• 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 a method of mounting a motor (1) on an aircraft pylon (3) comprising integral motor suspension members (31) of the pylon, the motor being secured to a cradle (6). suspension by which it is suspended from the pylon, the method comprising a step of hoisting the engine in a vertical direction to the pylon and a step of approaching the pylon by a displacement of the engine in another direction, characterized in that prior to the pylon, attaching to said suspension members (31), an intermediate piece (7) having an interface intended to cooperate with a complementary interface provided on the cradle (6), so as to position the cradle relative to the intermediate piece at the end of the berthing of the pylon. The invention also relates to the device for implementing the method.
    公开号:FR3025782A1
    申请号:FR1458756
    申请日:2014-09-16
    公开日:2016-03-18
    发明作者:Mario Lambey；Bruno Albert Beutin；Marc Patrick Tesniere
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to the field of turbine engines, such as turbojet or turboprop engines, and is intended for mounting them on an airplane. It applies more particularly to the mounting of an engine on a pylon secured to the aircraft. STATE OF THE ART In the context of a development relating to a provision of propulsion engines, it has been proposed to connect the engines to the fuselage, in particular at the rear, by means of pylons. The suspension of the engines advantageously comprises a cradle forming an interface with the pylon and a connection structure from the cradle to the engine. It should be noted that the connection of the cradle to the pylon comprises a pair of horizontal axes integral with the pylon which are embedded in ears integral with the cradle as seen in Figure 1. This type of arrangement allows installation of equipment more easy and a balanced recovery of efforts. Moreover it allows to install the engine on a pylon that can have a slope, particularly upwards, relative to the horizontal.
    [0002] In this case, however, there is a problem when installing the engine on the aircraft; operation which is also known as airplane. Mounting the engine on the aircraft is already in itself a delicate operation because the suspension and the pylon must be linked to each other with great precision. The accuracy of the position of an engine relative to the aircraft is essential, both from a mechanical point of view and from an aerodynamic point of view and the performance of the aircraft. It is observed that the interface between the engine and the pylon, the orientation of the engine, as well as the connection structure require to have the elements of the suspension preinstalled on the engine before the assembly operation on the aircraft.
    [0003] In this configuration, the hoisting operation of the engine also requires combining two displacements: first a vertical translation of the engine to bring it to exactly the right height and then a horizontal translation from the back to the before to allow the engine 5 of the suspension members of the pylon, that is to say belonging to the pylon, to interface properly with the suspensions. However, the lifting system consisting of a lifting bridge and slings, this operation has the risk of damage to the suspension members on the pylon, which would cause additional immobilization of the aircraft. The suspension members integral with the pylon may comprise horizontal axes and possible flexible damping pads. Engine mounting techniques with hoisting by slings and displacements by vertical and horizontal translations are known per se. An example of the procedure is described in the patent application WO2012172208 filed in the name of the present applicant. The solution proposed in this document does not solve the problem of protection of certain organs of the aircraft. DESCRIPTION OF THE INVENTION The present applicant has set itself the objective of overcoming this problem and of reducing the risks of damage associated with the aircraft's engines. This objective is achieved by implementing the method according to the invention.
    [0004] Thus, the method of mounting a motor on an aircraft pylon comprising motor suspension members integral with the pylon, the motor being secured to a suspension cradle by which it is suspended from the pylon, the method comprising a step of hoisting the motor 3025782 3 in a vertical direction to the pylon and a step of approaching the pylon by a displacement of the engine in another direction, is characterized in that it is fixed beforehand to the pylon, by hanging on said suspension members, an intermediate piece having an interface 5 intended to cooperate with a complementary interface provided on the cradle so as to wedge in position the cradle relative to the intermediate piece at the end of the berthing of the pylon. The two interfaces are preferably arranged in such a way that the docking can be achieved by translation perpendicular to the axis of the motor and the translation of the docking is preferably carried out in a horizontal plane. In order to guarantee a smooth approach, the cradle is guided and wedged in position relative to the intermediate piece by means of centering pins provided on one of the two interfaces, the pins cooperating with centering orifices arranged on the other interface. The fixing method 15 comprises a step of fixing the cradle to the intermediate piece, once the cradle wedged in position relative to the intermediate piece. The invention also relates to the device for implementing the method. It comprises a cradle and an intermediate piece, the cradle being arranged to be fixed to the motor by a connecting structure and the intermediate part 20 being arranged to be fixed to the pylon independently of the cradle. This device preferably also comprises means for fixing the cradle to the intermediate piece. This last fixing means comprises in particular bolts connecting the cradle to the intermediate piece. In order to facilitate docking, the device comprises a wedging means in position of the cradle on the intermediate piece. According to another feature the intermediate part of the device comprises means, such as ears arranged to cooperate with the suspension members, such as pins, integral with the pylon.
    [0005] The invention also relates to the assembly of an aircraft and at least one engine, the engine being fixed to a pylon inclined upwardly via the above device.
    [0006] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the following detailed explanatory description of an embodiment of the invention. invention given by way of purely illustrative and non-limiting example, with reference to the attached schematic drawings. In these drawings: FIG. 1 is a representation of an assembly formed by a motor and a pylon connecting the fuselage of an aircraft; FIG. 2 shows a structure for fixing a motor to a tower, which has drawbacks which the invention aims to solve; FIG. 3 shows in exploded perspective an arrangement for implementing the method according to the invention; - Figure 4 shows the engine with the cradle of the arrangement alone; FIG. 5 shows a mounting phase according to the invention of the motor on the pylon. DETAILED DESCRIPTION OF AN EMBODIMENT OF THE INVENTION FIG. 1 represents a motor 1, for example of the "open rotor" type with its rotating nacelle, represented here without the propellers. The engine is mounted on a tower 3 which is adapted to be attached to the fuselage of an aircraft, not visible here, forming a non-zero angle with a horizontal plane. FIG. 2 shows an example of suspension cradle 5 developed by the Applicant and making it possible to secure the motor 1 to the pylon 3. The motor, here of the "open rotor" type, is schematically represented. by a cylindrical front part showing the gas generator and a larger cylindrical rear cylindrical part showing the power turbine. Unducted propellers, typically two counter-rotating propellers, are not shown. The cradle 5 is extended on the motor side by a connecting structure with arms 51, 53 connecting a plate 54, or equivalent, of the cradle to various attachment points on the engine located on structural housing elements, such as the carcass 10 of the gas generator at the front and the rear case that carries the propellers. On the opposite side of the plate are located the fixing means to the pylon. This is also a question of radial lugs arranged in coaxial alignment and in which are slid coaxial axes 31 constituting suspension members integral with the pylon, which is not otherwise shown in FIG. are part of the pylon and constitute means of attachment of the engine to the pylon. Means not shown ensure the recovery of the axial forces between the engine and the pylon. Moreover, an arm 57 of the plate, perpendicular to the latter and in which one of the lugs 55 is formed, acts as a lever arm having as a pivot axis the common axis of the lugs 55. It makes it possible to take up the vertical forces transmitted. by the engine to the pylon, including the weight of the engine. This arm 57 of the plate is mounted on the pylon so as to prevent any rotation of the plate about the axes 31. The pylon may comprise a structuring box on which are fixed the axes 31 and an interface adapted to receive the tray arm. The fairing of the pylon 3 visible in Figure 1 is set up on the box after the connection of the cradle 5 to the box.
    [0007] According to a mounting mode initially envisaged and then abandoned by the applicant, the cradle is first fixed to the engine via the connecting structure, and then the assembly is put in place on the pylon. For this purpose, the motor is shown, for example, on a transport carriage which is disposed substantially under the distal end of the pylon, and then the motor is hooked to an elevator, such as a lifting bridge, and is hoisted vertically. to bring it substantially to the same height as the axes 31, see the arrow Fv. The elevator comprises for example a beam having the shape of a horizontal beam, one end of which is connected by slings to the casing of the power turbine, and the opposite end is connected by slings to the casing of the gas generator. In this way, the motor can be moved while keeping its horizontal axis. Nevertheless, due to the fact that the tower 3 forms a non-zero angle with a horizontal plane, the simple hoisting of the motor, that is to say only a translation from bottom to top, is not sufficient. Indeed, the displacement of the cradle 5 is hindered by the pylon and in particular by the suspension members comprising the axes 31 of the pylon. The hoisting of the engine must therefore bring the cradle 5 in a position spaced from the axes 31 and be followed by a translation in the direction of the pylon to bring the motor of the pylon. In particular here, the relative positions of the engine and the tower must allow a simple horizontal displacement along the axis xx of the engine, see arrow Fh. For this purpose the axes 31 must be placed so as to be coaxial with the axes of the ears 55. During this translation, which constitutes a step of approaching the pylon, it is necessary to prevent the cradle 5 from striking the axes 31 which 25 could be damaged, given the mass of the displaced assembly, requiring intervention on the pylon. The repair of the pylon would entail significant additional costs.
    [0008] It appears that this mode of assembly, initially envisaged, is not satisfactory: the risk of damaging the axes 31 of the pylon during movement is important; moreover, the hoisting is followed by several displacements in different directions, which complicates the implementation of the assembly and requires a device for horizontally moving the elevator in at least two directions. The applicant has therefore sought a solution to overcome these disadvantages. This is shown in FIGS. 3, 4 and 5. The device of the invention comprises a cradle 6 and an intermediate part 7. The cradle 6 itself comprises a plate 64 or equivalent, extending on the motor side by a connecting structure 61, 63. This connecting structure is formed, for example, rear fasteners 61 to the rear casing which carries the propellers in the case of an "open rotor" and front fasteners 63 to the carcass of the generator of gas. The construction of the link structure is not part of the invention and will not be detailed. Any structure providing at least the function of attaching the cradle to the motor is suitable. The cradle 6 also comprises, on the opposite side to the connecting structure, a means ensuring the attachment to the pylon via the intermediate part 7. The platform 64 of the cradle is interfaced so that it can be attached to the part intermediate 7 and fixed thereto by any appropriate removable means such as by screwing or bolting. FIG. 4 shows screws 66 in position to be screwed into corresponding orifices formed in the plate of the intermediate piece 7.
    [0009] The intermediate part 7 comprises a plate or equivalent 74 interfaced on the side of the cradle so that it can be attached and fixed on the cradle 6. For example, the plate 74 may have flat surfaces constituting bearing surfaces for flat surfaces. corresponding to the tray 64 of the 3025782 8 cradle. The intermediate piece 7 is interfaced on the side of the tower so as to be mounted on the suspension members of the motor, integral with the pylon, and in particular on the axes 31 of these suspension members. This latter interface comprises two lugs 75 arranged to receive the pins 5 31. Possibly this connection comprises flexible pads, which may be for example blocks of elastomeric material or braided metal, to attenuate the engine vibrations transmitted to the cabin of the plane. A flexible stud may be integrated between an axis 31 of the pylon and an ear 75 of the intermediate piece 7. The intermediate piece is according to this embodiment provided with an arm 77 whose function is to take up the vertical forces transmitted by the engine on the pylon. This arm 77 is fixed on the pylon so as to prevent any rotation of the intermediate part 7 about the axes 31 integral with the pylon. Centering pins 67 are here provided on the plate 64 of the cradle, and 15 are able to cooperate with corresponding centering orifices (not shown) provided on the plate 74 of the intermediate part 7 so as to facilitate assembly and assembly. in place of the engine on the pylon. Alternatively, the centering pins could be provided on the plate of the intermediate piece, and the corresponding centering holes provided on the tray of the cradle. The editing operations are as follows. We first fix the cradle 6 on the engine while it is still on the ground. The intermediate piece 7 is fixed on the pylon 3 by introducing the pins 31 of the latter into the lugs 75 of the intermediate piece and the arm 77 into its housing on the pylon. The position of the intermediate part 7 about the axes 31 is thus determined: no rotation is possible. Then there is the engine equipped with the cradle 6, substantially at the free distal end of the pylon. The motor is oriented around its axis 3025782 9 so that the free interface of its plate 64 is parallel to the free interface of the plate 74 of the intermediate part. As seen in Figure 5, the motor is hoisted by vertical translation, see the arrow Tv, to the level of the intermediate part 7 already in place on the pylon. The motor is then moved perpendicular to its axis by horizontal translation, see the arrow Th, in the direction of the intermediate part 7. The centering pins 67 preferably extend parallel to the horizontal direction of translation, to be located each substantially aligned with the axis of a corresponding centering hole provided on the plate 74 of the intermediate piece 7. The pins and the centering orifices thus ensure the correct positioning of the cradle relative to the intermediate piece during the horizontal translation . Once the two plates 64 and 74 come into contact with one another and positioned in abutment with respect to one another thanks to the complementarity of the interfaces of the cradle and the intermediate part, the two plates can be connected. to the other by means of the screws 66. In other words, the intermediate part 7 has an interface adapted to cooperate with a complementary interface provided on the cradle 6 so as to ensure the setting in position of the cradle by relative to the intermediate piece at the end of the docking step of the pylon. Thanks to this immobilization, the respective trays 64 and 74 of the cradle and the intermediate piece can be connected to each other without risk of relative displacement of one with respect to the other during the operation of connection, in particular without risk of inadvertent sliding of a tray on the other while the fixing screws are put in place. It is sufficient during the binding operation to maintain the hoist 25 in the end position docking. A possible small accidental displacement of the lifting device relative to the tower will not cause displacement of the cradle 6 on the intermediate part 7, thanks to the cooperation of the two interfaces.
    [0010] In the embodiment described in the present application, the interface of the intermediate part 7 comprises the plate 74 and the orifices (not shown) corresponding to the centering pins 67. The complementary interface of the cradle 6 comprises the plate 64. and the centering pins 67. It is understood that the two interfaces can be made by other arrangements not including trays and / or centering pins, since these provisions allow to position the cradle relative to the intermediate piece at the end of the docking step of the pylon. For example, a surface having a projecting portion could be provided in place of the plate 10 of the intermediate part 7, and a surface having a recessed portion in which the projecting portion comes to fit could be provided in place of the cradle tray. The solution of the invention thus makes it possible to mount the motors which are simple to implement, reducing to a minimum the risk of damage to the engine suspension members secured to the pylon, particularly thanks to the intermediate piece whose attachment to the pylon. does not pose any particular problem and can be carried out with optimum safety for the pylon.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. A method of mounting a motor (1) on an aircraft pylon (3) comprising integral motor suspension members (31) of the pylon, the motor being secured to a suspension cradle (6) by which it is suspended in the pylon, the method comprising a step of hoisting the engine in a vertical direction to the pylon and a step of docking the pylon by a displacement of the engine in another direction, characterized in that it is fixed beforehand to pylon, by hanging on said suspension members (31), an intermediate piece (7) having an interface intended to cooperate with a complementary interface provided on the cradle (6), so as to wedge in position the cradle relative to the intermediate piece at the end of the docking of the pylon.
    [0002]
    2. Method according to the preceding claim, wherein the motor extends along an axis and the two interfaces are arranged such that the docking can be achieved by translation perpendicular to the axis of the motor.
    [0003]
    3. Method according to the preceding claim whose translation is performed in a horizontal plane.
    [0004]
    4. Method according to one of claims 1 to 3, wherein during docking the cradle is guided and positioned relative to the intermediate piece by means of pins (66) for centering provided on one of the two interfaces, said pins (66) cooperating with centering orifices provided on the other interface. 3025782 12
    [0005]
    5. Method according to one of claims 1 to 3 comprising a step of fixing the cradle (6) to the intermediate piece (7) once the cradle wedged in position relative to the intermediate piece.
    [0006]
    6. Apparatus for carrying out the method according to one of the preceding claims comprising a cradle (6) and an intermediate piece (7), the cradle being arranged to be attached to the engine by a connecting structure (61, 63), and the intermediate piece (7) being arranged to be mounted on the pylon (3) independently of the cradle (6). 10
    [0007]
    7. Device according to the preceding claim comprising means for fixing the cradle to the intermediate piece.
    [0008]
    8. Device according to the preceding claim, the fixing means comprises bolts or screws (66) connecting the cradle to the intermediate piece. 15
    [0009]
    9. Device according to one of claims 6 to 8 comprising a wedging means in position of the cradle on the intermediate piece.
    [0010]
    10. Device according to one of claims 6 to 9, the intermediate part comprises ears arranged to cooperate with the suspension members (31) integral with the pylon. 20
    [0011]
    11. Device according to the preceding claim, wherein the suspension members (31) comprise horizontal axes fixed to the pylon.
    [0012]
    12. An assembly of an aircraft and at least one engine, the engine being fixed to a tower by means of a device according to one of claims 6 to 11.
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    同族专利:
    公开号 | 公开日
    US20170259928A1|2017-09-14|
    EP3194272A1|2017-07-26|
    US10486819B2|2019-11-26|
    RU2017109393A3|2019-04-18|
    FR3025782B1|2016-09-30|
    CN107074370A|2017-08-18|
    WO2016042264A1|2016-03-24|
    BR112017004954A2|2018-04-10|
    RU2690834C2|2019-06-05|
    CA2960869A1|2016-03-24|
    EP3194272B1|2018-10-31|
    RU2017109393A|2018-10-17|
    CN107074370B|2020-02-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5524847A|1993-09-07|1996-06-11|United Technologies Corporation|Nacelle and mounting arrangement for an aircraft engine|
    EP0844174A1|1996-11-21|1998-05-27|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Redundant front suspension for a turbo engine|
    FR2920409A1|2007-08-27|2009-03-06|Airbus France Sas|BLOWER HOOD SUPPORT ROD MOUNTED ON THE HOOK AND ON THE AIR INTAKE OF THE NACELLE|
    FR2974065A1|2011-04-14|2012-10-19|Snecma|METHOD FOR MOUNTING AN AIRCRAFT ENGINE ON A PYLONE AND ENGINE ATTACHMENT FOR THE IMPLEMENTATION OF SUCH A METHOD|US20170088278A1|2015-09-24|2017-03-30|Embraer S.A.|Aircraft engine pylon to wing mounting assembly|
    US20170088279A1|2015-09-24|2017-03-30|Embraer S.A.|Aircraft engine pylon to wing mounting assembly|RU1637186C|1989-10-05|1995-01-20|Авиационный комплекс им.С.В.Ильюшина|Pylon of motor mounting on swept wing of aircraft|
    RU63320U1|2006-12-28|2007-05-27|Закрытое акционерное общество "Гражданские самолеты Сухого"|ENGINE SUSPENSION Pylon|
    FR2920408B1|2007-08-30|2010-02-19|Snecma|PYLONE OF SUSPENSION OF AN ENGINE UNDER AN AIRCRAFT WING|
    FR2950323B1|2009-09-22|2011-11-04|Airbus Operations Sas|AIRCRAFT ENGINE HANDLING MACHINE, AN ASSEMBLY COMPRISING THIS MAT AND ASSOCIATED AIRCRAFT|FR3061148A1|2016-12-23|2018-06-29|Airbus Operations|SEMI-CONTINUOUS FASTENING OF A MOTOR ATTACHING MAT TO A FIXING DEVICE BELONGING TO THE VESSEL OF AN AIRCRAFT|
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    法律状态:
    2015-09-16| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-18| PLSC| Search report ready|Effective date: 20160318 |
    2016-09-02| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-04| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 5 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458756A|FR3025782B1|2014-09-16|2014-09-16|METHOD AND DEVICE FOR MOUNTING AN ENGINE ON AN AIRCRAFT PYLON|FR1458756A| FR3025782B1|2014-09-16|2014-09-16|METHOD AND DEVICE FOR MOUNTING AN ENGINE ON AN AIRCRAFT PYLON|
    CA2960869A| CA2960869A1|2014-09-16|2015-09-16|Method and device for mounting an engine on an aircraft pylon|
    US15/510,587| US10486819B2|2014-09-16|2015-09-16|Method and device for mounting an engine on an aircraft pylon|
    RU2017109393A| RU2690834C2|2014-09-16|2015-09-16|Method and device for mounting engine on aircraft pylon|
    CN201580049298.8A| CN107074370B|2014-09-16|2015-09-16|Method, system and assembly for mounting an engine on an aircraft strut|
    BR112017004954-6A| BR112017004954A2|2014-09-16|2015-09-16|Process and device of mounting an engine on an aircraft pillar|
    PCT/FR2015/052478| WO2016042264A1|2014-09-16|2015-09-16|Method and device for mounting an engine on an aircraft pylon|
    EP15787650.9A| EP3194272B1|2014-09-16|2015-09-16|Method and device for mounting an engine on an aircraft pylon|
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