• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an assembly for an aircraft engine attachment comprising: a hinge pin (72) supported by two plain bearings (76, 78), a locking device blocking the translation axis in translation (72) in a direction that comprises: a locking screw (90) screwed in operation in a first inner portion (84) threaded with a tubular extension (82) integral with one of the two plain bearings, ○ a first locking system (106) having an inner resilient locking ring (110) housed in a groove (112) in the tubular extension (82), and ○ a second locking system (108) having a locking thread (114) ) which passes through first orifices (116) passing through the second section (94) of the locking screw (90) and the second orifices (118) passing through the tubular extension (82).
    公开号:FR3077560A1
    申请号:FR1850974
    申请日:2018-02-06
    公开日:2019-08-09
    发明作者:Jean GELIOT；Thomas Deforet；Adeline Soulie
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    ASSEMBLY FOR AN AIRCRAFT ENGINE MOUNT COMPRISING A HINGE AXIS SUPPORTED BY A SCREED AND MOVABLE IN TRANSLATION
    The present application relates to an assembly for an aircraft engine mount comprising a hinge pin supported by a yoke and motionless in translation.
    According to a configuration visible in FIGS. 1 and 2, an aircraft 10 comprises several engine assemblies 12 which are positioned under the wing 14 of the aircraft 10.
    An engine assembly 12 comprises an engine 16, a nacelle (not shown in FIG. 2) positioned around the engine 16 and a mast 18 which provides the connection between the engine 16 and the rest of the aircraft 10, in particular the wing 14.
    The mast 18 comprises a primary structure 20 which is connected to the engine 16 by a front engine mount 22, a rear engine mount 24 and a pair of thrust rods 26 which ensure the resumption of the thrust forces.
    According to an embodiment visible in Figure 3, the front engine mount 22 comprises a plate 28, integral with the mast 18, which has two yokes 30 arranged on either side of the mast 18, as well as two connecting rods 32 which each connect one of the yokes 30 of the plate 28 to a yoke 34 integral with a casing of the motor 16. Thus, each connecting rod 32 is connected to one of the yokes 30 of the plate 28 by a first articulation axis 36 and to one of the yokes 34 of the motor 16 by a second hinge pin 38.
    According to an embodiment visible in FIG. 4 and described in detail in the document FR3014971, an assembly between the yoke 34 secured to the engine 16 and the connecting rod 32 comprises a hinge pin 38 mounted in a first smooth bearing 40 inserted in a first branch 34.1 of clevis 34 and in a second smooth bearing 42 inserted in a second branch 34.2 of the clevis 34, the hinge pin 38 supporting, between the first and second branches 34.1 and 34.2, a ball joint 44 configured to connect the connecting rod 32 and the hinge pin 38.
    The first smooth bearing 40 comprises, at a first end, an external flange 40.1 configured to bear against an internal face 34.11 of the first branch 34.1 and, at a second end, a shoulder 40.2 configured to block in translation the axis of articulation 38 in a first direction. The second smooth bearing 42 comprises, at a first end, an external flange 42.1 configured to bear against an internal face 34.21 of the second branch 34.2.
    The articulation axis 38 is a cylinder which has an axis A38, a first end face 38.1, substantially perpendicular to the axis A38, configured to bear against the shoulder 40.2 of the first plain bearing 40 and a second face end 38.2 substantially perpendicular to the axis A38.
    The assembly also comprises a blocking device 46 configured to block in translation the hinge pin 38 in a second direction which, associated with the shoulder 40.2, makes it possible to immobilize in translation the hinge pin 38.
    The blocking device 46 comprises:
    An extension 48 of the second plain bearing 42 which has an internal bore
    48.1 threaded and notches 48.2, a locking screw 50 screwed into the extension 48 which has a front face
    50.1 bearing against the second end face 38.2 of the hinge pin 38 and a rear part 50.2 of hexagonal section allowing the screw 50 to be screwed, a locking washer 52 comprising an opening 52.1 which is fitted onto the part rear 50.2 hexagonal of the screw 50 and two diametrically opposite tongues 52.2 which are housed in notches 48.2 of the extension 48 to immobilize the screw 50 relative to the extension 48, an external elastic stop ring 54 which is partially housed in an annular groove formed in the rear part 50.2 of the screw 50 making it possible to immobilize the locking washer 52 in the notches 48.2 of the extension 48, and a pin 56 which passes through the extension 48 and the rear part 50.2 of the screw 50 for immobilize in rotation the screw 50 relative to the extension 48.
    This embodiment makes it possible to obtain a double rotational locking of the screw 50 relative to the extension 48. However, the locking device 46 thus obtained generates an offset D, relative to the outer face of the fork leg, important given the stacking of the locking washer 52, the external elastic stop ring 54 and the pin 56.
    The present invention aims to remedy the drawbacks of the prior art.
    To this end, the subject of the invention is an assembly for an aircraft engine mount comprising:
    an axis of articulation, a first smooth bearing supporting the axis of articulation, positioned in a first branch of a yoke and comprising an internal shoulder blocking in translation the axis of articulation in a first direction in operation, a second plain bearing supporting the articulation axis, positioned in a second branch of the yoke, comprising a tubular body and a tubular extension, said tubular extension having a first internal threaded portion, a blocking device blocking in translation the axis of articulation in a second direction in operation which includes:
    o a locking screw, extending between a first end face against which the articulation axis is supported in operation and a second end face, having a first section which adjoins the first end face and a second section which adjoins the second end face, the first section comprising a thread screwing in operation on the first internal threaded portion of the tubular extension, o first and second locking systems for immobilizing the locking screw relative to the tubular extension.
    According to the invention:
    the first locking system comprises an internal elastic stop ring and a groove, formed in the tubular extension, partially accommodating in operation the internal elastic stop ring, and the second blocking system comprises a locking wire, first orifices passing through the second section of the blocking screw and second orifices passing through the tubular extension, the blocking wire traversing in operation the first and second orifices to ensure blocking of the blocking screw relative to the tubular extension.
    This arrangement makes it possible to obtain a more compact assembly, the offset of the tubular extension being less important than for the prior art.
    According to another characteristic, the internal elastic stop ring is interposed between the locking screw and the second locking system.
    According to another characteristic, the locking screw comprises a shoulder face, separating the first and second sections, substantially parallel to the first and second end faces, bearing in operation against the internal elastic stop ring.
    According to another characteristic, the tubular extension comprises a second smooth interior portion, interposed between the first interior portion and one end of the tubular extension, which has an interior diameter greater than or equal to the interior diameter of the first interior portion.
    According to one embodiment, the first section of the locking screw comprises a collar having a diameter greater than the outside diameter of the first section and slightly less than the inside diameter of the second inner portion of the tubular extension, the collar being positioned at one end of the first section so that one of its lateral faces is arranged in the extension of the shoulder face.
    According to another characteristic, the blocking wire comprises two ends connected to one another to ensure that it is held in the first and second orifices.
    According to one embodiment, the two ends of the locking wire are stranded.
    According to another characteristic, the locking screw comprises a through hole, coaxial with the first and second sections, said through hole extending between the first and second end faces.
    According to another characteristic, the tubular extension comprises an internal groove positioned between the tubular body and the first internal portion, the internal groove having a bottom with a diameter greater than the internal diameter of the first internal portion.
    The subject of the invention is also an aircraft comprising an assembly for a motor fastener according to one of the preceding characteristics.
    Other characteristics and advantages will emerge from the description of the invention which follows, description given by way of example only, with reference to the appended drawings among which:
    FIG. 1 is a perspective view of an aircraft,
    FIG. 2 is a schematic representation of a propulsion unit connected to a wing which illustrates an embodiment,
    FIG. 3 is a perspective view of a front engine mount which illustrates an embodiment,
    FIG. 4 is a section of an assembly of a motor tie which illustrates an embodiment of the prior art,
    FIG. 5 is a section through an assembly of a motor tie which illustrates an embodiment of the invention,
    FIG. 6 is an exploded perspective view of the assembly visible in FIG. 5,
    FIG. 7 is a view of one end of a hinge pin of the assembly visible in FIG. 5,
    FIG. 8 is a half-section of a tubular extension of a second plain bearing which illustrates an embodiment of the invention, and
    Figure 9 is a half section of a locking screw which illustrates an embodiment of the invention.
    According to an embodiment illustrated in FIG. 5, part of a front engine attachment 60 comprises a yoke 62, integral with an aircraft engine (or one of these casings), having two first and second branches 64, 66, connected by a link 68 to a connecting rod 70 itself connected to a primary structure of an aircraft mast. The connection 68 comprises an articulation axis 72, which supports in the central part a ball joint 74, connecting the articulation axis 72 and the connecting rod 70, and first and second smooth bearings 76, 78, arranged on either side another of the ball 74, connecting the hinge pin 72 and the branches 64, 66 of the yoke 62.
    The first branch 64 comprises an internal face 641, oriented towards the second branch 66, and an external face 64E parallel to the internal face 641. The second branch 66 comprises an internal face 661, oriented towards the first branch 64, and an external face 66E parallel to the inner face 661. According to one configuration, the outer face 64E of the first branch 64 is difficult to access and the hinge pin 72 is introduced via the outer face 66E of the second branch 66.
    The first branch 64 supports the first smooth bearing 76 which has a tubular body 76.1, an outer flange 76.2 at a first end bearing in operation against the inner face 641 of the first branch 64 and an inner shoulder 76.3 configured to block in translation l hinge pin 72 in a first direction.
    The second branch 66 supports the second smooth bearing 78 which has a tubular body
    78.1 and an external flange 78.2 at a first end bearing in operation against the internal face 661 of the second branch 66. The tubular body
    78.1 has an inner diameter D78.1
    The articulation axis 72 is a cylinder which has an axis A72, a first end face 72.1, substantially perpendicular to the axis A72, bearing in operation against the internal shoulder 76.3 of the first plain bearing 76 and a second end face 72.2 substantially perpendicular to the axis A72.
    The assembly also includes a blocking device 80 configured to block in translation the hinge pin 72 in a second direction (opposite to the first direction) which, associated with the shoulder 76.3 of the first plain bearing 76, makes it possible to immobilize in translation the articulation axis 72.
    With the exception of the second plain bearing 78 and the locking device 80, the other elements of the link 68 may be identical to those of the prior art described above. Thus, this assembly can be mounted on new engine attachments as well as existing ones.
    Furthermore, although described applied to a front engine mount, the assembly of the invention can be used for the other engine mountings.
    The second plain bearing 78 includes a tubular extension 82 which has an end 82E and an outside diameter identical to that of the tubular body 78.1 of the second plain bearing 78. In operation, the tubular extension 82 projects from the outer face 66E of the second branch 66.
    According to an embodiment visible in FIG. 8, the tubular extension 82 comprises a first internal threaded portion 84 which adjoins the tubular body 78.1 and which has an internal diameter D84 greater than or equal to the internal diameter D78.1 of the tubular body 78.1 as well as 'a second smooth inner portion 86, interposed between the first inner portion 84 and the end 82E of the tubular extension 82, which has an inner diameter D86 greater than or equal to the inner diameter D84 of the first inner portion 84. The first and second portions interior 84 and 86 are coaxial with an axis A82 which corresponds to the axis of the tubular extension 82.
    According to one configuration, the tubular extension 82 comprises an internal groove 88 positioned between the tubular body 78.1 and the first internal portion 84, the internal groove 88 having a bottom with a diameter greater than the internal diameter D84 of the first internal portion 84.
    The locking device 80 comprises a locking screw 90, extending between a first end face 90.1 and a second end face 90.2, having a first section 92 which adjoins the first end face 90.1 and a second section 94 which adjoins the second face terminal 90.2. The first and second sections 92 and 94 are coaxial with an axis A90 which corresponds to the axis of the locking screw 90. In operation, the axis A90 of the locking screw 90 coincides with the axis A82 of the tubular extension 82.
    The first and second sections 92 and 94 are separated by a shoulder face 96 substantially parallel to the first and second end faces 90.1 and 90.2.
    The first section 92 comprises a thread 98 configured to be screwed onto the first internal threaded portion 84 of the tubular extension 82.
    As an indication, the first section 92 has an outside diameter substantially equal to twice that of the second section 94.
    According to one configuration, the locking screw 90 comprises a through hole 100, coaxial with the first and second sections 92, 94, which extends between the first and second end faces 90.1, 90.2 and through holes 102 parallel to the axis A90 of the locking screw 90 which extend between the first end face 90.1 and the shoulder face 96. The through holes 102 are configured to accommodate lugs of a key in order to tighten the locking screw 90. These through holes 100 and 102 make it possible to reduce the mass of the locking screw 90.
    The first section 92 comprises a collar 104 which has a diameter greater than the outside diameter of the first section 92 and slightly less than the inside diameter D86 of the second interior portion 86 of the tubular extension 82. The collar 104 is positioned at one end of the first section 92 so that the shoulder face 96 of the locking screw comprises one of the lateral faces of said flange 104.
    The locking device 80 comprises first and second locking systems 106, 108 to immobilize the locking screw 90 relative to the tubular extension 82.
    The first locking system 106 comprises an inner elastic stop ring 110, also called an inner circlip, and a groove 112, formed in the second inner section 86 of the tubular extension 82, partially accommodating in operation the elastic stop ring 110 inside. In operation, the inner elastic stop ring 110 is interposed between the locking screw 90 and the second locking system 108, the shoulder face 96 bearing against the inner elastic stop ring 108. The groove 112 is separated from the first inner portion 84 by a distance substantially equal to, or very slightly greater than, the width L104 of the flange 104. In operation, when the elastic stop ring 110 inside is partially housed in the groove 112, it immobilizes in translation, and therefore in rotation, the locking screw 90. The lateral face of the flange 104 and the shoulder face 96 form a clean support for the elastic stop ring 110 so that the latter does not take off during an untimely unscrewing of the locking screw 90.
    The second blocking system 108 comprises a blocking wire 114, first orifices 116 passing through the second section 94 of the blocking screw 90 and second orifices 118 passing through the second interior portion 86 of the tubular extension 82, the blocking wire 114 passing through in operation, the first and second orifices 116 and 118 to block the locking screw 90 relative to the tubular extension 82.
    According to one configuration, the second section 94 of the locking screw 90 comprises six first orifices 116 distributed regularly over its periphery. The second inner portion 86 of the tubular extension 82 comprises ten second orifices 118 distributed regularly over its periphery.
    According to one configuration, the blocking wire 114 passes through one of the second orifices 118 of the second inner portion 86 of the tubular extension 82, two first diametrically opposed orifices 116 of the second section 94 of the blocking screw 90, then a second orifice 118 of the second inner portion 86 of the tubular extension 82.
    To maintain the locking wire in the first and second orifices 116 and 118, the two ends 114.1 and 114.2 of the locking wire 114 are connected together. According to one configuration, the ends 114.1 and 114.2 are twisted to ensure their connection.
    According to the invention, the blocking device 80 comprises only two blocking systems 106 and 108 in addition to the blocking screw 90, which makes it possible to reduce the offset D of the tubular extension 82 relative to the external face 66E of the second branch 66. Thus, a more compact assembly is obtained.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Assembly for an aircraft engine mount comprising:
    a hinge pin (72), a first smooth bearing (76) supporting the hinge pin (72), positioned in a first branch (64) of a yoke (62) and having an internal shoulder (76.3) blocking in translation the articulation axis (72) in a first direction in operation, a second smooth bearing (78) supporting the articulation axis (72), positioned in a second branch (66) of the yoke (62 ), comprising a tubular body (78.2) and a tubular extension (82), said tubular extension (82) having a first internal portion (84) threaded, a locking device blocking in translation the articulation axis (72) along a second sense in operation which includes:
    o a locking screw (90), extending between a first end face (90.1) against which the hinge pin (72) is supported in operation and a second end face (90.2), having a first section (92 ) which adjoins the first end face (90.1) and a second section (94) which adjoins the second end face (90.2), the first section (92) comprising a thread (98) which is screwed in operation on the first interior portion (84 ) threaded of the tubular extension (82), o of the first and second locking systems (106, 108) for immobilizing the locking screw (90) relative to the tubular extension (82), the assembly being characterized in that the first locking system (106) comprises an internal elastic stop ring (110) and a groove (112), formed in the tubular extension (82), partially accommodating in operation the internal elastic stop ring (110) and in what the second blocking system (1 08) comprises a locking wire (114), first holes (116) passing through the second section (94) of the locking screw (90) and second holes (118) passing through the tubular extension (82), the wire blocking (114) running during operation the first and second orifices (116, 118) to block the locking screw (90) relative to the tubular extension (82).
    [2" id="c-fr-0002]
    2. An assembly for an aircraft engine mount according to claim 1, characterized in that the internal elastic stop ring (110) is interposed between the locking screw (90) and the second locking system (108) .
    [3" id="c-fr-0003]
    3. An assembly for an aircraft engine mount according to claim 1 or 2, characterized in that the locking screw (90) comprises a shoulder face (96), separating the first and second sections (92, 94) , substantially parallel to the first and second end faces (90.1, 90.2), bearing in operation against the internal elastic stop ring (108).
    [4" id="c-fr-0004]
    4. An assembly for an aircraft engine mount according to the preceding claim, characterized in that the tubular extension (82) comprises a second inner portion (86) smooth, interposed between the first inner portion (84) and one end (82E ) of the tubular extension (82), which has an internal diameter (D86) greater than or equal to the internal diameter (D84) of the first internal portion (84).
    [5" id="c-fr-0005]
    5. An assembly for an aircraft engine mount according to the preceding claim, characterized in that the first section (92) of the locking screw (90) comprises a flange (104) having a diameter greater than the outside diameter of the first section (92) and slightly smaller than the inside diameter (D86) of the second inside portion (86) of the tubular extension (82), the flange (104) being positioned at one end of the first section (92) so that one of its side faces is arranged in the extension of the shoulder face (96).
    [6" id="c-fr-0006]
    6. An assembly for an aircraft engine mount according to one of the preceding claims, characterized in that the locking wire (114) comprises two ends (114.1, 114.2) interconnected to ensure its maintenance in the first and second orifices (116, 118).
    [7" id="c-fr-0007]
    7. An assembly for an aircraft engine mount according to the preceding claim, characterized in that the two ends (114.1, 114.2) of the locking wire (114) are stranded.
    [8" id="c-fr-0008]
    8. An assembly for an aircraft engine mount according to one of the preceding claims, characterized in that the locking screw (90) comprises a through hole (100), coaxial with the first and second sections (92, 94), said through hole (100) extending between the first and second end faces (90.1, 90.2).
    [9" id="c-fr-0009]
    9. An assembly for an aircraft engine mount according to one of the preceding claims, characterized in that the tubular extension (82) has an interior groove (88) positioned between the tubular body (78.1) and the first interior portion ( 84), the inner groove (88) having a bottom with a diameter greater than the diameter
    5 interior (D84) of the first interior portion (84).
    [10" id="c-fr-0010]
    10. Aircraft comprising an assembly for an engine mount according to one of the preceding claims.
    类似技术:
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    同族专利:
    公开号 | 公开日
    EP3521174B1|2020-04-15|
    FR3077560B1|2020-01-10|
    US20190241272A1|2019-08-08|
    CN110116813A|2019-08-13|
    EP3521174A1|2019-08-07|
    US10577114B2|2020-03-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6150656A|1998-12-10|2000-11-21|United Technologies Corporation|Method of assembly and inspection for a gas turbine engine|
    WO2014154980A1|2013-03-29|2014-10-02|Snecma|Ball-jointed device for suspending a turbomachine from a pylon or for suspending equipment from the body of the turbomachine.|
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    FR3014973B1|2013-12-12|2016-01-22|Airbus Operations Sas|ASSEMBLY COMPRISING A JOINT AXLE SUPPORTED BY A CAP AND IMMOBILIZED IN TRANSLATION BY A LOCKING DEVICE INCORPORATING A DOUBLE ANTI-ROTATION SYSTEM|
    FR3014972B1|2013-12-12|2016-04-22|Airbus Operations Sas|ASSEMBLY COMPRISING A JOINT AXLE SUPPORTED BY A CAP AND IMMOBILIZED IN TRANSLATION BY A LOCKING DEVICE INCORPORATING A DOUBLE ANTI-ROTATION SYSTEM|
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    FR3074146B1|2017-11-24|2019-10-18|Airbus Operations|IMPROVED PIVOTING AXIS FOR AN AIRCRAFT ENGINE ATTACHMENT|
    US20190353197A1|2018-05-16|2019-11-21|United Technologies Corporation|Anti-rotation device for fasteners|US10634092B2|2017-09-08|2020-04-28|United Technologies Corporation|Linkage assembly preventing axial rotation of the link rod|
    FR3074146B1|2017-11-24|2019-10-18|Airbus Operations|IMPROVED PIVOTING AXIS FOR AN AIRCRAFT ENGINE ATTACHMENT|
    法律状态:
    2019-02-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-08-09| PLSC| Publication of the preliminary search report|Effective date: 20190809 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-11-12| ST| Notification of lapse|Effective date: 20211005 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1850974|2018-02-06|
    FR1850974A|FR3077560B1|2018-02-06|2018-02-06|ASSEMBLY FOR AN AIRCRAFT ENGINE MOUNT COMPRISING A HINGE AXIS SUPPORTED BY A SCREED AND MOVABLE IN TRANSLATION|FR1850974A| FR3077560B1|2018-02-06|2018-02-06|ASSEMBLY FOR AN AIRCRAFT ENGINE MOUNT COMPRISING A HINGE AXIS SUPPORTED BY A SCREED AND MOVABLE IN TRANSLATION|
    US16/253,040| US10577114B2|2018-02-06|2019-01-21|Assembly for an aircraft engine mounting comprising an articulation axis supported by a yoke joint and translationally immobile|
    EP19153409.8A| EP3521174B1|2018-02-06|2019-01-24|Assembly for an aircraft engine attachment comprising a hinge pin supported by a yoke and immobile in translation|
    CN201910098352.8A| CN110116813A|2018-02-06|2019-01-31|Component and aircraft for aircraft engine installation part|
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