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公开(公告)号：US12085042B2
公开(公告)日：2024-09-10
申请号：US17666244
申请日：2022-02-07
申请人： Safran Nacelles
摘要： A position sensor for an aircraft nacelle thrust reverser door for an aircraft turbojet engine includes a target to be detected, a detector having a detection range and including a detection head configured to detect the target when it enters its detection range, and a target guide configured to guide the target in order to position it in the detection range of the detector. The detector is stationary relative to the target guide. In one form, the target is intended to be positioned on the door, and the detector and the target guide are intended to be positioned on a stationary structure of the thrust reverser. In another form, the target is intended to be positioned on a stationary structure of the thrust reverser, and the detector and the target guide are intended to be positioned on the door.
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2.发明公开公开(公告)号：US20230249805A1
公开(公告)日：2023-08-10
申请号：US18165253
申请日：2023-02-06
申请人： SAFRAN NACELLES
IPC分类号： B64C21/01
CPC分类号： B64C21/01
摘要： An aircraft having an airframe with several airframe elements and at least one fluidic propulsion device with a peripheral nozzle defining an internal cavity in which an external airflow circulates, the peripheral nozzle having openings configured to inject a plurality of high-speed airflows into the internal cavity so as to accelerate the external airflow in an upstream to downstream manner. A portion of the peripheral nozzle can be integrated into an airframe element so as to enable acceleration of an external airflow circulating from upstream to downstream on said airframe element so as to improve its re-adhesion to said airframe element.
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公开(公告)号：US20220267019A1
公开(公告)日：2022-08-25
申请号：US17630869
申请日：2020-08-11
申请人： SAFRAN NACELLES
IPC分类号： B64D33/02
摘要： Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.
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4.发明授权公开(公告)号：US11913403B2
公开(公告)日：2024-02-27
申请号：US17758037
申请日：2020-12-18
申请人： SAFRAN NACELLES
摘要： A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.
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公开(公告)号：US20230184193A1
公开(公告)日：2023-06-15
申请号：US18065875
申请日：2022-12-14
申请人： SAFRAN NACELLES
CPC分类号： F02K1/62 , F02K1/58 , F05D2220/323
摘要： A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.
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公开(公告)号：US11624339B2
公开(公告)日：2023-04-11
申请号：US16421519
申请日：2019-05-24
申请人： Safran Nacelles
摘要： An aircraft turbojet engine nacelle includes a rear section without a lower bifurcation, the rear section including a thrust reverser system, and the thrust reverser system including a movable cowl. The nacelle includes a guide system including a movable portion and a fixed portion, the movable portion being secured in translation to the movable cowl and cooperating with the fixed portion and the fixed portion being fixed relative to the nacelle. The guide system is disposed proximate to a position called the “6 O'clock” position. In one form, the length of the fixed portion of the guide system is larger than or equal to 50% of the length of the movable portion.
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公开(公告)号：US11866178B2
公开(公告)日：2024-01-09
申请号：US17630869
申请日：2020-08-11
申请人： SAFRAN NACELLES
CPC分类号： B64D15/04 , B64D33/02 , B64D2033/0233 , B64D2033/0286
摘要： Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.
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公开(公告)号：US11692480B2
公开(公告)日：2023-07-04
申请号：US16552516
申请日：2019-08-27
申请人： Safran Nacelles
CPC分类号： F02C7/05 , F02C7/18 , B60H1/30 , B64D33/08 , F05D2230/53
摘要： An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.
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公开(公告)号：US20230029052A1
公开(公告)日：2023-01-26
申请号：US17862806
申请日：2022-07-12
申请人： SAFRAN NACELLES
摘要： A connecting rod for a nacelle of a turbine engine is described. The connecting rod includes a region configured to move the center of aerodynamic forces able to be exerted on the connecting rod, in the direction of an air flow intended to be generated during a thrust generated by the turbine engine.
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