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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
Applicant: SAFRAN NACELLES
Inventor： Ophélie Schmitter , Hazem Kioua , Romain Gardel , Damien Lemoine
Abstract: 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：US12246846B2
公开(公告)日：2025-03-11
申请号：US18251095
申请日：2021-11-02
Applicant: SAFRAN NACELLES
Inventor： Hazem Kioua , Damien Lemoine , Pierre-Alain Reboul , Matthieu Menielle
Abstract: A propulsion unit for an aircraft, includes a support structure, a nacelle and a turbomachine. The support structure is configured to independently support, on the one hand, the turbomachine and, on the other hand, preferably by a cradle, an air inlet and/or a rear section of the nacelle.
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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
Applicant: SAFRAN NACELLES
Inventor： Hazem Kioua , Thomas Marlay , Damien Lemoine , Ophélie Schmitter
CPC classification number: B64D33/02 , F01D17/00 , F05D2260/53
Abstract: 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：US12037941B2
公开(公告)日：2024-07-16
申请号：US18247052
申请日：2021-10-01
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe Joret , Damien Lemoine , Charles-Antoine Lampaert , Hazem Kioua
CPC classification number: F02C7/047 , B64D33/02 , B64D2033/0233 , B64D2033/026 , F05D2220/80
Abstract: 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
Applicant: SAFRAN NACELLES
Inventor： Hazem Kioua , Pierre Charles Caruel , Jean-Philippe Joret , Charles-Antoine Lampaert
Abstract: 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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Patent Agency Ranking
公开(公告)号：US20220055760A1
公开(公告)日：2022-02-24
申请号：US17408125
申请日：2021-08-20
Applicant: SAFRAN NACELLES
Inventor： Ophélie Schmitter , Hazem Kioua , Romain Gardel , Damien Lemoine
Abstract: 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：US12214893B2
公开(公告)日：2025-02-04
申请号：US18258319
申请日：2021-12-21
Applicant: SAFRAN NACELLES
Inventor： Hazem Kioua , Thomas Marlay , Damien Lemoine , Ophélie Schmitter
Abstract: 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：US12044168B2
公开(公告)日：2024-07-23
申请号：US18247852
申请日：2021-10-01
Applicant: SAFRAN NACELLES
Inventor： Hazem Kioua , Pierre Charles Caruel , Jean-Philippe Joret , Charles-Antoine Lampaert
Abstract: 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
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe Joret , Hazem Kioua , Emmanuel Lesteven
CPC classification number: F02C7/047 , F05D2220/80
Abstract: 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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10.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
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe Joret , Hazem Kioua , Emmanuel Lesteven
IPC: F02C7/047
CPC classification number: F02C7/047 , F05D2220/80
Abstract: 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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