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1.发明申请公开(公告)号：US20190284952A1
公开(公告)日：2019-09-19
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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2.发明申请公开(公告)号：US20190283892A1
公开(公告)日：2019-09-19
申请号：US16274601
申请日：2019-02-13
Applicant: Airbus Operations SAS
Inventor： Pascal GARDES , Frédéric RIDRAY , Frédéric PIARD , José GONCALVES
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.发明申请公开(公告)号：US20190178206A1
公开(公告)日：2019-06-13
申请号：US16209413
申请日：2018-12-04
Applicant: Airbus Operations SAS
Inventor： Frédéric RIDRAY , Lionel CZAPLA , Frédéric PIARD
Abstract: A engine comprising a fan casing and a nacelle, the nacelle comprising a fixed structure and a thrust reversing system having a mobile assembly with a mobile cowl and a frame. The mobile assembly is translationally mobile on the fixed structure between an advanced position and a retracted position to define a window between the secondary jet and the outside of the nacelle. Inner and outer doors are mounted articulated between a stowed position and a deployed position. For each pair of doors, a runner is translationally mobile between a first and a second position. The switching from the stowed position to the deployed position of each door is mechanically associated with the switching of the runner from the first position to the second position and vice versa. For each runner, an actuator ensures the translational displacement of the runner from the first position to the second position.
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公开(公告)号：US20230132103A1
公开(公告)日：2023-04-27
申请号：US17971680
申请日：2022-10-24
Applicant: Airbus Operations SAS
Inventor： Lionel CZAPLA , Frédéric PIARD
IPC: B64D29/00
Abstract: An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.
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5.发明申请公开(公告)号：US20200025139A1
公开(公告)日：2020-01-23
申请号：US16264891
申请日：2019-02-01
Applicant: Airbus Operations SAS
Inventor： Frédéric RIDRAY , Frédéric PIARD
IPC: F02K1/72
Abstract: A jet engine comprising an engine, a fan casing and a nacelle comprising a fixed structure and a thrust reversing system having a mobile assembly with a mobile cowl and a frame. The mobile assembly is translationally mobile on the fixed structure between an advanced and a retracted position to define a window between the secondary jet and outside of the nacelle. Inner and outer doors are mounted articulated between a stowed and a deployed position. For each pair of doors, a runner is translationally mobile between a first and second position. Switching each door of the pair from the stowed to the deployed position is mechanically associated with the runner switching from the first to the second position. For each runner, an actuator ensures the translational runner displacement from the first to the second position. Each runner comprises two portions fastened to one another to adjust the mechanism.
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Patent Agency Ranking
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
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.
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公开(公告)号：US20180346138A1
公开(公告)日：2018-12-06
申请号：US15984622
申请日：2018-05-21
Applicant: Airbus Operations SAS
Inventor： Frédéric RIDRAY , Lionel CZAPLA , Frédéric PIARD
Abstract: A propulsion system comprising a pylon, a turbomachine with a core and a nacelle. The nacelle comprises two inner cowls and two outer cowls around the inner cowls, where each outer cowl is mounted articulated via hinges and is mobile between a closed position in which the outer cowl is tightened around the core and an open position in which the outer cowl is separated from the core. Furthermore, each inner cowl is mounted articulated on the pylon via fixed hinges and is mobile between a closed position in which the inner cowl is tightened around the core and an open position in which the inner cowl is separated from the core. The placement of the hinges between the pylon and each inner cowl makes it possible to separate the rotation of the inner cowl from the rotation of the associated outer cowl.
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公开(公告)号：US20230084689A1
公开(公告)日：2023-03-16
申请号：US17939000
申请日：2022-09-07
Applicant: Airbus Operations SAS
Inventor： Frédéric PIARD , Lionel CZAPLA
Abstract: An assembly including a support panel of an internal fixed structure, a thermal protection element and a plurality of fastening systems. Each fastening system includes a female part secured to the support panel and which has, in its interior, a circular shoulder, and a male part including a sleeve pierced with a main bore, a slide movable in translation in the main bore and a plurality of balls. For each ball, the sleeve has a secondary bore, and each ball is movable along the secondary bore between a locking position and an unlocking position. The slide is movable in translation between a blocking position and an unlocking position. Such an assembly makes it possible to fasten the thermal protection element to the support panel in a simple and rapid manner, also permitting easy removal if necessary.
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9.发明申请公开(公告)号：US20190309704A1
公开(公告)日：2019-10-10
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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10.发明申请公开(公告)号：US20190293021A1
公开(公告)日：2019-09-26
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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