公开(公告)号：US20230340929A1

公开(公告)日：2023-10-26

申请号：US18303076

申请日：2023-04-19

Applicant: Airbus Operations SAS

Inventor： Frédéric CHELIN ,  Christophe BOURDEAU ,  Romain CUSSET ,  Lauren DAVIS

IPC: F02K1/76 ,  F02K1/72

CPC classification number: F02K1/72 ,  F02K1/766

Abstract: A deflector provided with a spoiler for a thrust reverser of an aircraft engine nacelle. The deflector, a lateral deflector or an orbital deflector, may be in an exhaust structure of a thrust reverser and comprises a deflector plate configured to act on an aerodynamic flow. The deflector plate has a concave upstream face and a convex downstream face, as well as an intake end and an exhaust end. The deflector is fitted with a spoiler rigidly connected to the exhaust end of the deflector plate and arranged transversely in relation to the deflector plate. The spoiler endowing the deflector with specific properties to act on the aerodynamic flow.

公开(公告)号：US20200240359A1

公开(公告)日：2020-07-30

申请号：US16745606

申请日：2020-01-17

Applicant: Airbus Operations SAS

Inventor： Pascal GARDES ,  Guillaume SEGUIN ,  Laurent TIZAC ,  Fabien MENOU ,  Frédéric RIDRAY ,  Benoit ORTEU ,  Romain CUSSET

IPC: F02K1/38 ,  B64D29/06 ,  F16H55/26 ,  F16H25/18

Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

公开(公告)号：US20200025138A1

公开(公告)日：2020-01-23

申请号：US16201265

申请日：2018-11-27

Applicant: Airbus Operations SAS

Inventor： Christophe BOURDEAU ,  Quentin VAUCOULOUX ,  Romain CUSSET

IPC: F02K1/72

Abstract: A grating for the formation of a reverse flow of a turbofan engine and comprising fins of a first type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the first type, fins of a second type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the second type. In this grating, each fin of one of the two types is inserted between two fins of the other type moving from forward to aft and the cord of the fins of the second type is smaller than the cord of the fins of the first type.