公开(公告)号：US20200025141A1

公开(公告)日：2020-01-23

申请号：US16431173

申请日：2019-06-04

Applicant: Airbus Operations SAS

Inventor： Pascal GARDES ,  Frédéric RIDRAY ,  Lionel CZAPLA

IPC: F02K1/72 ,  F02K1/76

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.

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

IPC: F02K1/72 ,  F02K3/06

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.

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

IPC: B64D29/06 ,  F02K1/72 ,  B64D27/26 ,  B64D27/18

CPC classification number: B64D29/06 ,  B64D29/08

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.

公开(公告)号：US20250121927A1

公开(公告)日：2025-04-17

申请号：US18908982

申请日：2024-10-08

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Nandakumar DEVASIGAMANI ,  Lionel CZAPLA ,  Jorge A. CARRETERO BENIGNOS

IPC: B64C7/00 ,  B64D33/04 ,  B64D37/30

Abstract: A propulsion assembly having a propulsion system comprising a fairing, a rotary assembly having a combustion chamber and housed in the fairing, an exhaust nozzle positioned downstream of the combustion chamber and delimited by a nozzle wall, and ensuring the discharge of the combustion gases originating from the combustion of the dihydrogen in the combustion chamber, a dihydrogen tank, a supply duct which connects the tank and the combustion chamber, and at least one vane positioned inside the exhaust nozzle, wherein the supply duct has a duct portion arranged in the vane.

公开(公告)号：US20250026484A1

公开(公告)日：2025-01-23

申请号：US18776574

申请日：2024-07-18

Applicant: Airbus Operations SAS

Inventor： Jérôme MILLIERE ,  Lionel CZAPLA ,  Romain JOUBERT

IPC: B64D37/32 ,  B64D37/16 ,  B64D37/30

Abstract: A module for an aircraft, the module comprising a sealed housing comprising walls delimiting an interior volume, a processing system to process dihydrogen and fixed on the inside of the housing, an inlet port connected to the interior volume and equipped with a first shut-off valve, an outlet port connected to the interior volume and equipped with a second shut-off valve and beads filling the interior volume.

公开(公告)号：US20240417091A1

公开(公告)日：2024-12-19

申请号：US18742394

申请日：2024-06-13

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Kotaro FUKASAKU ,  Rémi AMARGIER

IPC: B64D27/40

Abstract: A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with first and second sleeves, a pair of flanges and a fasteners to the engine pylon. The fasteners comprise two adjacent fastening screws extending parallel to each other.

公开(公告)号：US20240327023A1

公开(公告)日：2024-10-03

申请号：US18602498

申请日：2024-03-12

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Christophe LABARTHE ,  Kotaro FUKASAKU

IPC: B64D37/30 ,  B64D27/18 ,  B64D29/02 ,  F02K1/36

CPC classification number: B64D37/30 ,  B64D27/18 ,  B64D29/02 ,  F02K1/36

Abstract: A propulsive assembly comprising a nacelle delimiting an internal volume, a T-shaped frame comprising a first wall fixed to the wing and a second wall that is vertical and that divides the internal volume into two sub-volumes, a dihydrogen consumer device, for each sub-volume, a dihydrogen processing system, a supply line connected between the processing system and the consumer device, and an input line connected between the processing system and a dihydrogen tank. Also an aircraft with a wing and such a propulsive assembly.

公开(公告)号：US20240125284A1

公开(公告)日：2024-04-18

申请号：US18484548

申请日：2023-10-11

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Benjamin THUBERT

IPC: F02K1/32

CPC classification number: F02K1/32

Abstract: An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.

公开(公告)号：US20240026813A1

公开(公告)日：2024-01-25

申请号：US18356662

申请日：2023-07-21

Applicant: Airbus Operations SAS

Inventor： Pierre-Olivier MARTIN ,  Lionel CZAPLA ,  Mathieu BELLEVILLE

IPC: F02C3/22 ,  F02C7/224 ,  F02C7/232

CPC classification number: F02C3/22 ,  F02C7/224 ,  F02C7/232

Abstract: A supply system for an aircraft arranged between two dihydrogen tanks and an engine. The supply system includes a supply module that assures the flow of dihydrogen between the tanks and an outlet pipe and two heaters mounted in series on a main pipe connected to the engine. The supply system also includes a network of pipes and solenoid valves that, in the event of a problem in one of the components of the supply system, enable dihydrogen to be redirected so as to reach the engine. Also an aircraft with such a supply system.

公开(公告)号：US20220411084A1

公开(公告)日：2022-12-29

申请号：US17849895

申请日：2022-06-27

Applicant: Airbus Operations SAS ,  Airbus SAS

Inventor： Pascal POME ,  Nicolas JOLIVET ,  Rémi AMARGIER ,  Lionel CZAPLA ,  Franck ALVAREZ ,  Kotaro FUKASAKU ,  Benoît PENVEN ,  Delphine JALBERT ,  Laurent LAFONT ,  Milan TASIC ,  Frédéric GOUPIL ,  Jean-Victor LAPEYRE ,  Emmanuel MERMOZ

IPC: B64D27/24 ,  B64D27/26

Abstract: A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.