公开(公告)号：US11981446B2

公开(公告)日：2024-05-14

申请号：US17878360

申请日：2022-08-01

Applicant: Airbus Operations SAS

Inventor： Umberto Gastaldi ,  Wolfgang Brochard ,  Olivier Pautis

IPC: B64D29/08 ,  B64D29/06

CPC classification number: B64D29/08 ,  B64D29/06

Abstract: An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

公开(公告)号：US11952135B2

公开(公告)日：2024-04-09

申请号：US17851407

申请日：2022-06-28

Applicant: Airbus Operations SAS

Inventor： Cédric Poupon ,  Olivier Pautis ,  Jonathan Blanc

IPC: B64D27/26 ,  F16C11/06

CPC classification number: B64D27/26 ,  F16C11/0628 ,  B64D2027/262

Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

公开(公告)号：US11780599B2

公开(公告)日：2023-10-10

申请号：US17694747

申请日：2022-03-15

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Jonathan Blanc

IPC: B64D29/02 ,  B64D27/26 ,  B64D29/08

CPC classification number: B64D29/02 ,  B64D27/26 ,  B64D29/08 ,  B64D2027/264

Abstract: An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.

公开(公告)号：US11215142B2

公开(公告)日：2022-01-04

申请号：US16714986

申请日：2019-12-16

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis

IPC: F02K1/72 ,  F02K1/08 ,  F02K1/76

Abstract: A bypass turbojet nacelle comprising a fixed structure, a fixed cowl and a cowl movable in translation between advanced and withdrawn positions by a ram with a reverser flap movable thereon, and a deployment system comprising a first slider integral with the movable cowl, a first groove comprising a first part and a curved, second part integral with the fixed structure, a second slider movable in translation in the second groove part, a first connecting rod rotatable on the first slider and on the second slider, and a second connecting rod articulated on both the first connecting rod first end and the reverser flap. The ram rod is articulated on the first connecting rod. Moving the first slider from the advanced to the withdrawn position moves the second slider along the first part and, when the first slider reaches the withdrawn position, the second slider moves along the second part.

公开(公告)号：US10556699B2

公开(公告)日：2020-02-11

申请号：US15496183

申请日：2017-04-25

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Jerome Colmagro ,  David Ewens

IPC: B64D27/14 ,  B64D27/20 ,  B64D27/26 ,  B64C11/30 ,  B64D27/12 ,  B64D27/00

Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.

公开(公告)号：US09919804B2

公开(公告)日：2018-03-20

申请号：US15008593

申请日：2016-01-28

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Rohan Nanda

IPC: B64D27/18 ,  B64D27/26

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/262 ,  B64D2027/268

Abstract: A propulsion assembly includes a turbojet incorporating a fan casing and a central casing around a longitudinal axis, a mounting pylon having a rigid structure, a forward engine attachment interposed between a forward extremity of the rigid structure and an upper part of the fan casing, the upper part being in a vertical median plane (P) passing through the longitudinal axis, an aft engine attachment interposed between a median zone of the rigid structure and an upper aft part of the central casing, and a device for absorbing the thrust forces generated by the turbojet, including two links placed either side of the median plane (P) and hinged, on one hand, forward, on a forward part of the central casing, and on the other, aft, directly on the rigid structure. Such an arrangement enables a reduction of the stresses, and the possibility of designing a simplified rigid structure.