公开(公告)号：US10100780B2

公开(公告)日：2018-10-16

申请号：US15364623

申请日：2016-11-30

Applicant: SAFRAN NACELLES

Inventor： Sarah Tissot ,  Xavier Bouteiller ,  Olivier Kerbler ,  Patrick Gonidec

IPC: F02K1/72 ,  F02K1/09 ,  F02K1/12 ,  F02K3/04 ,  F02K3/06

Abstract: The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.

公开(公告)号：US12044193B2

公开(公告)日：2024-07-23

申请号：US17790684

申请日：2020-12-18

Applicant: SAFRAN NACELLES

Inventor： Sebastien Laurent Marie Pascal ,  Patrick Gonidec ,  Alexandre Phi ,  Paul Ferrey

IPC: F02K1/60 ,  F02K1/70

CPC classification number: F02K1/60 ,  F02K1/70 ,  F05D2220/323 ,  F05D2300/601

Abstract: A thrust reverser including doors and at least one flexible deflector obstructing a lateral opening of the thrust reverser when the doors are open. Such a deflector allows better controlling the airflows in thrust reverser configuration and maximizing the counter-thrust force.

公开(公告)号：US10266162B2

公开(公告)日：2019-04-23

申请号：US16010868

申请日：2018-06-18

Applicant: Safran Nacelles ,  Safran Landing Systems

Inventor： Patrick Gonidec ,  Hakim Maalioune ,  François Taillard ,  Denis Jontef ,  Marie-Laure De-Crescenzo ,  Jean-François Hammann

IPC: B60T8/17 ,  B64C25/42 ,  F02K1/76 ,  B60T8/171 ,  B60T8/1761

Abstract: The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.

公开(公告)号：US09995246B2

公开(公告)日：2018-06-12

申请号：US15371281

申请日：2016-12-07

Applicant: SAFRAN NACELLES

Inventor： Patrick Gonidec ,  Olivier Kerbler ,  Corentin Hue ,  Patrick Boileau

IPC: F02K1/72 ,  F02K1/12 ,  F02K1/76

CPC classification number: F02K1/72 ,  F02K1/1261 ,  F02K1/763 ,  Y02T50/671

Abstract: A thrust reverser for a nacelle of an aircraft turbojet engine includes at least one movable thrust reverser cowl, a means for locking the cowl, a variable section outlet nozzle, and at least one actuator including an actuator rod. The thrust reverser is provided with a resilient coupler comprising a body which is rigidly connected to the thrust reverser cowl and a resilient return and abutment device that engages with the actuating rod of the actuator such as to resiliently return the nozzle to a neutral position. The return device is calibrated such that, when the cowl is unlocked, the return device opposes the relative movement of the actuating rod relative to the cowl, such as to enable the movement of the cowl and the nozzle, and when the cover is locked, the actuator drives the actuating rod against the return device to enable the movement of the nozzle.

公开(公告)号：US12163487B2

公开(公告)日：2024-12-10

申请号：US17271910

申请日：2019-08-15

Applicant: Safran Nacelles Limited

Inventor： James Marquis ,  Patrick Gonidec ,  Stuart Hardyman ,  Loic Chapelain

IPC: F02K1/80 ,  B64D29/08 ,  B64F5/60 ,  F01D17/02 ,  F01D21/00 ,  F02K1/72 ,  F02K1/76 ,  H01R35/04 ,  H02G11/00 ,  H02G11/02

Abstract: A structure comprising a nacelle or a thrust reverser, the structure comprising a stationary part and a movable part, the structure comprising: a first guide provided on or in the stationary part of the structure or the movable part of the structure; a first electrical connector attached to the stationary part of the structure: a second electrical connector attached to the movable part of the structure; and a carriage movable along the first guide: wherein the carriage comprises a closed loop electrical cable mounted in or on a carriage body such that the closed loop cable can rotate, wherein the first electrical connector is electrically connected to the closed loop electrical cable and the closed loop electrical cable is electrically connected to the second electrical connector, thereby providing an electrical connection from the stationary part of the structure to the movable part of the structure.

公开(公告)号：US12077309B2

公开(公告)日：2024-09-03

申请号：US18571073

申请日：2022-06-10

Applicant: SAFRAN NACELLES

Inventor： Patrick Gonidec ,  Albin Lafont ,  Virginie Emmanuelle Anne-Marie Digeos ,  Stuart Hardyman

IPC: B64D33/02 ,  F02C7/045 ,  G10K11/168

CPC classification number: B64D33/02 ,  F02C7/045 ,  B64D2033/0206 ,  F05D2220/323 ,  F05D2250/283 ,  F05D2260/96 ,  G10K11/168

Abstract: An acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit in contact with a fluidic flow, the panel including a first, acoustically reflective skin, a second, acoustically porous skin intended to be in contact with the fluidic flow, and a honeycomb structure extending between the first skin and the second skin and having a plurality of cavities. The panel includes at least one acoustically transparent reinforcing wall passing through a plurality of cavities of the honeycomb structure and extending from the second skin to the first skin, forming a non-orthogonal angle with the first and second skins.

公开(公告)号：US20220348314A1

公开(公告)日：2022-11-03

申请号：US17725453

申请日：2022-04-20

Applicant: SAFRAN NACELLES

Inventor： Patrick Gonidec ,  Loïc Chapelain ,  Xavier Carcenac ,  Vincent Lefeuvre

IPC: B64C17/00 ,  B64C11/00

Abstract: A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising: A standby protection device comprising a first connecting member fixedly mounted to the mast and a second connecting member fixedly mounted to the propulsion device, the second connecting member being rotatably hinged with respect to the first connecting member in at least one degree of freedom, and at least one retaining member keeping the second connecting member fixed with respect to the first connecting member, and configured, in the presence of a predetermined unbalance force on the propeller, to release the standby protection device in order to protect the mast.

公开(公告)号：US11268443B2

公开(公告)日：2022-03-08

申请号：US16253352

申请日：2019-01-22

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Patrick Gonidec ,  Jean-Nicolas Bouchout

IPC: F02C7/14 ,  F02C7/16 ,  F02K3/115 ,  B64D33/10 ,  F02C7/00 ,  B64D29/06 ,  B64D33/08 ,  F02K3/06

Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.