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公开(公告)号：US20240294265A1
公开(公告)日：2024-09-05
申请号：US18258319
申请日：2021-12-21
申请人： SAFRAN NACELLES
发明人： Hazem Kioua , Thomas Marlay , Damien Lemoine , Ophélie Schmitter
CPC分类号： B64D33/02 , F01D17/00 , F05D2260/53
摘要： An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.
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公开(公告)号：US11572188B2
公开(公告)日：2023-02-07
申请号：US17408125
申请日：2021-08-20
申请人： SAFRAN NACELLES
发明人： Ophélie Schmitter , Hazem Kioua , Romain Gardel , Damien Lemoine
摘要： A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl, each fan cowl comprising a hinged end and a closing end, each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.
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公开(公告)号：US12044168B2
公开(公告)日：2024-07-23
申请号：US18247852
申请日：2021-10-01
申请人： SAFRAN NACELLES
摘要： Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.
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公开(公告)号：US12037940B2
公开(公告)日：2024-07-16
申请号：US18247037
申请日：2021-10-01
申请人： SAFRAN NACELLES
CPC分类号： F02C7/047 , F05D2220/80
摘要： A supersonic air intake of an aircraft propulsion assembly comprises: •⋅ pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •⋅ a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •⋅ at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •⋅ at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.
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5.发明公开公开(公告)号：US20240018902A1
公开(公告)日：2024-01-18
申请号：US18247037
申请日：2021-10-01
申请人： SAFRAN NACELLES
IPC分类号： F02C7/047
CPC分类号： F02C7/047 , F05D2220/80
摘要： A supersonic air intake of an aircraft propulsion assembly comprises: a pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, a speed reducer fixedly mounted inside the pipe along the longitudinal axis, at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.
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公开(公告)号：US12037941B2
公开(公告)日：2024-07-16
申请号：US18247052
申请日：2021-10-01
申请人： SAFRAN NACELLES
CPC分类号： F02C7/047 , B64D33/02 , B64D2033/0233 , B64D2033/026 , F05D2220/80
摘要： Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.
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公开(公告)号：US20230417182A1
公开(公告)日：2023-12-28
申请号：US18247852
申请日：2021-10-01
申请人： SAFRAN NACELLES
摘要： Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.
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公开(公告)号：US20220055760A1
公开(公告)日：2022-02-24
申请号：US17408125
申请日：2021-08-20
申请人： SAFRAN NACELLES
发明人： Ophélie Schmitter , Hazem Kioua , Romain Gardel , Damien Lemoine
摘要： A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl , each fan cowl comprising a hinged end and a closing end , each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.
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公开(公告)号：US12110120B2
公开(公告)日：2024-10-08
申请号：US18255025
申请日：2021-12-01
申请人： SAFRAN NACELLES
CPC分类号： B64D27/40 , B64D29/06 , B64D29/08 , F01D25/243 , F01D25/28 , F02C7/00 , F02C7/04 , F02C7/20 , F05D2220/323
摘要： A propulsion unit for an aircraft includes a gas generator; an air inlet; and a sealing system inserted axially between the air inlet and the gas generator. The sealing system has at least: a compression ring with a first axial end configured for mechanical connection to one of the gas generator and the air inlet. The compression ring also has a second opposite axial end configured to be axially separated from the other of the gas generator and the air inlet by an annular space. An annular seal is mounted in the space and configured to be axially compressed by reduction of the axial dimension of said space.
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10.发明公开公开(公告)号：US20240018903A1
公开(公告)日：2024-01-18
申请号：US18247052
申请日：2021-10-01
申请人： SAFRAN NACELLES
CPC分类号： F02C7/047 , B64D33/02 , B64D2033/0233 , B64D2033/026 , F05D2220/80
摘要： Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.
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