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61.发明申请公开(公告)号：US20190314963A1
公开(公告)日：2019-10-17
申请号：US16456165
申请日：2019-06-28
申请人： Safran Nacelles
IPC分类号： B25B23/14
摘要： A screwdriving end fitting for a screwdriving tool for tightening a self-breaking fastener, such as a self-breaking nut or screw, includes a screwdriving socket and a retention module. The self-breaking fastener includes a threaded portion linked to a screwdriving head via a breaking area. The screwdriving socket of the screwdriving end fitting is capable of cooperating with the self-breaking fastener in order to drive it in rotation, and the retention module retains a broken portion of the self-breaking fastener in the screwdriving socket after the fastener has broken. The retention module includes at least one retainer movable between a locked position in which the retainer inhibits the broken portion of the self-breaking fastener from exiting the screwdriving socket and an unlocked position in which the retainer allows this exit.
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公开(公告)号：US20190202574A1
公开(公告)日：2019-07-04
申请号：US16222266
申请日：2018-12-17
申请人： SAFRAN NACELLES
发明人： Alexis LONCLE
摘要： A nacelle for an aircraft turbojet engine includes a fixed internal structure intended to receive an aircraft turbojet engine and an external structure. The fixed internal structure and external structure defines a flow channel for a secondary air flow. A set of lower and upper beams are linked together by the fixed internal structure. An external wall of the lower beam is designed to partially define an external aerodynamic surface of the nacelle, intended to come into contact with an outer air flow. The external wall of the lower beam is further designed to tolerate the damage caused by the outer air flow.
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公开(公告)号：US20190118978A1
公开(公告)日：2019-04-25
申请号：US16309340
申请日：2017-06-12
摘要： A monitoring system for monitoring a piece of aircraft equipment, the system comprising a master electronic module and a slave electronic module, each fitted with first wireless communication means, the slave electronic module further comprising measurement means for the purpose of taking measurements of a parameter of the aircraft equipment, and power supply means making the slave electronic module independent in terms of energy, the master electronic module further comprising detector means adapted to detect a stage of flight in which the aircraft is to be found, and control means for acting via the first wireless communication means to control the measurement means of the slave electronic module so as to adapt the measurements taken by the measurement means to the detected stage of flight.
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公开(公告)号：US20190040816A1
公开(公告)日：2019-02-07
申请号：US16074578
申请日：2017-02-03
摘要： An aircraft propulsion assembly including a bypass turbojet having a stationary inter-compressor casing positioned upstream from a space between passages, a nacelle including at its downstream end an inner wall that defines the outside of the space between passages and the inside of the bypass stream flow passage, and an outer wall arranged around the inner wall and that defines the outside of the bypass stream flow passage, at least a portion of the inner wall being suitable for moving between a maintenance position and a working position, and a thrust-reverser including a downstream element of the outer wall that is movable in translation between a retracted position and a thrust-reversal position in which it allows bypass stream deflector elements to be deployed in a radial direction, the deployment of the stream deflector elements being controlled by guide rods.
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公开(公告)号：US20190039265A1
公开(公告)日：2019-02-07
申请号：US16155417
申请日：2018-10-09
申请人： Safran Nacelles
摘要： The present disclosure relates to a preform that includes layers of textile reinforcements that are arranged in a mold by an automatic placement head and are connected to each other, and which can be dry or pre-impregnated, in order to form a part made of composite materials after curing of an impregnating resin. The part includes a folding produced by conformation of the preform after the placement of the layers of textile reinforcements. At the folding, there are spacings between at least some of the layers of textile reinforcements.
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公开(公告)号：US09995699B2
公开(公告)日：2018-06-12
申请号：US15589049
申请日：2017-05-08
申请人： SAFRAN NACELLES
CPC分类号： G01N25/02 , B64F5/60 , G01N25/4866
摘要： The present disclosure relates to a method of characterizing the thermal ageing of a part made of composite material, in particular a composite material having an organic matrix. The method includes taking from the part a sample of composite material, subjecting the sample to modulated temperature differential calorimetry, determining, from the curve representing the total heat flow component associated with irreversible phenomena, the temperature at which a local extremum appears, this local extremum being characteristic of the thermal ageing, and determining the thermal ageing of the composite material by comparing the temperature at which the local extremum appears with a reference chart.
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公开(公告)号：US20180079517A1
公开(公告)日：2018-03-22
申请号：US15829131
申请日：2017-12-01
申请人： Safran Nacelles
发明人： Vincent PEYRON , Serge BUNEL , Pascal SOULIER , Arnaud BONNY
摘要： 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：US09915269B2
公开(公告)日：2018-03-13
申请号：US14161595
申请日：2014-01-22
申请人： AIRCELLE
发明人： Romain Billault
CPC分类号： F04D29/403 , F01D25/243 , F02K1/80
摘要： A device for connecting a front frame of a turbojet engine nacelle to a fan casing includes a locking pin connected to a first assembly flange and a retaining flange that is movably mounted and has at least one opening. In particular, the locking pin has a shank passing through an orifice of a second assembly flange secured to the fan casing. The opening is crossed through by the shank of the locking pin and interacts with an end groove of said locking pin. When the retaining flange is in the unlocking position, the opening has dimensions larger than those of the shank of the locking pin, and when the retaining flange is in the locking position, the opening has dimensions larger than a thickness of the locking pin at its groove but smaller than an overall thickness of the shank of the orifice of the second flange.
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公开(公告)号：US09856826B2
公开(公告)日：2018-01-02
申请号：US15654087
申请日：2017-07-19
申请人： SAFRAN NACELLES
发明人： Patrick Boileau
CPC分类号： F02K1/72 , B64D27/10 , B64D27/16 , B64D29/06 , F02C7/20 , F02K1/763 , F05D2220/323 , F05D2260/50
摘要： 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.
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公开(公告)号：US20170321634A1
公开(公告)日：2017-11-09
申请号：US15654087
申请日：2017-07-19
申请人： SAFRAN NACELLES
发明人： Patrick BOILEAU
CPC分类号： F02K1/72 , B64D27/10 , B64D27/16 , B64D29/06 , F02C7/20 , F02K1/763 , F05D2220/323 , F05D2260/50
摘要： 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.
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