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公开(公告)号：US20210284350A1
公开(公告)日：2021-09-16
申请号：US17181577
申请日：2021-02-22
Applicant: Airbus Operations SAS
Inventor： Fabien MENOU , Julie CAZALIS
Abstract: A nacelle having a fan casing, a cowl that movable between an advanced position and a retracted position that opens an opening between a bypass duct and the outside, deflectors secured to the mobile cowl, wherein, in the advanced position, they are around the fan casing and wherein, in the retracted position, they are across the opening, and a fan ramp with a mounting base and flaps that are able to rotate on the mounting base between a stowed position and a deployed position. For each flap, the fan ramp has a return element that urges the flap) into the deployed position, and the deflectors have a stop in contact with the flap when the mobile cowl passes from the retracted position to the advanced position. Thus, in the advanced position, the flaps are folded back and their bulk is reduced.
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Patent Agency Ranking
2.发明申请公开(公告)号：US20220136459A1
公开(公告)日：2022-05-05
申请号：US17516251
申请日：2021-11-01
Applicant: Airbus Operations SAS
Inventor： Fabien MENOU , Laurent CAZEAUX , Thierry GACHES
IPC: F02K3/02
Abstract: A turbofan engine having a duct for a bypass flow and blades. Each blade is mobile between a stowed position and a deployed position. Each blade includes a rigid core a second, free end, and a sheath into which the core and the second end slide. Each sheath includes a first part which surrounds at least one part of the core and the second end, and an aileron which extends beyond the core facing the first part of the adjacent blade. The sheath is made of a flexible material such that the bypass flow causes the sheath to come into contact with the first part of the adjacent blade. A turbofan engine of this kind makes it possible to create blades whose production costs are low but whose aerodynamic behavior is effective.
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公开(公告)号：US20200240359A1
公开(公告)日：2020-07-30
申请号：US16745606
申请日：2020-01-17
Applicant: Airbus Operations SAS
Inventor： Pascal GARDES , Guillaume SEGUIN , Laurent TIZAC , Fabien MENOU , Frédéric RIDRAY , Benoit ORTEU , Romain CUSSET
Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.
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公开(公告)号：US20210301762A1
公开(公告)日：2021-09-30
申请号：US17209323
申请日：2021-03-23
Applicant: Airbus Operations SAS
Inventor： Fabien MENOU , Stéphanie FESQUET
Abstract: A bypass turbofan engine comprising a nacelle surrounding a flow path for a secondary flow and comprising a fixed structure, a mobile assembly with a slide capable of translational movement on the fixed structure and bearing a mobile cowl and a frame capable of translational movement on the fixed structure and bearing deflectors. The mobile assembly is able to move between a forward position and a retreated position making it possible to open a passage between the flow path and the outside through the deflectors. A differentiation mechanism ensures a length of travel of the slide that is different from the length of travel of the frame, and actuators providing a translational travel of the slide. Fitting a differentiation mechanism means that the length of travel of the deflectors with respect to the length of travel of the mobile cowl can be regulated.
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公开(公告)号：US20210285372A1
公开(公告)日：2021-09-16
申请号：US17199960
申请日：2021-03-12
Applicant: Airbus Operations SAS
Inventor： Pascal GARDES , Fabien MENOU , Pascal GOUGEON , Simon VANDERBAUWEDE
Abstract: An engine including a motor and a nacelle and a duct between the nacelle and the motor. The nacelle includes a fixed structure, a mobile assembly that is mobile between an advanced position and a retracted position to define a window between the duct and the outside, and a plurality of blades that are mobile in rotation between a stowed position and a deployed position, each one extending on either side of its axis of rotation with a first arm and a second arm. In the stowed position, the first arm is outside the duct and the second arm is inside the nacelle, and where, in the deployed position, the first arm is across the duct and the second arm projects out of the nacelle. With such blades, the flow of air is optimally directed towards the front without it being necessary to provide cascades.
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公开(公告)号：US20200256282A1
公开(公告)日：2020-08-13
申请号：US16736474
申请日：2020-01-07
Applicant: Airbus Operations SAS
Inventor： Fabien MENOU , Laurent CAZEAUX , Benoit ORTEU
Abstract: A turbojet comprising a nacelle with a fixed cowl, a fan duct and a thrust reverser comprising a cowl movable between a stowed and a deployed position where the movable cowl is remote from the fixed cowl, at least one blocking flap movable between the closed position and a fixed position where the flap at least partially blocks the fan duct, and also a drive mechanism for moving the movable cowl and the blocking flap. The drive mechanism comprises a roller slide comprising a rail and a roller rotatable in the rail, a connecting rod with a first end movable on the roller and a second end movable on the blocking flap. The rail comprises a bearing surface extending parallel to a turbojet longitudinal axis to support the connecting rod during movement of the movable cowl from the stowed position to an intermediate position between the stowed and deployed positions.
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