公开(公告)号：US20200377221A1

公开(公告)日：2020-12-03

申请号：US16998893

申请日：2020-08-20

Applicant: Safran Nacelles ,  Safran Aircraft Engines

Inventor： Patrick BOILEAU ,  Bruno BEUTIN

IPC: B64D29/06 ,  F02K1/70 ,  F02K1/76 ,  B64D27/26

Abstract: A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.

公开(公告)号：US20170321634A1

公开(公告)日：2017-11-09

申请号：US15654087

申请日：2017-07-19

Applicant: SAFRAN NACELLES

Inventor： Patrick BOILEAU

IPC: F02K1/72 ,  B64D29/06 ,  B64D27/16 ,  F02K1/76

CPC classification number: F02K1/72 ,  B64D27/10 ,  B64D27/16 ,  B64D29/06 ,  F02C7/20 ,  F02K1/763 ,  F05D2220/323 ,  F05D2260/50

Abstract: The present disclosure provides a rear nacelle assembly for a turbojet having at least one thrust reversal device to redirect air circulating from upstream to downstream in a flow path of a turbojet and a mast that connects the nacelle to a structure of an aircraft. In one form, the thrust reverser device includes a cradle having a first longeron and a second longeron extending longitudinally opposite sides of the mast. The first and second longeron each include a device for slideably guiding the cowl and the cascade. In another form, a rear portion and a front portion of the cradle connects to the mast by a rear connecting device and front connecting device, respectively, such that the cradle is adapted to follow the movements of the turbojet.

公开(公告)号：US20170089297A1

公开(公告)日：2017-03-30

申请号：US15377257

申请日：2016-12-13

Applicant: SAFRAN NACELLES

Inventor： Patrick BOILEAU

IPC: F02K1/62 ,  F01D25/24

CPC classification number: F02K1/625 ,  F01D25/24 ,  F02K1/72 ,  F05D2220/323 ,  Y02T50/671

Abstract: The disclosure relates to a turbofan nacelle including a thrust reverser, the thrust reverser including a movable cover moving back from a closed position in which the thrust is not reversed to an open position for uncovering cascades that reverse the direction of the flow of cold air which is diverted from the annular stream of secondary air, the movable cover including a radially outer portion intended for being adjacent to a leading edge of a wing of an aircraft. The movable cover includes on the radially outer portion at least one cut-out intended for avoiding interference with a movable slat of the leading edge of the wing of the aircraft, as well as a panel for closing the cut-out, the closing panel including a stationary portion at least partially covered by an upstream portion of the movable cover when the movable cover is in the open position.

公开(公告)号：US20210179393A1

公开(公告)日：2021-06-17

申请号：US17188520

申请日：2021-03-01

Applicant: Safran Nacelles

Inventor： Patrick BOILEAU

IPC: B66C1/10 ,  B64D33/02 ,  B64F5/50 ,  B64D29/06

Abstract: A handling assembly of a propulsion assembly includes a nacelle and an aircraft turbojet engine. The handling assembly also includes a handling envelope covering at least half of the circumference of an outer wall of an air inlet of the nacelle, when the propulsion assembly is mounted on said handling assembly, and at least two interfaces for attaching slings, the slings being connected to a hoisting system which is external to said handling assembly. A method for handling a propulsion assembly is also disclosed.

公开(公告)号：US20200369401A1

公开(公告)日：2020-11-26

申请号：US16991636

申请日：2020-08-12

Applicant: Safran Nacelles

Inventor： Virginie Emmanuelle Anne Marie DIGEOS ,  Patrick BOILEAU

IPC: B64D33/02 ,  B64D15/04

Abstract: A defrosting and acoustic treatment device for an air intake lip of a turbojet engine nacelle includes an embossed acoustic structure that delimits a plurality of acoustic cells, each acoustic cell being delimited by an independent peripheral wall that allows a flow of de-icing air to flow around each acoustic cell.

公开(公告)号：US20200325850A1

公开(公告)日：2020-10-15

申请号：US16907900

申请日：2020-06-22

Applicant: Safran Nacelles

Inventor： Patrick BOILEAU ,  Pierre CARUEL

IPC: F02K1/72 ,  B64D29/06 ,  B64D29/08 ,  B64D27/16

Abstract: A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.

公开(公告)号：US20200317356A1

公开(公告)日：2020-10-08

申请号：US16907944

申请日：2020-06-22

Applicant: Safran Nacelles

Inventor： Patrick BOILEAU

IPC: B64D29/06 ,  F02K3/06

Abstract: A propulsion unit for an aircraft includes a nacelle, a turbojet engine, an annular flow path for circulating a secondary air flow, and a precooler device communicating with a motor enclosure and including a scoop opening into the annular flow path. The propulsion unit includes a compressed air supply circuit arranged in the propulsion unit for injecting a flow of compressed air into the scoop of the precooler device. A method for ventilating a motor enclosure of a propulsion unit includes injecting compressed air into a scoop of the precooler device when the turbojet engine is stopped.

公开(公告)号：US20190193865A1

公开(公告)日：2019-06-27

申请号：US16288286

申请日：2019-02-28

Applicant: Safran Nacelles

Inventor： Patrick BOILEAU

IPC: B64D29/06 ,  B64D29/08

CPC classification number: B64D29/06 ,  B64D29/08

Abstract: The present disclosure relates to a nacelle for an aircraft turbojet engine that includes an air inlet having a leading edge of the nacelle extending forward by an inner wall and an outer wall of the air inlet and a fan cowling defining, in a closed position, aerodynamic continuity with the outer wall of the nacelle, intended for surrounding a turbojet engine fan cowling. The air inlet is designed to define at least one portion of the fan cowling. The present disclosure also relates to a propulsion assembly that includes a nacelle surrounding a turbojet engine.

公开(公告)号：US20170328305A1

公开(公告)日：2017-11-16

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 ,  F02K1/76 ,  F02K1/12

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：US20170321633A1

公开(公告)日：2017-11-09

申请号：US15654030

申请日：2017-07-19

Applicant: SAFRAN NACELLES

Inventor： Patrick BOILEAU ,  Olivier KERBLER ,  Julien LEZERAC ,  Armel GAUTIER ,  Loïc GRALL ,  Ludovic TOUPET

IPC: F02K1/72 ,  F01D25/24 ,  B64D27/16 ,  F02C7/20 ,  B64D29/06

CPC classification number: F02K1/72 ,  B64D27/16 ,  B64D27/26 ,  B64D29/06 ,  B64D2027/264 ,  F01D25/24 ,  F02C7/20 ,  F05D2220/323 ,  F05D2260/50

Abstract: The present disclosure provides a nacelle rear assembly for turbojet engine including at least one thrust reverser device to redirect air flow circulating from upstream to downstream in a flow path of the turbojet engine and a mast to link the nacelle to a structure of the aircraft. In one form, the nacelle extends longitudinally from forth to back along an axis and includes a cradle fastened on the mast. In one form, the cradle includes a first longeron and a second longeron extending longitudinally on either side of the mast. The first and second longeron each include a sliding guide device for sliding of a movable cowl and of a cascade of the thrust reverser device.