公开(公告)号：US20240110536A1

公开(公告)日：2024-04-04

申请号：US18475570

申请日：2023-09-27

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Benjamin THUBERT

IPC: F02K3/04 ,  B64D29/02 ,  B64D29/06

CPC classification number: F02K3/04 ,  B64D29/02 ,  B64D29/06 ,  F05D2220/36

Abstract: A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.

公开(公告)号：US20240067354A1

公开(公告)日：2024-02-29

申请号：US18456586

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 plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

公开(公告)号：US20230045036A1

公开(公告)日：2023-02-09

申请号：US17878331

申请日：2022-08-01

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Antoine ABELE ,  Benjamin THUBERT ,  Alexis PISSAVIN ,  Abhishek VERMA ,  Alistair FORBES ,  Jorge A. CARRETERO BENIGNOS ,  Benedikt BAMMER

IPC: F02C7/224 ,  F02C7/22 ,  B64D37/04 ,  B64D37/30

Abstract: An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.

公开(公告)号：US20190383172A1

公开(公告)日：2019-12-19

申请号：US16424650

申请日：2019-05-29

Applicant: Airbus Operations SAS

Inventor： Thierry GACHES ,  Lionel CZAPLA ,  Bastian SABATHIER

IPC: F01D25/26 ,  B64D33/04 ,  F01D25/30

Abstract: A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.

公开(公告)号：US20250092829A1

公开(公告)日：2025-03-20

申请号：US18883246

申请日：2024-09-12

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Alexis PISSAVIN

IPC: F02C7/22

Abstract: A powerplant for an aircraft, comprising a propulsion system with a core enclosed in a casing and having a combustion chamber, a supply pipe conveying dihydrogen to the combustion chamber by passing through the casing in an injection zone, and a closed enclosure, delimited by first and second walls and containing a downstream pipe, a treatment system for treating the dihydrogen, and the injection zone, wherein the first wall is formed by part of the casing.

公开(公告)号：US20250074612A1

公开(公告)日：2025-03-06

申请号：US18820521

申请日：2024-08-30

Applicant: Airbus Operations SAS

Inventor： Kotaro FUKASAKU ,  Lionel CZAPLA ,  Rémi AMARGIER ,  Alain RAZAFINDRABE ,  Thomas SPIGOLON

IPC: B64D27/40

Abstract: An aircraft comprising at least one engine mounting system which connects a propulsion unit and a wing and which comprises a primary structure, engine mounts connecting the primary structure and the propulsion unit, as well as at least first, second and third wing mounts connecting the primary structure and the wing structure, the first and second wing mounts being offset height-wise with respect to one another, the third wing mount being offset in the longitudinal direction toward the rear with respect to the first and second wing mounts.

公开(公告)号：US20240367810A1

公开(公告)日：2024-11-07

申请号：US18653407

申请日：2024-05-02

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Philippe MOGILKA ,  Lionel CZAPLA

IPC: B64D37/00 ,  B64D37/30 ,  F02C7/22

Abstract: An aircraft with at least one engine system, at least one zone for ejection of debris originating from the engine system and at least one fluid supply circuit. The latter comprises a shutter configured to occupy open and closed states, at least one return element configured to push the shutter to the closed state and at least one control positioned at least partially in the ejection zone and configured to hold the shutter in the open state against the return element. When the control is broken in the case of an accident, it no longer holds the shutter, which switches automatically to the closed state.

公开(公告)号：US20240317419A1

公开(公告)日：2024-09-26

申请号：US18608140

申请日：2024-03-18

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Jérôme MILLIERE ,  Lionel CZAPLA ,  Alexis PISSAVIN

IPC: B64D37/30 ,  B64D37/32

CPC classification number: B64D37/30 ,  B64D37/32

Abstract: A module between a dihydrogen tank and an engine in an aircraft. The module comprises outer and inner boxes, a pipeline between the tank and the engine through the boxes, pressure limiters mounted on the pipeline and the inner box, an exhaust pipeline between the pressure limiters and the outside, shut-off valves mounted on the pipeline at the outer box, a detector for detecting a leak of the pipeline or of the outer box and a controller configured to control each shut-off valve as a function of the information delivered by the detector.

公开(公告)号：US20240109668A1

公开(公告)日：2024-04-04

申请号：US18476586

申请日：2023-09-28

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Philippe MOGILKA ,  Lionel CZAPLA ,  Alexis PISSAVIN

IPC: B64D37/30 ,  B64D27/12 ,  F02C7/22

CPC classification number: B64D37/30 ,  B64D27/12 ,  F02C7/222 ,  B64D29/08

Abstract: A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.

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.