公开(公告)号：US20200369394A1

公开(公告)日：2020-11-26

申请号：US16878034

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Rémi LANSIAUX ,  Olivier DUBOIS ,  Anthony MERTES ,  Jacky PUECH

IPC: B64D27/26

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.

公开(公告)号：US20200346771A1

公开(公告)日：2020-11-05

申请号：US16807351

申请日：2020-03-03

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Rémi LANSIAUX ,  Olivier DUBOIS ,  Anthony MERTES ,  David ALRIC ,  Stéphane NOGUES

IPC: B64D27/26

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

公开(公告)号：US20190241272A1

公开(公告)日：2019-08-08

申请号：US16253040

申请日：2019-01-21

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE

IPC: B64D27/26 ,  F16M1/04 ,  F16B21/20

Abstract: An assembly for an aircraft engine mounting comprising an articulation axis supported by two plain bearings and a blocking device blocking the translation of the articulation axis in a direction which comprises a blocking screw that is screwed, in operation, into a first, tapped internal portion of a tubular extension secured to one of the two plain bearings, a first blocking system comprising an internal elastic stop ring housed in a groove formed in the tubular extension, and a second blocking system comprising a blocking screw which passes through first orifices passing through the second section of the blocking screw and second orifices passing through the tubular extension.

公开(公告)号：US20190161198A1

公开(公告)日：2019-05-30

申请号：US16195971

申请日：2018-11-20

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE ,  Benoit ORTEU

IPC: B64D27/26

Abstract: A swivel axis for an aircraft engine attachment, comprising a tubular main axis which has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a first nut. A fail-safe axis is configured to be mounted to swivel inside the main axis. The fail-safe axis has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a second nut. The fail-safe axis is linked by an axial link to the first nut. Since the fail-safe axis is linked to the first nut, it is necessarily inserted into the main axis when the first nut is screwed onto the main axis.

公开(公告)号：US20190152615A1

公开(公告)日：2019-05-23

申请号：US16192950

申请日：2018-11-16

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE ,  Benoit ORTEU

IPC: B64D27/26

Abstract: A rear engine attachment for an engine of an aircraft which comprises a pylon having a bottom face, the rear engine attachment comprising a first fitting configured to be fixed against the bottom face and having a wall, a second fitting configured to be secured to a structural casing of the engine, two front links and two rear links, which are fixed by one and the same main link point to the wall and by two link points on either side of the second fitting. Such a motorization assembly allows for a reduction of the bulk, in particular at the rear engine attachment, which helps in improving the overall performance of the motorization assembly.

公开(公告)号：US20240417088A1

公开(公告)日：2024-12-19

申请号：US18740971

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Mathieu MAHE ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  A62C3/08 ,  A62C35/68

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine, an attachment pylon having a rigid structure, and an extinguishing system. The extinguishing system is located in a front position relative to the rigid structure, the extinguishing system being positioned between the rigid structure and the jet engine.

公开(公告)号：US20240417087A1

公开(公告)日：2024-12-19

申请号：US18740961

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

公开(公告)号：US20240400216A1

公开(公告)日：2024-12-05

申请号：US18673984

申请日：2024-05-24

Applicant: Airbus Operations SAS

Inventor： Eric RENAUD ,  Thomas DEFORET ,  Mathieu KALETA ,  Antoine CLAVEYROLLAS ,  Mathieu MAHE ,  Ginesa TORRES LOPEZ

IPC: B64D29/06 ,  F01D25/24

Abstract: A propulsion assembly comprising a fan casing and a nacelle which comprises an air inlet which is connected to the front end of the fan casing, an intermediate portion which is positioned around the fan casing and a rear portion which cooperates with the rear end of the fan casing. The intermediate portion comprises at least one aerodynamic panel which extends from a front edge which is attached to the air inlet as far as a rear edge which is attached to the rear portion and at least one intermediate radial support comprising an internal edge which is connected to the fan casing and an external edge which is connected to the aerodynamic panel, this panel comprising a front edge which is connected to the air inlet by a first connection system. Also an aircraft with such a propulsion assembly.

公开(公告)号：US20200369396A1

公开(公告)日：2020-11-26

申请号：US16879121

申请日：2020-05-20

Applicant: Airbus Operations SAS

Inventor： Christophe LABARTHE ,  Michael BERJOT ,  Thomas DEFORET

IPC: B64D27/26

Abstract: A rear engine attachment system for an aircraft engine. The attachment system has an engine pylon with a lower spar having a lower surface, and a rear engine attachment having a beam fixed against the lower surface and to which a pair of rods is fixed. Each rod is fixed to the beam by at least one first connection point and to the engine by at least one second connection point. The beam includes front and rear fittings, and an intermediate fitting with a shoe and an intermediate clevis. The shoe presses against the lower surface. The front fitting presses against the intermediate fitting at the front and the rear fitting presses against the intermediate fitting at the rear. The fixing to the lower spar is ensured by bolts, each passing through the front base or the rear base, the shoe and the lower spar.

公开(公告)号：US20200369393A1

公开(公告)日：2020-11-26

申请号：US16878011

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Rémi LANSIAUX ,  Olivier DUBOIS ,  Jacky PUECH

IPC: B64D27/26

Abstract: A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.