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1.发明申请公开(公告)号：US20170174353A1
公开(公告)日：2017-06-22
申请号：US15453308
申请日：2017-03-08
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe Joret , Emmanuel LESTEVEN , Vincent PEYRON , Patrick BOILEAU
CPC classification number: B64D29/06 , B64D27/16 , F02K1/763 , F05D2220/323 , F05D2230/72 , F05D2250/11 , F05D2260/57
Abstract: A propulsion unit for an aircraft is provided. The propulsion unit includes a stationary unit having at least one cowl pivotally mounted on an axis collinear with a longitudinal axis of the propulsion unit between an operating position or a maintenance position allowing access to the turbojet engine for regular maintenance operations and irregular maintenance operations. The maintenance position for irregular maintenance operations includes an opening angle of the cowl that is greater than the opening angle of the cowl to carry out regular maintenance operations. The propulsion unit further includes at least one cylinder and at least one safety connecting rod secured to the cowl and stationary unit.
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公开(公告)号：US20220025816A1
公开(公告)日：2022-01-27
申请号：US17492783
申请日：2021-10-04
Applicant: Safran Nacelles
Inventor： Julien CORBIN , David PEREIRA , Vincent PEYRON , Jean-Nicolas BOUCHOUT , Caroline DANG , Nicolas CHOUQUET
Abstract: A cooling system for cooling an aircraft turbojet engine includes a first heat-exchanger for exchanging heat between a heat-transfer fluid and a lubricant of the turbojet engine, a second heat-exchanger for exchanging heat between the heat-transfer fluid and air, and a circulation duct for circulating heat-transfer fluid in a closed circuit. The cooling system further includes at least one regulating device for regulating the heat drawn from the lubricant, controlled by a control module of the regulating device that is configured to receive information according to the various flight phases.
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公开(公告)号：US20200318546A1
公开(公告)日：2020-10-08
申请号：US16839123
申请日：2020-04-03
Applicant: Safran Nacelles
Inventor： Vincent PEYRON , Nicolas BOUCHOUT
Abstract: A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.
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公开(公告)号：US20220186684A1
公开(公告)日：2022-06-16
申请号：US17685649
申请日：2022-03-03
Applicant: Safran Nacelles
Inventor： Vincent PEYRON
Abstract: A thrust reverser includes a diverter configured to divert at least a portion of an air flow from a nacelle and a cowl movable relative to an outer fixed structure of the thrust reverser. The thrust reverser further includes at least one rotatably hinged flap. The cowl configured to move from a closure position in which it provides aerodynamic continuity of the nacelle with the flap and covers the diverter. The flap is movable from a retracted position to an opening position in which it opens a passage in the nacelle and uncovers the diverter. The flap obstructs a portion of an annular channel of the nacelle when in the opening position. The thrust reverser also includes a cable-pulley system for driving the flap. The cable-pulley system includes at least one cable associated with at least one pulley to connect the flap to the thrust reverser.
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Patent Agency Ranking
公开(公告)号：US20180079517A1
公开(公告)日：2018-03-22
申请号：US15829131
申请日：2017-12-01
Applicant: Safran Nacelles
Inventor： Vincent PEYRON , Serge BUNEL , Pascal SOULIER , Arnaud BONNY
CPC classification number: B64D29/06 , B64C7/02 , B64D29/00 , E05B65/06 , E05C1/00 , E05C7/04 , F02K1/64
Abstract: The present disclosure provides a device for locking a first cowling and a second cowling of a thrust reverser of an aircraft propulsion assembly. The cowlings are mounted such that each cowl pivots around a longitudinal axis between a closed flight position and an open maintenance position. The locking device includes a telescopic connecting rod having at least one sliding shaft, a locking mechanism on a proximal end of a shaft on the second cowling, and a connecting rod support. The connecting rod support or the tubular element includes two walls each delimiting a hole, and the tubular element of the connecting rod or the connecting rod support has two support fingers which each extend longitudinally on a side of the tubular element into a hole. The holes engage with the support fingers when the cowlings are open and allow free movement of the support fingers in a closed-cowlings configuration.
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公开(公告)号：US20220023931A1
公开(公告)日：2022-01-27
申请号：US17492790
申请日：2021-10-04
Applicant: Safran Nacelles
Inventor： Vincent PEYRON , Jean-Nicolas BOUCHOUT , Flavie HUBERT-CHOINARD , Alexandra DUGARDIN
IPC: B21D53/04
Abstract: A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.
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公开(公告)号：US20200317358A1
公开(公告)日：2020-10-08
申请号：US16839145
申请日：2020-04-03
Applicant: Safran Nacelles
Inventor： Vincent PEYRON , Nicolas BOUCHOUT
Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).
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8.发明申请公开(公告)号：US20200277916A1
公开(公告)日：2020-09-03
申请号：US16876704
申请日：2020-05-18
Applicant: Safran Nacelles
Inventor： Pierre CARUEL , Vincent PEYRON
Abstract: An aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser includes cascades of mobile deflection vanes connected to cascade rails with a slideway connection that allows the cascades of vanes a translational movement between a cruising-flight position and a reverse-thrust position. The thrust reverser allows the cascade rails to be positioned in a forward position, in which the engine, the cascade rails and the deflection vanes can be removed from the propulsion assembly without the cascade rails colliding with the mobile cowl of the reverser. Dismantling and assembly or reassembly methods allow maintenance operations to be carried out on the engine thus dismantled.
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公开(公告)号：US20190153947A1
公开(公告)日：2019-05-23
申请号：US16253352
申请日：2019-01-22
Applicant: Safran Nacelles
Inventor： Vincent PEYRON , Patrick GONIDEC , Nicolas BOUCHOUT
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.
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