公开(公告)号：US12292015B2

公开(公告)日：2025-05-06

申请号：US18644977

申请日：2024-04-24

Applicant: Airbus Operations SAS

Inventor： Frédéric Chelin ,  Christophe Bourdeau ,  Olivier Scholz

IPC: F02K1/72 ,  F02K1/62 ,  F02K1/76

Abstract: An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state; at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system toward the upstream end of the nacelle, at least one downstream deflector positioned at the downstream edge of the lateral opening and configured to deflect the air stream deflected by the deflection system toward the upstream end of the nacelle.

公开(公告)号：US12247528B2

公开(公告)日：2025-03-11

申请号：US18303076

申请日：2023-04-19

Applicant: Airbus Operations SAS

Inventor： Frédéric Chelin ,  Christophe Bourdeau ,  Romain Cusset ,  Lauren Davis

IPC: F02K1/72 ,  F02K1/76

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：US12012911B2

公开(公告)日：2024-06-18

申请号：US18129507

申请日：2023-03-31

Applicant: AIRBUS OPERATIONS (SAS)

Inventor： Lauren Davis ,  Christophe Bourdeau ,  Frédéric Chelin

IPC: F02K1/72

CPC classification number: F02K1/72

Abstract: A deflector for an ejection structure of a thrust reverser is disclosed including a deflector plate configured to act on an aerodynamic flow, the deflector plate having a concave upstream face, a convex downstream face, an inlet end, and an outlet end. The upstream face and the downstream face of the deflector plate have different curved profiles, the deflector has a particular profile giving it properties allowing it to act effectively on the aerodynamic flow so as to enhance the performance of the thrust reverser in which it is mounted.

公开(公告)号：US11028801B2

公开(公告)日：2021-06-08

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.