LIP
    4.
    发明申请
    AIR INTAKE LIP OF A TURBOMACHINE NACELLE COMPRISING AN ACOUSTIC DEVICE AND METHOD FOR PRODUCING SUCH A LIP 有权

    公开(公告)号：US20220212809A1

    公开(公告)日：2022-07-07

    申请号：US17614148

    申请日：2020-05-14

    Applicant: SAFRAN NACELLES

    Inventor： Virginie Emmanuelle Anne-Marie Digeos ,  Patrick Gonidec

    IPC: B64D33/02 ,  F02C7/045 ,  F02C7/047 ,  B64D29/00

    Abstract: The invention relates to an air intake lip of an aircraft turbomachine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the inner wall and the outer wall being connected by an upstream wall so as to delimit an annular cavity, the lip comprising an annular acoustic device mounted in the annular cavity. The lip has a first module, comprising the outer wall, the wall and a front wall forming an upstream portion of the inner wall, and a second module, comprising the acoustic device and a front skin forming a downstream portion of the inner wall, the first module and the second module being secured together so that the front wall and the front skin together form the inner wall of the lip.

    AIR INTAKE LIP OF AN AIRCRAFT ENGINE NACELLE, COMPRISING AT LEAST ONE INFRARED EMISSION SOURCE
    7.
    发明申请
    AIR INTAKE LIP OF AN AIRCRAFT ENGINE NACELLE, COMPRISING AT LEAST ONE INFRARED EMISSION SOURCE 有权

    公开(公告)号：US20220219831A1

    公开(公告)日：2022-07-14

    申请号：US17614146

    申请日：2020-05-14

    Applicant: SAFRAN NACELLES

    Inventor： Patrick Gonidec ,  Jean-Paul Rami

    IPC: B64D33/02 ,  B64D29/00 ,  F02C7/047 ,  B64C7/02 ,  B64D15/12

    Abstract: The invention relates to an air intake lip of an aircraft engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the inner wall and the outer wall being connected by an upstream wall and a partition so as to delimit an annular cavity, in which at least one infrared emission source is housed, wherein at least one wall, selected among the inner wall, the outer wall and the upstream wall, is made of a material configured to transmit on an outer face at least 30% of the infrared received on an inner face.

    System for actuating a panel of a turbojet engine nacelle
    8.
    发明授权
    System for actuating a panel of a turbojet engine nacelle 有权

    公开(公告)号：US10774786B2

    公开(公告)日：2020-09-15

    申请号：US16257765

    申请日：2019-01-25

    Applicant: Safran Nacelles

    Inventor： Patrick Gonidec ,  Loïc Chapelain ,  Faycel Bouabdallah

    IPC: F02K1/76 ,  F02K1/11 ,  F02K1/12 ,  F02K1/06 ,  B64D29/06 ,  F02K1/70

    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.

    Door for thrust reverser of an aircraft propulsion assembly, comprising a flexible baffle
    9.
    发明授权
    Door for thrust reverser of an aircraft propulsion assembly, comprising a flexible baffle 有权

    公开(公告)号：US12060850B2

    公开(公告)日：2024-08-13

    申请号：US17610580

    申请日：2020-05-05

    Applicant: SAFRAN NACELLES

    Inventor： Patrick Gonidec ,  Gerard Clere ,  Alexandre Phi

    IPC: F02K1/70

    CPC classification number: F02K1/70 ,  F05D2300/601

    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.

    Aircraft turbojet engine nacelle
    10.
    发明授权
    Aircraft turbojet engine nacelle 有权

    公开(公告)号：US10590886B2

    公开(公告)日：2020-03-17

    申请号：US15655276

    申请日：2017-07-20

    Applicant: SAFRAN NACELLES

    Inventor： Olivier Kerbler ,  Fabrice Henri Emile Metezeau ,  Patrick Gonidec ,  Loïc Grall

    IPC: F02K1/72 ,  B64D33/04 ,  B64D29/06 ,  B64D27/16

    Abstract: The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.

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