公开(公告)号：US11136938B2

公开(公告)日：2021-10-05

申请号：US16656632

申请日：2019-10-18

Applicant: Airbus Operations SAS

Inventor： Pascal Gardes ,  Frédéric Ridray ,  José Goncalves

IPC: F02K1/72 ,  B29C65/70 ,  B29C65/78 ,  B29C65/00 ,  B29C65/48 ,  B29L31/30 ,  F02K1/54 ,  F02K1/68

Abstract: A bypass turbofan engine with a nacelle comprising a fan case and a thrust-reversal system. The fan case comprises an exterior wall, and the reversal system comprises a slider having an upstream frame, a downstream frame and a plurality of spars fixed between the upstream frame and the downstream frame, in which the slider is able to move between a forward position and a retracted position. The fan case comprises, at a rear edge of its exterior wall, a support. Each support comprises, for each spar, a shoe fixed to the exterior wall and positioned radially about the spar, and a skirt secured to the shoes and extending the rear edge, in which, in a forward position, the skirt bears around the downstream frame, and in which in a forward/retracted/intermediate position, the shoes are distant from the spars from the upstream frame.

公开(公告)号：US11220978B2

公开(公告)日：2022-01-11

申请号：US16699890

申请日：2019-12-02

Applicant: Airbus Operations SAS

Inventor： Pascal Gardes ,  José Goncalves ,  Bastian Sabathier

IPC: F02K1/72 ,  F04D27/02 ,  F01D17/16 ,  F02K1/42 ,  F02K1/12 ,  F02K1/09 ,  F02K1/64

Abstract: A turbofan having a nacelle comprising a slider mobile in translation between an advanced and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one mobile in rotation on the slider between a stowed and a deployed position, where the blades are split into groups, where each group comprises a first blade, and a maneuvering system moving each blade and comprising a cam integral with the first blade of one of the groups and having a tooth, a groove receiving the tooth, a first transmission system transmitting the movement of the first blade bearing the cam to a first blade of each other group, and, for each group, a second transmission system transmitting the movement of the blade that bears the cam or is moved by the first transmission system to each of the other blades of the group.

公开(公告)号：US11161619B2

公开(公告)日：2021-11-02

申请号：US16274601

申请日：2019-02-13

Applicant: Airbus Operations SAS

Inventor： Pascal Gardes ,  Frédéric Ridray ,  Frédéric Piard ,  José Goncalves

IPC: B64D29/06 ,  F02K1/80 ,  F02K1/72 ,  B64D27/18 ,  F02K3/06 ,  B64D29/02 ,  F02K1/62 ,  B64D29/04 ,  F02K1/64 ,  F02K1/70 ,  F01D25/28

Abstract: A turbojet engine comprising an engine, a nacelle comprising a fan case, an intermediate case having a part forming a hub and an outer shroud radially spaced away from the hub by a secondary, or bypass, flow path and fixed to the hub via arms, in which the outer shroud is situated to the rear and in the continuity of the fan case, a fixed structure fixed to the outer shroud, a mobile assembly mounted with the ability to effect translational movement on the fixed structure, and a ramp fixed to the outer shroud and configured to direct the secondary or bypass flow to exit the outer shroud. Such a turbojet engine makes it possible to simplify assembly and among other things, makes it possible to fix the ramp directly to the outer shroud.

公开(公告)号：US11814184B2

公开(公告)日：2023-11-14

申请号：US17532813

申请日：2021-11-22

Applicant: Airbus Operations SAS

Inventor： José Goncalves

IPC: B64D29/06 ,  B64D29/08 ,  F16B5/02 ,  B64D29/00 ,  B64D7/02 ,  B64D29/02

CPC classification number: B64D29/06 ,  B64D29/08 ,  F16B5/0208 ,  F16B5/0266 ,  B64D7/02 ,  B64D29/00 ,  B64D29/02

Abstract: An assembly of a pylon and of a nacelle of an aircraft, wherein the nacelle has a structure, a visor, two centering systems and two tensioning systems. Each tensioning system comprises a first fitting, which is attached to the structure and has an engagement wall through which an orifice passes, a second fitting, which is attached to the visor, a threaded rod that is articulated on the second fitting and passes through the orifice, a spring element fitted on the threaded rod against the opposite face of the engagement wall from the second fitting, and an arresting means that blocks the spring element. Each centering system comprises a first fitting, which is attached to the structure and has a bore, and a second fitting, which is attached to the visor and bears a shaft that is accommodated in the bore.