公开(公告)号：US20190383172A1

公开(公告)日：2019-12-19

申请号：US16424650

申请日：2019-05-29

Applicant: Airbus Operations SAS

Inventor： Thierry GACHES ,  Lionel CZAPLA ,  Bastian SABATHIER

IPC: F01D25/26 ,  B64D33/04 ,  F01D25/30

Abstract: A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.

公开(公告)号：US20220136459A1

公开(公告)日：2022-05-05

申请号：US17516251

申请日：2021-11-01

Applicant: Airbus Operations SAS

Inventor： Fabien MENOU ,  Laurent CAZEAUX ,  Thierry GACHES

IPC: F02K3/02

Abstract: A turbofan engine having a duct for a bypass flow and blades. Each blade is mobile between a stowed position and a deployed position. Each blade includes a rigid core a second, free end, and a sheath into which the core and the second end slide. Each sheath includes a first part which surrounds at least one part of the core and the second end, and an aileron which extends beyond the core facing the first part of the adjacent blade. The sheath is made of a flexible material such that the bypass flow causes the sheath to come into contact with the first part of the adjacent blade. A turbofan engine of this kind makes it possible to create blades whose production costs are low but whose aerodynamic behavior is effective.

公开(公告)号：US20220106927A1

公开(公告)日：2022-04-07

申请号：US17488725

申请日：2021-09-29

Applicant: Airbus Operations SAS

Inventor： Corentin VILHES ,  Simon VANDERBAUWEDE ,  Thierry GACHES ,  Laurent CAZEAUX ,  Pascal GARDES ,  Guillaume SEGUIN

IPC: F02K7/08 ,  F04D29/52

Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

公开(公告)号：US20200072161A1

公开(公告)日：2020-03-05

申请号：US16552079

申请日：2019-08-27

Applicant: Airbus Operations SAS

Inventor： Eric BOUCHET ,  Laurent CAZEAUX ,  Thierry GACHES ,  Morad KASSEM ,  Claire MAFFRE

IPC: F02K1/82 ,  F02C7/24

Abstract: A structure which absorbs low-frequency sound comprising a perforated skin, a box having two lateral walls in the shape of a strip, that delimit between them an opening, and a bottom opposite the opening connecting the two lateral walls, the lateral walls becoming closer together with increasing distance from the opening to the bottom. The box is attached to the skin at the opening. Each lateral wall extends width-wise between the opening and the bottom. Each box has two tongues, each tongue being strip shaped, extending lengthwise over an entire box length, and width-wise between the opening and the bottom of the box. Each tongue has a first end attached along an edge of the opening and a second, free end which extends towards the bottom, becoming closer to the second end of the other tongue, where each tongue has an arcuate shape along its length.