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：US20230340928A1

公开(公告)日：2023-10-26

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.