-
公开(公告)号：US11572184B2
公开(公告)日：2023-02-07
申请号：US16878006
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 having an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and a front engine attachment having a beam that is fixed against the front face and to which is fixed, on either side of a median plane, a rod system, wherein each rod system is fixed to the beam in an articulated manner by at least one first connection point, and is configured to be fixed to a front part of the engine in an articulated manner by at least one second connection point. Such a front engine attachment system thus has rod systems having two rods, allowing the shape of the rods and the shape of the beam to be simplified.
-
公开(公告)号：US11518531B2
公开(公告)日：2022-12-06
申请号：US16733783
申请日：2020-01-03
Applicant: Airbus Operations SAS
Inventor： Jacky Puech , Thomas Deforet , Julien Cayssials
Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.
-
公开(公告)号：US10577114B2
公开(公告)日：2020-03-03
申请号：US16253040
申请日：2019-01-21
Applicant: Airbus Operations SAS
Inventor： Jean Geliot , Thomas Deforet , Adeline Soulie
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：US11535389B2
公开(公告)日：2022-12-27
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.
-
公开(公告)号：US11434015B2
公开(公告)日：2022-09-06
申请号：US16733691
申请日：2020-01-03
Applicant: Airbus Operations SAS
Inventor： Jacky Puech , Thomas Deforet , Julien Cayssials
Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove in such a manner as to immobilize the shear pin in translation.
-
Patent Agency Ranking
公开(公告)号：US11319081B2
公开(公告)日：2022-05-03
申请号：US16437260
申请日：2019-06-11
Applicant: Airbus Operations SAS
Inventor： Thomas Deforet , Benoit Orteu , Olivier Gleize
Abstract: A mounting pylon comprising a structure that comprises two C-shaped semi-structures and comprising an upper spar, a lower spar and a lateral flank, an upper panel, a lower panel, a reacting attachment point, two bars attached between the reacting attachment point and a jet engine, and a front wing attachment point attached to a wing box. The lateral flank comprises joists that are aligned between the front wing attachment point and the reacting attachment point, and where the angles between two successive joists are equal.
-
公开(公告)号：US10858114B2
公开(公告)日：2020-12-08
申请号：US16431280
申请日：2019-06-04
Applicant: Airbus Operations SAS
Inventor： Thomas Deforet , Jacky Puech
Abstract: An assembly for an aircraft comprising a pylon having a mounting plate having a front face and a rear face and through which there passes, between the front face and the rear face, at least one central bore, a front engine mount comprising a spar with a rear face bearing against the mounting plate front face and which, for each central bore, has a complementary central bore aligned with the central bore, and for each central bore, a mounting system. The mounting system comprises a shear pin inserted into the central bore and the complementary central bore from the rear face with a flange bearing against the rear face, a support with a central hole, the diameter of which is greater than the flange diameter and fixed to the rear face, and a cap fixed to the support closing off the central hole and bearing against the shear pin.
-
公开(公告)号：US10934009B2
公开(公告)日：2021-03-02
申请号：US16180129
申请日：2018-11-05
Applicant: Airbus Operations SAS
Inventor： Stéphane Combes , Jean Geliot , Thomas Deforet , Adeline Soulie , Benoit Orteu
IPC: B64D27/26
Abstract: An engine attachment system comprising an engine pylon with a top wall, a bottom wall and two lateral walls, and a front engine attachment with a beam which bears two connecting rods for fixing the engine. The engine attachment system also comprises an intermediate piece with a bottom wall and four lateral walls, wherein the beam is fixed against an outer face of the bottom wall, wherein the intermediate piece is fitted at a front-end face of the engine pylon in such a way that an inner face of the bottom wall comes against the front-end face of the engine pylon, and in such a way that the lateral walls of the intermediate piece are superposed with the walls of the engine pylon. In such an engine attachment system, the front engine attachment is thus located on the front-end face of the engine pylon, allowing a space saving.
-
公开(公告)号：US10882630B2
公开(公告)日：2021-01-05
申请号：US16138242
申请日：2018-09-21
Applicant: Airbus Operations SAS
Inventor： Stéphane Combes , Jean Geliot , Thomas Deforet , Adeline Soulie , Benoit Orteu
Abstract: A dual-flow jet engine comprising a fixed structure, a central core, and a cowl comprising a fixed part and a mobile cowl mounted to be rotationally mobile on the fixed structure via hinges with swan neck fitting. The fixed part has a first edge and the mobile cowl has a second edge, in which, when the mobile cowl is in a closed position, the second edge extends against the first edge. For each hinge with swan neck fitting, the fixed part is hollowed at the first edge, so as to delimit a recess opposite the swan neck fitting and allow the passage of the swan neck fitting when the mobile cowl switches from the closed position to the open position. The recess for each hinge with swan neck fitting allows for a reduction of the dimensions of the swan neck during the movement of the mobile cowl.
-
公开(公告)号：US10647441B2
公开(公告)日：2020-05-12
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
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.
-
-
-
-
-
-
-
-
-
Search Results
26
records
(took 0.013 seconds)
