公开(公告)号：US20200025141A1

公开(公告)日：2020-01-23

申请号：US16431173

申请日：2019-06-04

Applicant: Airbus Operations SAS

Inventor： Pascal GARDES ,  Frédéric RIDRAY ,  Lionel CZAPLA

IPC: F02K1/72 ,  F02K1/76

Abstract: A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.

公开(公告)号：US20190003421A1

公开(公告)日：2019-01-03

申请号：US16017634

申请日：2018-06-25

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Laurent TIZAC ,  Frédéric RIDRAY ,  Lionel CZAPLA ,  Frédéric PIARD

IPC: F02K1/72 ,  F02K3/06

Abstract: A turbofan comprising a fan casing and a nacelle comprising a cowl translatable between an advanced position and a pushed-back position in which the mobile cowl and the fan casing define a window therebetween. The nacelle also comprises reverser flaps, each reverser flap being mounted in a linked manner on the mobile assembly between a closed position in which it obstructs the window and an open position in which it does not obstruct the window. The nacelle also has an impelling mechanism comprising a lever arm rotatable on the mobile assembly and having a roller, a connecting rod mounted rotatably between the reverser flap and the lever arm, and a channel receiving the roller, the channel having a front part parallel with the translation direction and a rear part extending after the front part and oriented inward as it progresses from the front toward the rear.

公开(公告)号：US20180346138A1

公开(公告)日：2018-12-06

申请号：US15984622

申请日：2018-05-21

Applicant: Airbus Operations SAS

Inventor： Frédéric RIDRAY ,  Lionel CZAPLA ,  Frédéric PIARD

IPC: B64D29/06 ,  F02K1/72 ,  B64D27/26 ,  B64D27/18

CPC classification number: B64D29/06 ,  B64D29/08

Abstract: A propulsion system comprising a pylon, a turbomachine with a core and a nacelle. The nacelle comprises two inner cowls and two outer cowls around the inner cowls, where each outer cowl is mounted articulated via hinges and is mobile between a closed position in which the outer cowl is tightened around the core and an open position in which the outer cowl is separated from the core. Furthermore, each inner cowl is mounted articulated on the pylon via fixed hinges and is mobile between a closed position in which the inner cowl is tightened around the core and an open position in which the inner cowl is separated from the core. The placement of the hinges between the pylon and each inner cowl makes it possible to separate the rotation of the inner cowl from the rotation of the associated outer cowl.