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1.发明授权公开(公告)号：US11215141B2
公开(公告)日：2022-01-04
申请号：US16431173
申请日：2019-06-04
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Frédéric Ridray , Lionel Czapla
Abstract: A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.
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公开(公告)号：US11161619B2
公开(公告)日：2021-11-02
申请号：US16274601
申请日：2019-02-13
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Frédéric Ridray , Frédéric Piard , José Goncalves
IPC: B64D29/06 , F02K1/80 , F02K1/72 , B64D27/18 , F02K3/06 , B64D29/02 , F02K1/62 , B64D29/04 , F02K1/64 , F02K1/70 , F01D25/28
Abstract: A turbojet engine comprising an engine, a nacelle comprising a fan case, an intermediate case having a part forming a hub and an outer shroud radially spaced away from the hub by a secondary, or bypass, flow path and fixed to the hub via arms, in which the outer shroud is situated to the rear and in the continuity of the fan case, a fixed structure fixed to the outer shroud, a mobile assembly mounted with the ability to effect translational movement on the fixed structure, and a ramp fixed to the outer shroud and configured to direct the secondary or bypass flow to exit the outer shroud. Such a turbojet engine makes it possible to simplify assembly and among other things, makes it possible to fix the ramp directly to the outer shroud.
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3.发明授权公开(公告)号：US11434849B2
公开(公告)日：2022-09-06
申请号：US16827021
申请日：2020-03-23
Applicant: Airbus Operations SAS
Inventor： Antoine Cousin , Frédéric Ridray
Abstract: A turbofan engine with a nacelle including a runner translationally mobile between advanced and back-off positions to open a window between a stream and an outside, a plurality of blades, each rotatable on the runner between retracted and deployed positions, and a maneuvering system displacing each blade and comprising, for each blade, a shaft rotatable on the runner and to which the blade is fixed, and a toothed segment on the shaft, and a toothed arc rotatable on the runner about a longitudinal axis, the tooth arc teeth meshing with the toothed segment teeth, a slip translationally mobile on the runner in a plane at right angles to the longitudinal axis between first and second positions, a connecting rod mounted articulated between the slip and the toothed arc, a rib integral to the fixed structure, and a guiding U integral to the slip and which straddles the rib.
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公开(公告)号：US11255293B2
公开(公告)日：2022-02-22
申请号：US16832344
申请日：2020-03-27
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Frédéric Ridray , Benoit Orteu , Pascal Gougeon , Frédéric Piard
IPC: F02K1/72
Abstract: A turbofan with a secondary duct and including a fixed structure and a mobile assembly including a frame with openwork regions. The mobile assembly is translatable between advanced and extended positions. The openwork regions are positioned across the window in the extended position. A plurality of blocking doors is provided, each being mobile between stowed and deployed positions. An array of rams move the mobile assembly. A cascade grille mounts on the frame across the openwork region. The grille slides on the frame parallel to the translational direction. For each grille, a rear stop limits rearward movement, and a compression spring pushes the grille to the rear for abutment against a rear stop. For each grille, the fixed structure comprises a stop element against which the grille abuts upon movement from the advanced position to the extended position.
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公开(公告)号：US11136938B2
公开(公告)日：2021-10-05
申请号：US16656632
申请日：2019-10-18
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Frédéric Ridray , José Goncalves
Abstract: A bypass turbofan engine with a nacelle comprising a fan case and a thrust-reversal system. The fan case comprises an exterior wall, and the reversal system comprises a slider having an upstream frame, a downstream frame and a plurality of spars fixed between the upstream frame and the downstream frame, in which the slider is able to move between a forward position and a retracted position. The fan case comprises, at a rear edge of its exterior wall, a support. Each support comprises, for each spar, a shoe fixed to the exterior wall and positioned radially about the spar, and a skirt secured to the shoes and extending the rear edge, in which, in a forward position, the skirt bears around the downstream frame, and in which in a forward/retracted/intermediate position, the shoes are distant from the spars from the upstream frame.
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Patent Agency Ranking
公开(公告)号：US11565822B2
公开(公告)日：2023-01-31
申请号：US16708760
申请日：2019-12-10
Applicant: Airbus Operations SAS
Inventor： Philippe Auge , Benoit Orteu , Julien Bernat , Jean Geliot , Delphine Jalbert , Frédéric Ridray , Laurent Lafont , Pascal Gardes
Abstract: A propulsion assembly having a pylon, a turbomachine comprising an engine and a fan that is enclosed by a fan casing, a nacelle surrounding the engine and the fan casing and having a load support disposed in the top part of the nacelle, a front engine attachment between the pylon and a front part of the engine, a rear engine attachment between the pylon and a rear part of the engine, a front fan attachment between the fan casing and the load support, and a rear pylon attachment between the pylon and the load support. Such a propulsion assembly allows a reduction in bulk since the load of the turbojet engine is distributed between the load support and the pylon, and the pylon is attached to the engine.
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7.发明授权公开(公告)号：US11187188B2
公开(公告)日：2021-11-30
申请号：US16371430
申请日：2019-04-01
Applicant: Airbus Operations SAS
Inventor： Frédéric Ridray , Lionel Czapla , Frédéric Piard
Abstract: A ducted fan turbojet including a nacelle including a fixed structure, a thrust reverser system having a frame, a mobile structure fastened to the frame, inner doors and outer doors hinged at the frame. The frame is mobile in translation on the fixed structure between a forward position and a rear position so as to define a window between the fixed structure and the mobile structure, the window being open between a bypass duct and the exterior of the nacelle. Each door is mobile between a stowed position and a deployed position and the mobile structure is assembled hinged on the frame via at least one hinge whose axis of rotation is globally parallel to a longitudinal axis of the ducted fan turbojet.
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公开(公告)号：US11143141B2
公开(公告)日：2021-10-12
申请号：US16359475
申请日：2019-03-20
Applicant: Airbus Operations SAS
Inventor： Frédéric Ridray , Frédéric Piard
Abstract: A nacelle having a window open between a secondary jet and the outside of the nacelle and comprising a fixed structure and a thrust-reversing system having a frame and outer doors articulated on the frame. The frame is translationally mobile on the fixed structure between an advanced position and a retracted position. Each outer door is mobile between a stowed position and a deployed position. The nacelle comprises at least one anti-vibration system which comprises a chock fixed to the fixed structure and having a hole, and a finger fixed to the outer door. The finger and the hole are configured so that the finger lodges in the hole when the frame is in advanced position. Such a nacelle makes it possible to limit the vibrations of the outer doors when they are in stowed position and before the mobile frame begins to be displaced to the retracted position.
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公开(公告)号：US11105297B2
公开(公告)日：2021-08-31
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：US10830089B2
公开(公告)日：2020-11-10
申请号：US16281593
申请日：2019-02-21
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Frédéric Ridray , Frédéric Piard
Abstract: A turbofan with a fan casing and a nacelle which comprises a fixed structure, a movable assembly with a movable cowl and a slide, which is translationally movable between an advanced position and a retreated position in which the movable cowl is moved away from the fan casing in order to define a window open between a duct and the outside of the nacelle, a plurality of blades, each being mounted rotatably on the slide, where each blade is movable between a retracted position in which the blade is outside of the duct and a deployed position in which the blade is across the duct, a set of actuators for moving the slide and an operating system configured to move each blade from the retracted position to the deployed position, and vice versa.
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