• 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 engine attachment (100) for an aircraft, intended to attach an engine to a mast and comprising: - a fastening body (302) intended to be fixed to the mast and having a cylindrical extension (316), and a fixing assembly (350) comprising a pallet (352) intended to be fixed to the engine and connecting means (354) integral with the pallet (352) and arranged on the cylindrical extension (316) so as to form a ball joint connection between said cylindrical extension (316) and the pallet (352), the connecting means (354) comprising: - a one-piece ball (356) having a central bore (358) into which the cylindrical extension ( 316) and whose outer surface is a spherical portion, - fixing means (362) provided for fixing the ball (356) on the cylindrical extension (316), - two cages (364a-b), each having a surface interior (366a-b) in the form of a spherical portion, the two inner surfaces ures (366a-b) facing one another to accommodate the ball (356), and - for each cage (364a-b), securing means (369) provided for securing said cage (364a); b) with the pallet (352).
    公开号:FR3021298A1
    申请号:FR1454722
    申请日:2014-05-26
    公开日:2015-11-27
    发明作者:Jerome Cassagne；Antoine Cousin；Thomas Deforet
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an engine attachment for an aircraft, an engine assembly comprising a motor, a motor attachment pylon, and a fastening system comprising such an engine attachment, and an aircraft comprising at least one such engine assembly. .
    [0002] Usually, a mast of an aircraft is provided to form the connecting interface between an engine, such as a turbojet engine, and a structural part, generally the wing, of the aircraft. The mast also allows the establishment of appropriate means to ensure the transfer of fuel and air, as well as the establishment of electrical and hydraulic systems, between the engine and the aircraft. In addition, the mast is provided in particular with a fastening system interposed between the engine and a rigid structure of the mast. This fastening system generally comprises at least one front engine attachment and at least one rear engine attachment, the layout and design of which are determined and certified to effectively recover the forces and moments that may be generated along the three axes of the engine. 'aircraft. Fig. 6 shows a front engine attachment 700 of the state of the art which comprises inter alia, a fastener body 702 on which is mounted a pallet 752 provided to attach to the compressor housing of the engine. The pallet 752 is mounted on the attachment body 702 via a ball joint. The ball joint is formed by two shells 756a-b of hemispherical outer surfaces disposed between a cylindrical extension 716 of the fastener body 702 and a bore 704 of the pallet 702. The attachment of the two shells 756a-b is ensured by a plate 712 fixed by four screws 714 which screw into the extension 716 in an axial direction of the extension 716. Such an arrangement causes a deformation of the two shells 756a-b when the screws 714 are too tight and then a risk of radial jamming of ball joint. In addition, the position of the screws 714 in a cramped location prevents the screw diameter 714 from being increased in the event of repair of the threads of the extension.
    [0003] An object of the present invention is to provide an engine attachment for an aircraft which does not have the drawbacks of the prior art and which in particular avoids the risk of jamming of the ball joint. For this purpose, there is provided an engine attachment for an aircraft, intended to attach an engine to a mast, the engine attachment comprising: a fastening body intended to be fixed to the mast and having a cylindrical extension, and a set fixing device comprising a pallet intended to be fixed to the engine and connecting means integral with the pallet and arranged on the cylindrical extension so as to form a ball joint connection between said cylindrical extension and the pallet, the engine attachment being characterized in that that the connecting means comprise: - a ball which is monobloc, which has a central bore in which the cylindrical extension is enclosed and whose outer surface is a spherical portion, - fixing means provided for fixing the ball on the cylindrical extension, - two cages, each cage having an inner surface in the form of a spherical portion, the two inner surfaces facing one of the other re to define a housing in which houses the ball, and - for each cage, securing means provided for securing said cage with the pallet. Such an engine attachment has a ball joint based on a one-piece ball which is not constrained in clamping, thus limiting the risk of deformation and jamming. The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in connection with the attached drawings, among which: FIG. . 1 is a side view of an aircraft according to the invention, FIG. 2 is a schematic side view of an engine assembly according to the invention, FIG. 3 is a perspective view of an engine attachment according to the invention, FIG. 4 is a sectional view of the motor attachment of FIG. 3 by a substantially horizontal plane, and FIG. 5 is an exploded view of the motor attachment of FIG. 3. FIG. 1 shows an aircraft 10 which comprises a mast 12 fixed under the structure of a wing 14 of the aircraft 10. The aircraft 10 also has a nacelle 16 fixed to the mast 12 and inside which is arranged a motor ( 20, Fig. 2). Fig. 2 shows a motor assembly 200 which comprises the motor 20, the mast 12 to the structure 22 of which is fixed the motor 20, and an attachment system 24 which comprises a front engine attachment 100 and a rear engine attachment 26 which fix the engine In the example presented here, the motor 20 has a compressor housing 28 and a central housing 30.
    [0004] The motor assembly 200 is assigned an orthonormal referential R having X, Y and Z axes or directions. It is considered that: the direction X is a longitudinal direction, this direction X passing at the front attachment 100 and being parallel to a longitudinal axis of the motor 20 and substantially parallel to a median longitudinal direction of the mast 12, the direction Y is a transverse direction oriented transversely to the mast 12, the direction Y being orthogonal to the direction X, and the Z direction is a vertical direction, which is orthogonal to the X and Y directions. In addition, throughout the description, the terms "front" and "rear" are to be considered with respect to a direction of advancement of the aircraft 10 encountered during a thrust exerted by the motor 20, this direction being shown schematically by an arrow 18 in FIGS. 1 and 2. The rear engine attachment 26 is of the usual type and known to those skilled in the art and is not described further.
    [0005] The forward engine attachment 100 includes, as shown in FIG. 3, an elongated fastener body 302, which is mounted in the X direction and which is conventionally attached to the rigid structure 22 of the mast 12. This fastener body 302 is provided at a front end 304 of an assembly fastening 350, to make a connection with the compressor housing 28.
    [0006] The front engine attachment 100 also comprises two lateral rods 306a-b connected to a rear end 308 of the fastening body 302. The two connecting rods 306a-b are arranged symmetrically with respect to a vertical plane XZ. The two connecting rods 306a-b are each hingedly connected, on the one hand, by a front end 310a-b, to a rear part of the compressor casing 28, and on the other hand by a rear end 312a , to a spreader 314 hingedly mounted on the rear end 308 of the fastener body 302. The fastening assembly 350 will now be more specifically described in support of Figs. 4 and 5.
    [0007] The attachment body 302 has, at its front end 304, a cylindrical extension 316 which extends forward substantially parallel to the axis X. The attachment assembly 350 comprises a pallet 352 to which the compressor housing 28 is fixed and connecting means 354 secured to the pallet 352 and arranged on the cylindrical extension 316 so as to form a ball joint connection between said cylindrical extension 316 and the pallet 352. The connecting means 354 comprise: a ball 356 which is one-piece, which has a central bore 358 in which the cylindrical extension 316 engages and whose outer surface 360 is a spherical portion, - fixing means 362 provided for fixing the ball 356 on the cylindrical extension 316, - Two cages 364a-b, each cage 364a-b having an inner surface 366a-b in the form of a spherical portion, the two inner surfaces 366a-b facing one another to define a box in which housing 356 the ball, and - for each cage 364a-b, securing means 369 provided for securing said cage 364a-b with the pallet 352. The two inner surfaces 366a-b can thus be movable relative to the 20 ball 356 and thus accompany a displacement of the motor 20. Such an arrangement allows to have a ball joint based on a ball 356 consists of a single component which limits the risk of jamming of the ball joint because the 356 ball n ' is not constrained in tightening. The dimensions of the outer surface 360 of the ball 356 and the inner surfaces 366a-b of the cages 364a-b are such that the inner surfaces 366a-b slide without stress on the ball 356. The complementary shapes of spherical portions of the cages 364a and ball 356 prevent movement of cages 364a-b and ball 356 relative to each other parallel to the X axis. In the embodiment of the invention presented herein, two cages 364a-b are symmetrical with respect to the XZ plane. The fixing means 362 here take the form of an axis 372 and two circlips 374a-b. The cylindrical extension 316 has a radial bore 376 and the ball 356 also has a radial bore 378 which aligns with the radial bore 376 of the cylindrical extension 316. The axis 372 then engages in the two radial bores. 376 and 378. Each circlip 374a-b fits into a groove located at each end of the radial bore 378 of the ball 356 to axially block the axis 372. For each cage 364a-b, the securing means 369 take here the form of at least one threaded rod 370a-d integral with the cage 364a-b and oriented towards the front, that is to say in the direction of the pallet 352, and for each threaded rod 370a-d, a nut 382a-b. The pallet 352 has, for each threaded rod 370a-d, a bore 380a-d into which said threaded rod 370a-d engages. A nut 382a-b is then screwed onto each threaded rod 370a-d to sandwich the pallet 352. In the embodiment of the invention presented here, each cage 364a-b has a flat 368a-b which extends outwardly relative to the inner surface 366a-b and which carries the threaded rod or rods 370a-d (here two) which are oriented said flat 368a-b forwards.
    [0008] During assembly, each plate 368a-b bears against a rear face of the pallet 352 when tightening the nuts 382a-b. The pallet 352 here has two holes 384a-b in each of which a screw-nut assembly can be put in place to fix the compressor casing 28. In the embodiment of the invention presented here, the attachment body 302, and therefore the cylindrical extension 316 consist of two brackets symmetrical with respect to the XZ plane and fixed against each other. In the same way, here, the pallet 352 consists of two fittings substantially symmetrical with respect to a plane perpendicular to the axis of the cylindrical extension 316.
    [0009] The assembly of the forward engine attachment 100 then consists of: - presenting the cylindrical extension 316, - fitting the ball 356 on the cylindrical extension 316, - fixing the ball 356 with the fixing means 362 - to place the two stands 364a-b on either side of the ball 356, - to present the pallet 352, and - to secure the cages 364a-b with the pallet 352 by means of the securing means 369 .
    [0010] Fixing the ball 356 on the cylindrical extension 316 here consists of fitting the axis 372 in the two radial bores 376 and 378 and to set up the two circlips 374a-b. The securing of the pallet 352 on the cages 364a-b here consists of inserting each threaded rod 370a-d into a bore 380a-d of the pallet 352 and tightening a nut 382a-b. The engine attachment 100 thus has a relatively small number of parts and the assembly is simple and does not require any specific tool.
    权利要求:
    Claims (6)
    [0001]
    CLAIMS1) Engine attachment (100) for an aircraft (10), intended to attach a motor (20) to a mast (12), the engine attachment (100) comprising: - a fastening body (302) intended to be attached to the mast (12) and having a cylindrical extension (316), and - a fixing assembly (350) comprising a pallet (352) intended to be fixed to the motor (20) and connecting means (354) integral with the pallet (352) and arranged on the cylindrical extension (316) so as to form a ball joint connection between said cylindrical extension (316) and the pallet (352), the engine attachment (100) being characterized in that the means for link (354) comprises: - a ball (356) which is integral, which has a central bore (358) in which the cylindrical extension (316) is gated and whose outer surface (360) is a spherical portion; fastening means (362) for attaching the ball (356) to the cylindrical extension (316), two cages (364a-b), each cage ( 364a-b) having an inner surface (366a-b) in the form of a spherical portion, the two inner surfaces (366a-b) facing one another to define a housing in which the ball (356), and - for each cage (364a-b), securing means (369) provided for securing said cage (364a-b) with the pallet (352).
    [0002]
    2) A motor attachment (100) according to claim 1, characterized in that the cylindrical extension (316) has a radial bore (376), in that the ball (356) has a radial bore (378) which aligns with the radial bore (376) of the cylindrical extension (316), and in that the fastening means (362) comprise an axis (372) and two circlips (374a-b), said axis (372) being embedding in the two radial bores (376, 378), and each circlip (374a-b) fitting into a groove at each end of the radial bore (378) of the ball (356).
    [0003]
    3) Motor attachment (100) according to one of claims 1 or 2, characterized in that the securing means (369) take the form of at least one threaded rod (370a-d) integral with the cage (364a). b) and facing forward, and for each threaded shank (370a-d), a nut (382a-b), in that the pallet (352) has, for each threaded shank (370a-d), a bore (380a-d) into which said threaded rod (370a-d) is engaged, a nut (382a-b) then screwing onto each threaded rod (370a-d).
    [0004]
    4) Motor attachment (100) according to claim 3, characterized in that each cage (364a-b) has a plate (368a-b) which extends outwardly with respect to the inner surface (366a-b) and which carries the threaded rod or rods (370a-d).
    [0005]
    5) Motor assembly (200) comprising a motor (20), a mast (12), and a fastening system (24) comprising at least one motor attachment (100) according to one of claims 1 to 4, the attachment body (302) is attached to the mast (12), and whose pallet (352) is attached to the engine (20).
    [0006]
    Aircraft (10) having at least one engine assembly (200) according to claim 5.
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    同族专利:
    公开号 | 公开日
    FR3021298B1|2016-07-01|
    US9573694B2|2017-02-21|
    US20150336678A1|2015-11-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3006587A|1956-11-12|1961-10-31|Snecma|Suspension device for jet propulsion units|
    US3141231A|1961-04-17|1964-07-21|Superior Ball Joint Corp|Method of fabricating a ball and socket assembly|
    EP0844172A1|1996-11-21|1998-05-27|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Redundant front suspension for a turbine engine|
    WO2006097484A1|2005-03-18|2006-09-21|Airbus France|Engine fastener of a mounting system interposed between an attachment strut and an aircraft engine|
    US7461902B1|2005-10-26|2008-12-09|Robert Darst|Auger car bearing support|
    US20140084129A1|2012-09-27|2014-03-27|United Technologies Corporation|Assembly for mounting a turbine engine case to a pylon|FR3061480A1|2016-12-30|2018-07-06|Airbus Operations|AIRCRAFT ENGINE ASSEMBLY COMPRISING A FRONT ENGINE ATTACHMENT FACILITATING ITS ASSEMBLY|US6843449B1|2004-02-09|2005-01-18|General Electric Company|Fail-safe aircraft engine mounting system|
    US7810239B2|2006-10-23|2010-10-12|United Technologies Corporation|Engine mount bearing sleeve repair|
    US20130193298A1|2012-01-29|2013-08-01|David F. Sandy|Gas turbine engine mounting structure with secondary load path|
    FR3003896B1|2013-03-29|2015-03-20|Snecma|JOINT JOINT DEVICE FOR SUSPENDING A TURBOMACHINE TO A PYLONE OR SUSPENSION OF EQUIPMENT TO THE BODY OF THE TURBOMACHINE|
    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|FR3016608B1|2014-01-21|2016-02-26|Airbus Operations Sas|ENGINE ATTACHMENT FOR AIRCRAFT.|
    US10144525B2|2015-09-24|2018-12-04|Embraer S.A.|Aircraft engine pylon to wing mounting assembly|
    US9868539B2|2015-09-24|2018-01-16|Embraer S.A.|Aircraft engine pylon to wing mounting assembly|
    FR3065442B1|2017-04-25|2021-03-19|Airbus Operations Sas|ENGINE ASSEMBLY FOR AIRCRAFT INCLUDING A FRONT ENGINE ATTACHMENT INTEGRATED IN THE HOUSING OF THE MAST|
    法律状态:
    2015-05-21| PLFP| Fee payment|Year of fee payment: 2 |
    2015-11-27| PLSC| Search report ready|Effective date: 20151127 |
    2016-05-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-05-22| PLFP| Fee payment|Year of fee payment: 5 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-05-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-05-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1454722A|FR3021298B1|2014-05-26|2014-05-26|ENGINE ATTACHMENT FOR AN AIRCRAFT|FR1454722A| FR3021298B1|2014-05-26|2014-05-26|ENGINE ATTACHMENT FOR AN AIRCRAFT|
    US14/719,583| US9573694B2|2014-05-26|2015-05-22|Engine fastener for an aircraft|
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