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公开(公告)号：US20220082064A1
公开(公告)日：2022-03-17
申请号：US17536480
申请日：2021-11-29
摘要： An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.
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2.发明申请公开(公告)号：US20210239047A1
公开(公告)日：2021-08-05
申请号：US17238602
申请日：2021-04-23
申请人： Safran Nacelles
发明人： Patrick BOILEAU
摘要： A nacelle for use in an aircraft having a turbojet engine (the turbojet engine including a fan casing and a suspension pylon) includes a D-shaped structure downstream section embedding a thrust reverser device. The D-shaped structure downstream section includes a movable cascades vane. The D-shaped structure downstream section also includes two D-shaped half-structures each having an outer half-cowl movable in translation along a longitudinal axis, a connector between the cascades vane and the outer half-cowl, a twelve o'clock half-bifurcation, an inner half-structure defining an inner portion of the annular flow path, and a twelve o'clock half-beam mounted on the twelve o'clock half-bifurcation articulated on the pylon. The nacelle further includes an axial retention device of the downstream section of the nacelle, relative to the turbojet engine, configured to provide a connection defining an axial retention between the twelve o'clock half-beam and a fixed element of the fan casing.
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公开(公告)号：US20210079871A1
公开(公告)日：2021-03-18
申请号：US16914782
申请日：2020-06-29
申请人： Safran Nacelles
发明人： Loïc GRALL , Alexis HEAU , Benjamin BREBION , Sébastien Michel Thierry GUILLEMANT , Mélody SERISET , Patrick BOILEAU
IPC分类号： F02K1/70
摘要： A grid-type thrust reverser for a turbojet engine includes a moving O-shaped thrust reverser body that is generally cylindrical in shape around a longitudinal central axis (A) and includes an inner wall configured to delimit a cold air stream, with an inner structure that surrounds the turbojet engine, the movable thrust reverser body being mounted so as to be able to slide along the longitudinal central axis (A) between a direct jet position in which the outer cowl covers the thrust reverser grids, and a thrust-reversal position in which the outer cowl uncovers the thrust reverser grids. The movable thrust reverser body includes a first half-portion and a second half-portion that are mounted so as to each pivot about a longitudinal pivot axis (B), between a closed position and an open gullwing position for removing the turbojet engine, via the cradle.
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4.发明申请公开(公告)号：US20200309065A1
公开(公告)日：2020-10-01
申请号：US16901690
申请日：2020-06-15
申请人： Safran Nacelles
发明人： Patrick BOILEAU
摘要： A propulsion unit for an aircraft including a nacelle with a D-shaped structure housing a thrust-reversing device with movable vanes, the nacelle containing two D-shaped half-structures each including an external reverser half-cowl. The propulsion unit contains an assembly box-type structure, attached in downstream cantilevered fashion to the turbojet engine fan casing, the box-type structure including two guide rails guiding the deflection vanes, a locking device between the assembly box-type structure and the half-beams in the six o'clock position of the D-shaped half-structures, the assembly box-type structure being arranged in the propulsion unit such that the guide rails guiding the vanes of the assembly box-type structure are situated in the continuation of the guide rails in the six o'clock position guiding the vanes attached to the fan casing, to provide continuity between the rails.
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公开(公告)号：US20240254944A1
公开(公告)日：2024-08-01
申请号：US18560510
申请日：2022-05-13
申请人： SAFRAN NACELLES
摘要： A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.
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公开(公告)号：US20210237891A1
公开(公告)日：2021-08-05
申请号：US17215197
申请日：2021-03-29
申请人： Safran Nacelles
发明人： Patrick BOILEAU
摘要： An air intake for a nacelle of an aircraft propulsion assembly includes an upstream section that defines an air intake flow path, a central section surrounding a fan of an engine, and a downstream section surrounding a combustion chamber of the engine. The air intake includes a disassembly mechanism which has a panel able to move between a flush closed position in which the panel provides aerodynamic continuity of the air intake in the air intake flow path, and an open maintenance position in which the panel is radially and outwardly retracted in relation to its flush closed position in order to free up a space which allows removal of a blade of the fan at its distal end.
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公开(公告)号：US20210190005A1
公开(公告)日：2021-06-24
申请号：US17191106
申请日：2021-03-03
申请人： Safran Nacelles
摘要： A thrust reverser for an aircraft propulsion assembly includes a movable structure provided with external covers connected to hinges through a pivot connection allowing the external covers to rotate between a closed position and a maintenance position. The hinges are connected to secondary rails rigidly attached to an engine pylon through a sliding connection allowing the external covers to move in translation between a direct thrust position and a reverse thrust position. The hinges and the secondary rails are independent of beams to which the parts of the movable structure other than the external covers are connected. A method for maintaining an aircraft propulsion unit is also disclosed. The method includes positioning of the external covers in maintenance position followed by a placement of the beams and of the parts of the movable structure other than the external covers.
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公开(公告)号：US20200309029A1
公开(公告)日：2020-10-01
申请号：US16901733
申请日：2020-06-15
申请人： Safran Nacelles
发明人： Patrick BOILEAU , Caroline COAT-LENZOTTI , Marc VERSAEVEL , Virginie Emmanuelle Anne Marie DIGEOS , Pierre-François BEHAGHEL
摘要： An air inflow lip of a nacelle for a turbojet of an aircraft, including a cavity defined by a leading edge of the nacelle and by an annular wall, includes an inner wall, an acoustic treatment device, and a pneumatic de-icing device including a de-icing fluid supply device. The inner wall of the air inflow lip includes acoustic boreholes and the pneumatic de-icing device includes a honeycombed de-icing plate mounted inside the cavity on the inner wall of the air inflow lip. Also included are conduits for the circulation of a de-icing fluid and acoustic wells communicating with the acoustic boreholes.
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公开(公告)号：US20210003097A1
公开(公告)日：2021-01-07
申请号：US17025019
申请日：2020-09-18
摘要： A turbofan propulsion assembly includes a thrust reverser with movable flaps. The propulsion assembly further includes an engine and a nacelle surrounding the engine, and the nacelle includes a thrust reverser with sliding cowls and thrust reverser flaps, and an inner structure. The portion of the inner structure positioned perpendicular to the thrust reverser flaps includes two halves that can open toward the exterior of the nacelle cowls.
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10.发明申请公开(公告)号：US20200378341A1
公开(公告)日：2020-12-03
申请号：US16998720
申请日：2020-08-20
摘要： A propulsion unit includes a nacelle, a turbojet engine, and a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the turbojet engine. The propulsion unit further includes actuators arranged around the annular duct and each actuator has a front end attached to the turbojet engine and a rear end which translates movable rear covers and gratings for opening, in the annular duct, radial passages which receive said gratings. The propulsion unit further has lifting points that are arranged around the annular duct for lifting the turbojet engine. At least one of the lifting points is formed on a beam for attaching an front end of an actuator.
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