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公开(公告)号：US11338930B2
公开(公告)日：2022-05-24
申请号：US16907346
申请日：2020-06-22
申请人： Safran Nacelles
发明人： Loïc Grall , Mélody Seriset , Alexis Heau , Benjamin Brebion , Olivier Kerbler
摘要： A nacelle of an aircraft turbofan engine including an air inlet upstream from the engine, a median section configured to surround a fan of the engine and delimited on the outside by a fan cowl supported by a fan housing to which it is attached at the upstream portion, a downstream section delimiting an annular flow path in which the air is configured to flow and housing thrust reversal devices, the thrust reversal approach including a movable cowl associated with at least one actuator for moving the movable cowl between a direct jet position, in which it provides the aerodynamic continuity of the nacelle and an indirect jet position in which it opens up a passage in the nacelle by uncovering cascade vanes arranged around this flow path that receive the cold air flow to return it towards the outside and forwards, the cascade vanes being attached to the movable cowl.
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公开(公告)号：US10883447B2
公开(公告)日：2021-01-05
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：US09995246B2
公开(公告)日：2018-06-12
申请号：US15371281
申请日：2016-12-07
申请人： SAFRAN NACELLES
CPC分类号： F02K1/72 , F02K1/1261 , F02K1/763 , Y02T50/671
摘要： A thrust reverser for a nacelle of an aircraft turbojet engine includes at least one movable thrust reverser cowl, a means for locking the cowl, a variable section outlet nozzle, and at least one actuator including an actuator rod. The thrust reverser is provided with a resilient coupler comprising a body which is rigidly connected to the thrust reverser cowl and a resilient return and abutment device that engages with the actuating rod of the actuator such as to resiliently return the nozzle to a neutral position. The return device is calibrated such that, when the cowl is unlocked, the return device opposes the relative movement of the actuating rod relative to the cowl, such as to enable the movement of the cowl and the nozzle, and when the cover is locked, the actuator drives the actuating rod against the return device to enable the movement of the nozzle.
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公开(公告)号：US11767808B2
公开(公告)日：2023-09-26
申请号：US16933179
申请日：2020-07-20
申请人： Safran Nacelles
发明人： Pierre Caruel , Loïc Grall , Alexis Heau , Olivier Kerbler , Mélody Seriset
CPC分类号： F02K1/72 , F02K1/763 , B64D29/06 , F02K3/06 , F05D2220/323 , F05D2240/129
摘要： A nacelle rear assembly of a nacelle of a turbojet engine of an aircraft extends along a longitudinal central axis (A) and includes a sliding cascade thrust reverser. The cascade thrust reverser includes at least one sliding cowl, a deflection cascade including a plurality of rows of vanes that each extend around the longitudinal central axis (A) and that are longitudinally arranged from a first front row of vanes up to a last rear row of vanes, each row of vanes including at least one deflection vane for deflecting the airflow toward the outside of the rear assembly of the nacelle, the deflection cascade being movably integral with the sliding cowl, wherein the deflection cascade includes at least one additional neutral row of vanes that is interposed between the last row of vanes and the sliding cowl and that includes at least one neutral vane.
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公开(公告)号：US11549462B2
公开(公告)日：2023-01-10
申请号：US16884948
申请日：2020-05-27
发明人： Sébastien Michel Thierry Guillemant , Pierre Caruel , Olivier Kerbler , Alexis Heau , Mathieu Lerouvreur , Antoine Elie Hellegouarch
摘要： A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.
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公开(公告)号：US11186379B2
公开(公告)日：2021-11-30
申请号：US15653971
申请日：2017-07-19
申请人： SAFRAN NACELLES
发明人： Patrick Boileau , Olivier Kerbler , Julien Lezerac , Aurélien Gonzalez , Loïc Grall , Ludovic Toupet
摘要： The present disclosure concerns a system for installing and removing a propulsion unit on a pylon of an aircraft, a propulsion unit of the type including a nacelle and a turbojet engine, the turbojet engine being linked on the pylon by at least one front suspension and one rear suspension. The system includes a supporting structure which is adapted to support a thrust reverser device, a front suspension of the turbojet engine, which carries a front part of the supporting structure, and which is removably fastened on a front part of the pylon, and a rear suspension of the turbojet engine which carries a rear part of the supporting structure, and which is removably fastened on a rear part of the pylon, and the disengagement of said suspensions of the pylon allowing removing the propulsion unit mounted on the pylon.
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公开(公告)号：US10590886B2
公开(公告)日：2020-03-17
申请号：US15655276
申请日：2017-07-20
申请人： SAFRAN NACELLES
摘要： The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.
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8.发明授权公开(公告)号：US10100780B2
公开(公告)日：2018-10-16
申请号：US15364623
申请日：2016-11-30
申请人： SAFRAN NACELLES
摘要： The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.
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