公开(公告)号：US20240239508A1

公开(公告)日：2024-07-18

申请号：US18411190

申请日：2024-01-12

Applicant: Airbus Operations SAS

Inventor： Grégory DE OLIVEIRA ,  Thomas BOURDIEU ,  Julien FERREIRA

IPC: B64D29/06

CPC classification number: B64D29/06

Abstract: A propulsion system comprising a chassis, a fan cowl, an articulation system fixed between the chassis and the fan cowl and comprising a shaft with two offset cylinders in which a central cylinder is movably mounted in rotation on the chassis and wherein a lateral cylinder is movably mounted in rotation on the fan cowl, a blocking device limits the rotation of the central cylinder relative to the chassis between a closed position and an intermediate position, and a stopping device allows rotation of the fan cowl between the intermediate position and the open position and preventing rotation of the fan cowl beyond the intermediate position.

公开(公告)号：US20240228051A1

公开(公告)日：2024-07-11

申请号：US18408127

申请日：2024-01-09

Applicant: Airbus Operations SAS

Inventor： Julien FERREIRA ,  Rémy WEILL

IPC: B64D29/06 ,  F01D25/24 ,  F01D25/28

CPC classification number: B64D29/06 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/36 ,  F05D2260/30

Abstract: A propulsion system having a chassis, two fan cowls and, for each one, an articulation system fastened between the chassis and the fan cowl, so as to move the fan cowl between a closed position and an open position and a locking device like a clamping screw, wherein each articulation system has, for each fan cowl, two pantograph hinges. With such an arrangement, each fan cowl moves away laterally as soon as its opening starts.

公开(公告)号：US20200232344A1

公开(公告)日：2020-07-23

申请号：US16743077

申请日：2020-01-15

Applicant: Airbus Operations SAS

Inventor： Julien FERREIRA ,  Vincent TROCELLIER ,  Sandrine ANDRE ,  Michael KILKENNY

IPC: F01D25/30 ,  F02K1/80 ,  F01N13/08

Abstract: An internal structure of a primary exhaust duct of a turbomachine, the internal structure comprising a primary wall comprising a surface of revolution about a longitudinal axis, allowing the air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin comprising a surface of revolution about the longitudinal axis, arranged inside the primary wall, an upstream flange and a downstream flange which attach the interior skin to the interior of the primary wall, at least one separator which is attached to the interior skin and which extends from the interior skin towards the primary wall, the, or each, separator extends in a plane generally parallel to the longitudinal axis, between the two flanges, and the, or each, separator is not attached to the primary wall.

公开(公告)号：US20240239507A1

公开(公告)日：2024-07-18

申请号：US18402979

申请日：2024-01-03

Applicant: Airbus Operations SAS

Inventor： Grégory DE OLIVEIRA ,  Thomas BOURDIEU ,  Julien FERREIRA

IPC: B64D29/06 ,  B64D45/00 ,  E05B41/00

CPC classification number: B64D29/06 ,  B64D45/00 ,  E05B41/00

Abstract: An aircraft with a visual indication system for indicating the locked or unlocked state of a locking device. The system comprises has an opening passing through a wall, a transparent wall closing off the opening and allowing an inner zone of the aircraft to be seen from an outer zone, an indicator to move between first and second positions depending respectively on the locked or unlocked state. The indicator is positioned in the inner zone of the aircraft and has a zone visible through the transparent wall from the outer zone of the aircraft when the indicator is in the first position, the zone not being visible when the indicator is in the second position.

公开(公告)号：US20240124158A1

公开(公告)日：2024-04-18

申请号：US18480785

申请日：2023-10-04

Applicant: Airbus Operations SAS

Inventor： Julien FERREIRA ,  Rémy WEILL

IPC: B64F5/10 ,  B64C23/06

CPC classification number: B64F5/10 ,  B64C23/06 ,  B64C5/08

Abstract: A method for mounting a vortex generator on an aerodynamic panel of an aircraft, including, before the step of assembling the vortex generator and the aerodynamic panel, a step of installing at least one shim interposed between the base of the vortex generator and the aerodynamic panel, the shim including a first face, oriented towards the aerodynamic panel during operation, that is shaped like the inner surface of the aerodynamic panel, and a second face, oriented towards the base during operation, that is shaped like the upper face of the arm of the base. This solution makes it possible to manufacture the vortex generator without taking into account the curvature of the aerodynamic panel. An aircraft is provided including at least one vortex generator mounted in this way.

公开(公告)号：US20210262364A1

公开(公告)日：2021-08-26

申请号：US17181566

申请日：2021-02-22

Applicant: Airbus Operations SAS

Inventor： Sandrine ANDRE ,  Vincent TROCELLIER ,  Julien FERREIRA ,  Michael KILKENNY

IPC: F01D25/30 ,  F01D9/06 ,  F01D25/28 ,  F02K1/34

Abstract: An internal structure of a primary exhaust duct of a turbomachine, which has a primary wall allowing air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin arranged inside the primary wall, and at least one separator of which a first edge region is attached to the interior skin and which has two geometries. A change from the first geometry to the second takes place when the temperature of the separator exceeds a first temperature, and the change from the second to the first takes place when the temperature of the separator drops below a second temperature. The coefficient of expansion of the separator is greater than that of the interior skin. The variation in the geometry of the separators depending on the temperature of the engine eases assembly at ambient temperature due to the compression of the separators.