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：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：US20190162079A1

公开(公告)日：2019-05-30

申请号：US16195142

申请日：2018-11-19

Applicant: Airbus Operations SAS

Inventor： Laurent BERTANDEAU ,  Grégory DE OLIVEIRA ,  Erwan KRIER ,  Sandrine ANDRE ,  Morad KASSEM ,  Michael KILKENNY

IPC: F01D25/30 ,  F02K1/04 ,  F01D25/28 ,  B64D33/04

Abstract: An internal structure of a primary exhaust duct of a turbomachine. The internal structure comprises a primary wall comprising a surface of revolution, allowing air to pass through the orifices and forming an internal surface of the primary exhaust duct, an interior skin, comprising a surface of revolution, arranged inside the primary wall and extending between an upstream flank for facing toward the front of the turbomachine and a downstream flank for facing toward the rear of the turbomachine, and a plurality of spacers angularly distributed around a periphery of the interior skin and fixed between the primary wall and the interior skin. The particular way in which the interior wall is fixed makes the internal structure easier to construct and allows attenuation of noise at chosen frequencies.