公开(公告)号：US20200207481A1

公开(公告)日：2020-07-02

申请号：US16615924

申请日：2017-12-12

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Adeline SOULIE ,  Olivier PAUTIS

IPC: B64D27/26

Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.

公开(公告)号：US20190003421A1

公开(公告)日：2019-01-03

申请号：US16017634

申请日：2018-06-25

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Laurent TIZAC ,  Frédéric RIDRAY ,  Lionel CZAPLA ,  Frédéric PIARD

IPC: F02K1/72 ,  F02K3/06

Abstract: A turbofan comprising a fan casing and a nacelle comprising a cowl translatable between an advanced position and a pushed-back position in which the mobile cowl and the fan casing define a window therebetween. The nacelle also comprises reverser flaps, each reverser flap being mounted in a linked manner on the mobile assembly between a closed position in which it obstructs the window and an open position in which it does not obstruct the window. The nacelle also has an impelling mechanism comprising a lever arm rotatable on the mobile assembly and having a roller, a connecting rod mounted rotatably between the reverser flap and the lever arm, and a channel receiving the roller, the channel having a front part parallel with the translation direction and a rear part extending after the front part and oriented inward as it progresses from the front toward the rear.

公开(公告)号：US20250010997A1

公开(公告)日：2025-01-09

申请号：US18761912

申请日：2024-07-02

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT ,  Jean-Baptiste VIGNES

IPC: B64D27/40

Abstract: An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.

公开(公告)号：US20240327008A1

公开(公告)日：2024-10-03

申请号：US18618130

申请日：2024-03-27

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Laurent AGOSTINI ,  Jérôme COLMAGRO

IPC: B64D27/40 ,  B64D27/18

CPC classification number: B64D27/402 ,  B64D27/18

Abstract: The invention relates to a propulsion assembly having a jet engine with an intermediate casing with a rear face and a core casing to the rear of the intermediate casing, and an attachment pylon with a frontal wall and two lateral walls, a front engine attachment having a front fitting fastened in an articulated manner via two lateral fastening points to the rear face and in a rigid manner via an upper fastening zone to the frontal wall, and an intermediate engine attachment comprising a front link rod and a rear link rod on each side. Each of the link rods is mounted in an articulated manner between the front fitting and the lateral wall. With such an arrangement, the bulk of the engine attachments is reduced in the bypass flow.

公开(公告)号：US20230202665A1

公开(公告)日：2023-06-29

申请号：US18073049

申请日：2022-12-01

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA ,  Olivier PAUTIS

IPC: B64D29/06 ,  B64D27/26

CPC classification number: B64D29/06 ,  B64D27/26 ,  B64D2027/262

Abstract: An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

公开(公告)号：US20220411085A1

公开(公告)日：2022-12-29

申请号：US17621467

申请日：2020-06-09

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT

IPC: B64D27/26 ,  B64C3/18

Abstract: An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

公开(公告)号：US20220017229A1

公开(公告)日：2022-01-20

申请号：US17375393

申请日：2021-07-14

Applicant: Airbus Operations SAS

Inventor： Germain GUENEAU ,  Michael BERJOT ,  Olivier PAUTIS

IPC: B64D27/26 ,  B64C3/18 ,  B64D27/16 ,  B64C3/32

Abstract: An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

公开(公告)号：US20190202572A1

公开(公告)日：2019-07-04

申请号：US16228966

申请日：2018-12-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Jérôme COLMAGRO

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D27/18

Abstract: An aircraft comprises a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. This arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure, at least one securing member articulated to each of the first and second connecting portions. Furthermore, the first connecting portions of the two fittings are made in one piece in a single wing connector extending over essentially the entire height of the front wing spar.

公开(公告)号：US20250051020A1

公开(公告)日：2025-02-13

申请号：US18796631

申请日：2024-08-07

Applicant: Airbus Operations SAS

Inventor： Frédéric JOURNADE ,  Olivier PAUTIS ,  Jérôme COLMAGRO ,  Germain GUENEAU ,  Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Fabrice GRIMAL

IPC: B64D27/40

Abstract: A propulsion system comprising a turbojet with a fan casing and a central casing, a pylon with an upper spar, a front wall and on either side of a vertical median plane, a fitting rigidly fixed to the rigid structure, a cylindrical pin as one with the fan casing and inserted in a hole of the upper spar, a shackle with at the vertical median plane, an upper articulation between the shackle and the front wall and on either side of the vertical median plane, a lower articulation between the shackle and the central casing, and two reaction rods disposed on either side of the median plane, where each rod is articulated, at a front end, on the central casing, and, at rear end, on the fitting.

公开(公告)号：US20250010998A1

公开(公告)日：2025-01-09

申请号：US18761974

申请日：2024-07-02

Applicant: Airbus Operations SAS

Inventor： Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Germain GUENEAU ,  Olivier PAUTIS

IPC: B64D27/40 ,  B64D27/18

Abstract: An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.