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公开(公告)号：US11542026B2
公开(公告)日：2023-01-03
申请号：US16907944
申请日：2020-06-22
Applicant: Safran Nacelles
Inventor： Patrick Boileau
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.
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公开(公告)号：US11186379B2
公开(公告)日：2021-11-30
申请号：US15653971
申请日：2017-07-19
Applicant: SAFRAN NACELLES
Inventor： Patrick Boileau , Olivier Kerbler , Julien Lezerac , Aurélien Gonzalez , Loïc Grall , Ludovic Toupet
Abstract: The present disclosure concerns a system for installing and removing a propulsion unit on a pylon of an aircraft, a propulsion unit of the type including a nacelle and a turbojet engine, the turbojet engine being linked on the pylon by at least one front suspension and one rear suspension. The system includes a supporting structure which is adapted to support a thrust reverser device, a front suspension of the turbojet engine, which carries a front part of the supporting structure, and which is removably fastened on a front part of the pylon, and a rear suspension of the turbojet engine which carries a rear part of the supporting structure, and which is removably fastened on a rear part of the pylon, and the disengagement of said suspensions of the pylon allowing removing the propulsion unit mounted on the pylon.
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公开(公告)号：US11840352B2
公开(公告)日：2023-12-12
申请号：US17510643
申请日：2021-10-26
Applicant: Safran Nacelles
Inventor： Gina Ferrier , Patrick Boileau , Pierre Caruel
CPC classification number: B64D33/02 , B64D29/06 , F02C7/04 , B64D2033/0206 , B64D2033/0273 , B64D2033/0286 , F05D2230/60
Abstract: An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.
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4.发明授权公开(公告)号：US11512641B2
公开(公告)日：2022-11-29
申请号：US17238602
申请日：2021-04-23
Applicant: Safran Nacelles
Inventor： Patrick Boileau
Abstract: A nacelle for use in an aircraft having a turbojet engine (the turbojet engine including a fan casing and a suspension pylon) includes a D-shaped structure downstream section embedding a thrust reverser device. The D-shaped structure downstream section includes a movable cascades vane. The D-shaped structure downstream section also includes two D-shaped half-structures each having an outer half-cowl movable in translation along a longitudinal axis, a connector between the cascades vane and the outer half-cowl, a twelve o'clock half-bifurcation, an inner half-structure defining an inner portion of the annular flow path, and a twelve o'clock half-beam mounted on the twelve o'clock half-bifurcation articulated on the pylon. The nacelle further includes an axial retention device of the downstream section of the nacelle, relative to the turbojet engine, configured to provide a connection defining an axial retention between the twelve o'clock half-beam and a fixed element of the fan casing.
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公开(公告)号：US11300076B2
公开(公告)日：2022-04-12
申请号：US16998720
申请日：2020-08-20
Applicant: Safran Nacelles , Safran Aircraft Engines
Inventor： Patrick Boileau , Quentin Garnaud , Antoine Elie Hellegouarch , Gina Ferrier
Abstract: A propulsion unit includes a nacelle, a turbojet engine, and a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the turbojet engine. The propulsion unit further includes actuators arranged around the annular duct and each actuator has a front end attached to the turbojet engine and a rear end which translates movable rear covers and gratings for opening, in the annular duct, radial passages which receive said gratings. The propulsion unit further has lifting points that are arranged around the annular duct for lifting the turbojet engine. At least one of the lifting points is formed on a beam for attaching an front end of an actuator.
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Patent Agency Ranking
公开(公告)号：US10689125B2
公开(公告)日：2020-06-23
申请号：US16288286
申请日：2019-02-28
Applicant: Safran Nacelles
Inventor： Patrick Boileau
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.
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公开(公告)号：US12103694B2
公开(公告)日：2024-10-01
申请号：US17510626
申请日：2021-10-26
Applicant: Safran Nacelles
Inventor： Gina Ferrier , Patrick Boileau
CPC classification number: B64D33/02 , B64D29/06 , F02C7/04 , B64D2033/0206 , B64D2033/0273 , B64D2033/0286 , F05D2230/60
Abstract: An air intake for a nacelle of an aircraft engine includes a substantially cylindrical outer wall, a substantially cylindrical inner wall, a front lip, a front mounting flange, and a support structure. The front lip connects the substantially cylindrical inner wall and the substantially cylindrical outer wall. The front mounting flange is configured to cooperate with a rear flange of a wall of the aircraft engine forming a fan casing. The support structure comprises a lower end configured to be secured to the fan casing, by the rear flange, and an upper end in contact at least with a downstream portion of the outer wall. The support structure includes access apertures configured to be crossed by maintenance tools during operations of maintenance of the air intake.
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8.发明授权公开(公告)号：US11834187B2
公开(公告)日：2023-12-05
申请号：US16998893
申请日：2020-08-20
Applicant: Safran Nacelles , Safran Aircraft Engines
Inventor： Patrick Boileau , Bruno Beutin
CPC classification number: B64D29/06 , B64D27/26 , B64F5/50 , F02K1/70 , F02K1/763 , B64D2027/262 , F05D2220/323 , F05D2260/02
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.
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公开(公告)号：US10458362B2
公开(公告)日：2019-10-29
申请号：US15377257
申请日：2016-12-13
Applicant: SAFRAN NACELLES
Inventor： Patrick Boileau
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.
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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
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.
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