公开(公告)号：US20220228541A1

公开(公告)日：2022-07-21

申请号：US17580110

申请日：2022-01-20

Applicant: Airbus Operations SAS

Inventor： Alain PORTE ,  Lionel CZAPLA ,  Benjamin THUBERT

IPC: F02K3/02

Abstract: A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.

公开(公告)号：US20210207557A1

公开(公告)日：2021-07-08

申请号：US17140717

申请日：2021-01-04

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Benjamin THUBERT ,  Julien LE FANIC

IPC: F02K1/72 ,  F02K1/76

Abstract: A turbofan having a nacelle delimiting a duct for a bypass flow and including a fixed structure including a guide vane support with guide vanes, a mobile cowl movable in translation between an advanced position and a retracted position, arms, each one being mobile in rotation on the guide vane support between a stowed position and a deployed position and comprising a distal end and a proximal end, for each pair of adjacent arms, a flexible screen extending angularly between the two arms, and of which an exterior edge is attached to the guide vane support, and wherein the distal end of each arm is fixed along the interior edge, a link rod mounted articulated between the distal ends, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Such an arrangement allows a reduction in weight.

公开(公告)号：US20210207556A1

公开(公告)日：2021-07-08

申请号：US17140707

申请日：2021-01-04

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Benjamin THUBERT ,  Julien LE FANIC

IPC: F02K1/72 ,  F02K1/76

Abstract: A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.

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

IPC: F02K1/76 ,  F02K1/62

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.

公开(公告)号：US20250027452A1

公开(公告)日：2025-01-23

申请号：US18772636

申请日：2024-07-15

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Rémi AMARGIER

IPC: F02C7/25 ,  B64D27/10 ,  B64D29/08 ,  B64D37/30 ,  B64D37/32 ,  F02C7/22

Abstract: A propulsion assembly having a combustion chamber and a turbine, a nacelle with a front cowl facing the turbine, with a window passing through it, and a rear cowl to the rear of the turbine, a fire barrier between the front cowl and the rear cowl, a dihydrogen supply pipe meandering from the inside of the rear cowl, then in a sealed manner through the fire barrier, then through the window as far as the combustion chamber, wherein the supply pipe has an intermediate section between the fire barrier and the window, and a plate fastened in a sealed manner to the intermediate section and fastened in a sealed manner to the front cowl around the window.

公开(公告)号：US20250026483A1

公开(公告)日：2025-01-23

申请号：US18776566

申请日：2024-07-18

Applicant: Airbus Operations SAS

Inventor： Jérôme MILLIERE ,  Lionel CZAPLA ,  Romain JOUBERT

IPC: B64D37/30

Abstract: A module for an aircraft, the module comprising a sealed housing comprising walls delimiting an interior volume, a processing system intended to process dihydrogen fixed on the inside of the sealed housing and filling elements filling at least in part the interior volume around the processing system. The filling elements may be foam or beads. Also an aircraft with such a module.

公开(公告)号：US20240417090A1

公开(公告)日：2024-12-19

申请号：US18742442

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 first and second parts of the baseplate placed against each other so as to form 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 a sleeve, a pair of flanges and fasteners to the engine pylon.

公开(公告)号：US20240174368A1

公开(公告)日：2024-05-30

申请号：US18519467

申请日：2023-11-27

Applicant: Airbus Operations SAS

Inventor： Jérôme CASSAGNE ,  Frédéric VINCHES ,  Lionel CZAPLA ,  Kotaro FUKASAKU ,  Rémi AMARGIER

IPC: B64D27/24 ,  B60L50/70 ,  B64D27/26

CPC classification number: B64D27/24 ,  B60L50/70 ,  B64D27/26 ,  B60L2200/10 ,  B64D2027/262

Abstract: A propulsion assembly for an aircraft, having a T-shaped chassis with a horizontal structure and a vertical structure, a gearbox fastened to a front of the chassis, and a propulsion system having the following propulsion elements: an electric motor driving the components of the gearbox, a fuel cell, a tank and a cooling system, wherein the propulsion elements are fastened beneath the horizontal structure and against the vertical structure by fastening means.

公开(公告)号：US20240150033A1

公开(公告)日：2024-05-09

申请号：US18356655

申请日：2023-07-21

Applicant: Airbus Operations SAS

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

IPC: B64D37/30 ,  B64D37/00 ,  F02C7/232

CPC classification number: B64D37/30 ,  B64D37/005 ,  F02C7/232

Abstract: A supply system for an aircraft, wherein the supply system has a supply module with outlet pipes, feed pipes connected to dihydrogen tanks, and means for channeling the dihydrogen in the feed pipes towards the outlet pipes, a distribution module having introduction pipes connected to the outlet pipes via heaters, distribution pipes connected to an engine, and means for channeling the dihydrogen in the introduction pipes towards the distribution pipes, and a control unit which commands the means of the supply module and of the distribution module depending on the information provided by the detection means. Also an aircraft with such a supply system.

公开(公告)号：US20240067355A1

公开(公告)日：2024-02-29

申请号：US18456587

申请日：2023-08-28

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Emmanuel VARDELLE

IPC: B64D37/30 ,  B64D27/12 ,  B64D37/04

CPC classification number: B64D37/30 ,  B64D27/12 ,  B64D37/04

Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective cylinder fastened to the frame or to the casing by fastening means and positioned around the casing and between the supply pipe and the turbine. With such an arrangement, if a blade of the turbine became detached it would meet the protective cylinder blocking its path to the dihydrogen pipe and would thus be diverted or stopped.