• 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 member (32) for supporting an aircraft turbine engine (10) with longitudinal axis (A) on a maintenance carriage (34), comprising at least one means for fixing said member (34). to the casing (16) of the turbomachine (10), and at least one support and articulation means configured to allow the support of said member (32) and the turbomachine (10) on the carriage (34) and the pivoting of said member (32) to a vertical position of the turbomachine (10), characterized in that it comprises a first fixing means configured to cooperate with an upper means for fixing the casing (16) of the turbomachine (10) on the aircraft, a second attachment means configured to cooperate with a first lower fixing means of the housing (16) of the turbomachine (10) dedicated to transport, and a pivot means forming the support and articulation means cooperating with complementary receiving means (44) carried by the carriage (34).
    公开号:FR3058987A1
    申请号:FR1661457
    申请日:2016-11-24
    公开日:2018-05-25
    发明作者:Alexandre Dervaux；Roland Crochemore Yves；Franck DUBREUCQ；Thibaud MANGIN
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Technical field of the invention:
    The present invention relates to the attachment of power units to aircraft. It relates more particularly to a member, a removal kit, and a method for the removal of a turbomachine from an aircraft, a method of immobilizing and transporting this turbomachine after its removal, and a method of maintenance in vertical position of this turbomachine after its removal and / or after its transport.
    State of the art :
    When it is desired to intervene on a turbomachine, it is necessary to remove it from the aircraft in which it is mounted before considering any maintenance intervention. Thus, it is known to provide a removal carriage enabling the turbomachine to be received during its removal.
    In most cases, the turbomachine is mounted in the aircraft in a substantially horizontal position, and it is received substantially horizontally on the carriage. Such a configuration is for example known from documents US-6,292,999-B1 or EP-0.038.227-A1.
    It may also occur that the turbomachine is mounted vertically in the aircraft, and in this case the turbomachine is received substantially vertically on the depositing carriage, then tilted thereon as described for example in document FR-1,467,339- AT. To this end, the turbomachine is previously mounted in a frame which is then pivotally received on the removal carriage. This frame is particularly bulky. In addition, the carriage is not intended to maintain the turbomachine in a vertical position, this position being only a transient position intended to ensure the reception of the turbomachine before its final positioning in a horizontal position.
    The removal carts known from the prior art are essentially used for short-distance transport of the turbomachine from the aircraft to a maintenance workshop dedicated to maintenance interventions, or from the aircraft to a another trolley, specifically dedicated to long distance transport, for its transport by air or road.
    Removal trolleys known from the state of the art, which ensure the stability of the turbomachine only in a horizontal position, in any event do not make it possible to envisage maintenance operations of great complexity, but can at best allow minor operations carried out in a horizontal position, such as the replacement of peripheral accessories of the turbomachine. This type of removal carriage does not in any case allow intervention on the structure of the turbomachine, and it does not in particular allow the replacement of modular elements of the turbomachine, this type of operation requiring vertical positioning of the turbomachine.
    In fact, by construction, a turbomachine is produced in the form of an assembly of modules, for example a blower module, compressor modules, a combustion chamber module, and turbine modules. At least the compressor and turbine modules include a rotor element received in a stator or casing element which is paired with the rotor element. When it is desired to replace a compressor or turbomachine turbine module, the compressor or turbine rotor or rotors and the stators or housings associated therewith are simultaneously replaced.
    Such a replacement can therefore only be carried out in a vertical position of the turbomachine. Therefore, it can not be performed on the carriage used for the removal of the turbomachine, because it ensures the stability of the turbomachine only in a horizontal position. Indeed, the removal carriages that allow the vertical reception of the turbomachine are not intended to ensure its maintenance in this position, and do not provide sufficient stability to it to consider maintenance.
    Document FR-2,952,922-A1 discloses a handling assembly allowing the tilting of a turbomachine between a horizontal position and a vertical position in order to facilitate assembly from modules when they exit from the body. Such a handling assembly is not mobile because it is reserved for assembly in the workshop. As a result, it cannot be routed to an aircraft.
    Furthermore, whether they are removal carts or handling assemblies known in the art, none of these devices is designed to be loaded on a vehicle, whether it is a road vehicle or of an aircraft, because it does not offer sufficient clamping of the turbomachine for its transport.
    There is therefore a need for a carriage making it possible both to carry out the removal of the turbomachine, and / or to perform complex maintenance operations in the vertical position of said turbomachine, and / or to provide air or road transport of the turbomachine stably.
    This need is particularly acute in regions that do not have dedicated maintenance workshops near the runways, and do not always offer a replacement turbomachine in the event of failure.
    A conventional turbomachine 10 has different types of fasteners, as illustrated in FIG. 1.
    In known manner, in its upper part 12, the turbomachine 10, of longitudinal axis A, conventionally comprises upper means 14 for fixing a casing 16 of the turbomachine to the aircraft, which are arranged on either side other of the turbomachine 10. These upper fixing means 14 allow the turbomachine 10 to be suspended from a pylon (not shown) fixed under the wing of the aircraft. These upper fixing means 14 cannot be used alone to support the total weight of the turbomachine 10 in a vertical position.
    In a lower part 18, the turbomachine 10 comprises, in a conventional manner, first lower fixing means 20 for the casing 16 of the turbomachine dedicated to transport, which are arranged in an upstream part 22 of the turbomachine 10 on either side of the turbomachine 10. The upstream part 22 is a part close to a fan 24 of the turbomachine 10.
    In the lower part 18, the turbomachine 10 also conventionally comprises second lower fixing means 26 for the casing 16 of the turbomachine 10 dedicated to transport, which are arranged in a downstream part 28 of the turbomachine 10. This downstream part 28 is a part close to an exhaust nozzle 30 of the turbomachine 10. It will be understood that the terms “upstream” and “downstream” are defined by reference to the direction of flow of the gases in the turbomachine 10.
    The first and second lower fixing means 20, 26 are also arranged on either side of the casing 16 of the turbomachine 10. These first and second lower fixing means 20, 26 cannot be used alone to support the total weight of the turbomachine 10 in a vertical position.
    Presentation of the invention:
    The invention takes advantage of the coexistence of the upper fixing means and of the first and second lower fixing means to allow the support of the turbomachine in a carriage corresponding to the needs mentioned above, this carriage allowing the removal of the turbomachine, the transport of the turbomachine, and maintenance operations in the vertical position carried out on the turbomachine, without requiring transfer from the turbomachine to a carriage or a frame specifically dedicated to only one of these uses.
    To this end, the invention firstly proposes a support member cooperating with the upper fixing means and the first lower fixing means of the turbomachine.
    To this end, the invention firstly proposes a member for supporting an aircraft turbomachine of longitudinal axis A on a maintenance trolley, after lowering and depositing said turbomachine from an aircraft to which the turbomachine is fixed, said member being configured to be fixed to a casing of the turbomachine and comprising at least one means for fixing said member to the casing of the turbomachine, and at least one support and articulation means configured to allow support for said member and of the turbomachine on the carriage and the pivoting of said member accompanied by the turbomachine about a substantially horizontal axis, between at least one position where the axis A is horizontal and a position where the axis A is vertical, characterized in that that the member comprises a first fixing means configured to cooperate with an upper means for fixing the casing of the turbomachine to the aircraft, a second fixing means configured to cooperate with a first means at the bottom for fixing the casing of the turbomachine dedicated to transport, and in that the support and articulation means comprise a pivot means configured to cooperate with a complementary reception means carried by the carriage.
    According to another characteristic of the member, the latter being considered with respect to so-called internal and external orientations according to which the internal orientation corresponds to an orientation facing the turbomachine and the internal orientation corresponding to an orientation facing the opposite to the turbomachine, the member is shaped in the form of a first arm, configured to be fixed laterally to the turbomachine and to extend in a plane transverse to its axis A in an upstream part of the casing of said turbomachine, opposite ends of said first arm comprising on an internal side of the first arm respectively the first and second fixing means, and an intermediate part of said first arm comprising, on the external side of said first arm, an axis forming the pivot means of the support and articulation, said axis being able to cooperate with a yoke of said carriage formed in the complementary reception means of said carriage.
    The invention secondly proposes a support kit for an aircraft turbomachine of longitudinal axis A on a maintenance trolley substantially symmetrical along an orientation axis B and comprising a pair of receiving means opposite transversely to said axis B, characterized in that it comprises a pair of members of the type described above, said members being configured to be fixed by their internal sides in the same plane transverse to the axis A on either side of a upstream part of the casing of the turbomachine and to cooperate complementarily by their external sides with the receiving means carried by the carriage.
    The invention thirdly proposes a maintenance trolley for an aircraft turbomachine of longitudinal axis A, characterized in that it comprises a chassis extending substantially symmetrically on either side of an orientation axis B which includes:
    - A pair of receiving means, opposite transversely to said axis B, which are arranged substantially near a first longitudinal end of the carriage, and which are configured to receive between their internal sides a support kit of the type described above fixed at the upstream part of the casing of said turbomachine, and cooperate with said support kit,
    - A pair of clamping means, opposite transversely to said axis B, which are arranged substantially near a second longitudinal end of the carriage, and which are configured to receive between their internal sides a downstream part of the casing of the turbomachine in the horizontal position of the axis of said turbomachine and to be fixed thereto,
    rolling means, fixed under said chassis,
    - At least one autonomous tilting means, which is configured to cause the tilting of the support kit between the horizontal position and the vertical position of the turbomachine.
    According to other characteristics of the cart:
    - The carriage is configured to cooperate with members of the type described above, and each receiving means comprises a second substantially vertical arm, one free end of which comprises the clevis for receiving the axis of the pivot means of the first arm forming the member. corresponding,
    each clamping means comprises a third substantially vertical arm, one free end of which comprises means for fixing to a second lower means for fixing the casing of the turbomachine dedicated to transport, arranged in a downstream part of the turbomachine, and
    - The autonomous tilting means is configured to drive in rotation at least one of the bodies in rotation around the pivot means.
    These organs, kit and carriage can be implemented in a method of removing an aircraft turbomachine, the removal being carried out on the carriage of the type described above, using the kit of members as described above. This process is characterized in that it comprises at least:
    a first step during which the turbomachine is supported relative to the aircraft and then during which it is separated from the aircraft,
    a second step during which the two components of the kit are fixed to the casing of the turbomachine,
    a third step during which the carriage is positioned under the turbomachine so that the axis of the turbomachine and the axis of the carriage are arranged in the same vertical plane, and so that the axes of the pivot means of the members are arranged in line with the yokes for receiving the carriage,
    a fourth step during which the turbomachine is lowered with respect to the carriage until the axes of the pivot means of the members penetrate into the yokes of the means for receiving the carriage, and the second lower means of fixing of the turbomachine casing dedicated to transport comes into contact with the arm of the corresponding clamping means.
    These organs, kit and carriage can also be implemented in a method of immobilizing / transporting in an horizontal position an aircraft turbomachine. This process is characterized in that it takes place at the end of a removal process of the type described above and in that it comprises at least one locking step during which the axes of the pivot means are locked in the yokes and the second lower means for fixing the casing of the turbomachine with the arm of the corresponding clamping means.
    These organs, kit, and carriage can finally be implemented in a maintenance method in an vertical position of an aircraft turbomachine.
    This process is characterized in that it is implemented on a trolley of the type described above, in that it takes place at the end of a removal process and / or an immobilization process of the above type described, and in that it comprises at least:
    a first step during which a fan of the turbomachine is deposited,
    a second step during which the unlocking of the second lower means for fixing the casing of the turbomachine is ensured with the arm of the corresponding clamping means,
    a third step during which the autonomous tilting means are actuated to tilt the turbomachine from the horizontal position to the vertical position of its axis,
    a fourth step during which at least one maintenance operation is carried out in the vertical position of the turbomachine.
    Brief description of the figures:
    The invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the description which follows, given by way of nonlimiting example and with reference to the appended drawings, in which:
    - Figure 1 (already described) is a perspective view of a turbomachine and its upper and lower fixing means;
    - Figure 2 is a perspective view of the turbomachine of the figure equipped with a kit of members according to the invention;
    - Figure 3 is an end view of the turbomachine of Figure 2 equipped with its component kit;
    - Figure 4 is a perspective view of the turbomachine received on the carriage in the horizontal position;
    - Figure 5 is a side view of the turbomachine received on the carriage in a horizontal position;
    - Figure 6 is a perspective view of the turbomachine received on the carriage in the vertical position;
    - Figure 7 is a perspective view of the turbomachine fitted with variant bodies of the invention received on a variant invention trolley in a horizontal position;
    - Figure 8 is a perspective view of the turbomachine received on the carriage of Figure 7, the turbomachine occupying a vertical position;
    - Figure 9 is a block diagram illustrating the steps of a removal process according to the invention;
    - Figure 10 is a block diagram illustrating the step of an immobilization / transport method according to the invention; and
    - Figure 11 is a block diagram illustrating the steps of a vertical position maintenance method according to the invention.
    Detailed description :
    In the following description, identical reference numerals designate identical parts or having similar functions.
    FIGS. 2 and 3 show members 32 arranged on either side of the turbomachine 10. These members 32 are intended to support the turbomachine 10 on a maintenance carriage 34, of the type which has been shown in Figures 4 to 6, the turbomachine 10 having been previously removed and lowered from the aircraft to which it was attached. The members 32 are two in number, and thus form a support kit that can be adapted to the turbomachine 10.
    As illustrated in FIGS. 2 and 3, the members 32 are generally configured to be fixed to the casing 16 of the turbomachine 10 and each member 32 comprises at least one fixing means 36, 38 of said member 32 to casing 16 of the turbomachine, and at least one support and articulation means 40.
    The support and articulation means 40 is configured, as illustrated in FIGS. 4 to 6, to allow the support of said member 32 and of the turbomachine to which it is fixed on the carriage 34, and the pivoting of said member 32 accompanied of the turbomachine 10 around a substantially horizontal axis T, between at least one position where the axis A of the turbomachine 10 is horizontal, as shown in FIGS. 4 and 5, and a position where the axis A of the turbomachine 10 is vertical, as shown in Figure 6.
    According to the invention, each member 32 comprises a first fixing means 36 which is configured to cooperate with the upper means 14 for fixing the casing 16 of the turbomachine 10 to the aircraft, and a second fixing means 38 which is configured to cooperate with the first lower means 20 for fixing the casing 16 of the turbomachine 10 dedicated to transport. In FIG. 3, the fixing means 36, 38 of the member 32 are shown in the form of single faces of said member 32 which are turned towards the turbomachine 10 and which are in contact respectively with the upper fixing means 14 and the first lower fixing means 20. In particular, the detail of the fixing of the fixing means 36, 38 has not been shown and it will be understood that it can take any known form capable of ensuring a rigid connection. It will be understood that this arrangement is not limiting of the invention and that other interfaces between the turbomachine 10 and the arms 32 can be envisaged.
    Each member 32 also comprises the support and articulation means 40, which more particularly comprises a pivot means 42 which is configured to cooperate with a complementary reception means 44 carried by the carriage 34, as shown in FIGS. 4 to 6.
    More particularly, as illustrated in FIG. 3, each member 32 is shaped in the form of a first arm 32, configured to be fixed laterally to the turbomachine 10 on an internal side 31 of the first arm 32. The first arm 32 extends, as illustrated in FIGS. 3 and 5, in a plane P which is transverse to the axis A of the turbomachine 10 and which is located in the upstream part 22 of the casing 16 of said turbomachine 10. This plane P has been shown in Figures 3 and 5 in the position where the axis A of the turbomachine 10 is horizontal.
    Opposite ends 48, 50 of each first arm 32, with respect to its general direction, respectively comprise the first and second fixing means 36, 38 which, on the internal side 31 of the first arm 32, are turned towards the turbomachine 10 of so as to cooperate with the upper means 14 for fixing the casing 16 and with the first lower means 20 for fixing the casing 16. Each first arm 32 furthermore has, on an external side 35 of the first arm 32 opposite the side 31, a axis 42 forming the pivot means of the support and articulation means 40. This axis 42 is able to cooperate with a yoke 45 of said carriage 34 formed in the receiving means 44 complementary to said carriage 34.
    The first and second fixing means 36, 38 can take any form known from the state of the art, as long as they cooperate with the upper means 14 for fixing the casing 16 and with the first lower means 20 for fixing the casing 16. As the detail of embodiment of this assembly is not the subject of the invention, it will not be described more explicitly in the remainder of this description.
    In their simplest form, the arms 32 can be independent, as shown in FIGS. 3 to 6. In an alternative form of writing of the invention which has been shown in FIGS. 7 and 8, the arms 32 can at otherwise be part of a frame 33 having substantially a U-shape, in which is received the turbomachine 10.
    This latter configuration makes it possible to improve the rigidity of the assembly of the arms 32 and of the turbomachine 10.
    Once the turbomachine 10 has been fitted with a fixing kit comprising the two arms 32 fixed by their internal sides 31 to the casing 16 of the turbomachine 10, it is received on the carriage 34. The carriage 34 comprises a chassis 52, preferably made in mechanically welded construction, which extends substantially symmetrically on either side of an orientation axis B, as has been shown in Figures 4, 6, 7, and 8. When one descends the turbomachine 10 on the carriage 34, it is ensured that the axis A of the turbomachine 10 and the axis B of the carriage 34 are superimposed in the same vertical plane, so as to substantially center the turbomachine 10 relative to the carriage 34.
    The chassis 52 preferably comprises a frame 55 which is fixed to the chassis 52 by means of damping elements 57, which are for example produced in the form of elastomer pads 57 of the "silentbloc" type.
    As illustrated in FIGS. 4 to 6, the carriage 34 comprises a pair of receiving means 44, carried by the frame 55 and arranged transversely with respect to the axis B, and which are each intended to receive the axis 42 forming the pivot means of the support and articulation means 40. The two reception means 44 are intended to receive between their internal sides 43 the support kit and to cooperate with the two axes 42 of the support kit, which are carried by the outer sides 35 of the arms 32. The receiving means 44 are preferably arranged substantially at one end of the frame 55, near a first longitudinal end 54 of the carriage 34.
    The carriage 34 also comprises a pair of clamping means 56, transversely opposite with respect to the axis B, which are carried by the frame 55 and which are preferably arranged at the other end of the frame 55, substantially close to a second longitudinal end 58 of the carriage 34, that is to say substantially opposite to the pair of receiving means 44. The clamping means 56 are configured to receive between their internal sides 59 the downstream part 28 of the casing 16 of the turbomachine 10 in the horizontal position of the axis A of said turbomachine, and to be fixed thereto.
    The carriage 34 also comprises rolling means 46 which are fixed under the chassis 52. In FIGS. 4 to 6, these rolling means 46 have been shown in their simplest form in the form of wheels 46 arranged at the four corners of the chassis 52. However, as illustrated in FIGS. 7 and 8, these rolling means comprise plates 60, which are pivotally mounted at the four corners of the frame 52, and which receive rollers 62, as shown in FIGS. 7 and 8. This configuration allows to move and orient the carriage 34 in all directions. It will also be noted that, in known manner, the plates 60 can be equipped with means for blocking the rollers 62, in order to immobilize the carriage 34 in a determined position.
    Finally, the carriage 34 comprises at least one autonomous tilting means, which is configured to cause the tilting of the support kit between the horizontal position and the vertical position of the axis A of the turbomachine 10. In FIGS. 4 to 6, which represent the general principle of operation of the carriage 34, this autonomous means has not been shown. In FIGS. 7 and 8, the autonomous tilting means 64 has been shown in the form of a hydraulic pump 66, actuated by a lever 68, which is capable of supplying oil to a jack 70 which is interposed between the frame 55 of the carriage 34 and one of the arms 32 of the frame 33. Thus, the autonomous tilting means 64 is configured to rotate at least one of the members 32 in rotation around the pivot means 42, and in doing so, to cause the tilting of the turbomachine 10, driven by this first arm 32.
    It will be understood that this configuration is not limiting of the invention, and that the autonomous means 64 can take other forms known in the art provided that it does not require for its current operation any fixed supply of electric flow or hydraulic. On the other hand, the autonomous means 64 could consist of an electric jack powered by a rechargeable battery. It is in fact desirable that the autonomous means 64 can be used, for example, near an aircraft at the end of the runway or in any other place devoid of recharging means in the immediate vicinity.
    The autonomous means 64 may, depending on its configuration, be sufficient to block the turbomachine 10 in a vertical position. However, it is possible to provide a means for blocking the turbomachine 10 in a vertical position.
    Preferably, each receiving means 44 comprises a second substantially vertical arm 72, carried by the frame 55, one free end of which comprises the yoke 45 for receiving the axis 42 of the pivot means 40 of the corresponding first arm 32.
    Each clamping means 56 comprises, meanwhile, a third substantially vertical arm 74, carried by the frame 55, one free end of which comprises a fixing means (not shown) to one of the second lower fixing means 26 dedicated to transport which is arranged in the downstream part 28 of the turbomachine 10. As illustrated in FIG. 6, this third arm 74 can in particular be removable and / or retractable, to facilitate access to the turbomachine 10 when it is tilted with its axis A vertically, in order to allow an operator to intervene on said turbomachine 10 without risking to interfere with this third arm 74. It will be understood that the third arms 74 can therefore be indifferently removable or simply retractable.
    In this configuration, the members 32, used in the form of a kit, and the carriage 34 can be used in various ways.
    With the aid of these elements, as illustrated in FIG. 9, it is first possible to proceed with the removal of an aircraft turbomachine 10 on a carriage 34 by means of a kit of the type described above, by operating in a first step ET1 during which, the turbomachine 10 being in place in the aircraft, one begins by supporting the turbomachine and detaching it from the aircraft. Then, during a second step ET2, the two members 32 of the kit are fixed to the casing 16 of the turbomachine 10. Then, during a third step ET3, the carriage 34 is positioned transversely under the turbomachine 10 of so that the axis A of the turbomachine 10 and the axis B of the carriage 34 are arranged in the same vertical plane. The carriage 34 is also positioned longitudinally so that the axes 42 of the pivot means 40 of the members 32 are arranged in line with the yokes 45 of the reception means 44 of the carriage 34. Then, during a fourth step ET4, lower the turbomachine 10 with respect to the carriage 34 until the axes 42 of the pivot means 40 of the members 32 penetrate into the yokes 45 of the receiving means 44 of the carriage 34, and the second lower fixing means 26 of the turbomachine casing dedicated to transport comes into contact with the arm 74 of the corresponding clamping means 56.
    In this configuration, the turbomachine 10 rests stably by gravity on the carriage 34, as shown in FIGS. 4 to 8.
    If it is desired to immobilize and / or transport the turbomachine 10 in a horizontal position, as may be necessary in the case of road or air transport, it is necessary to clamp the turbomachine 10 on the carriage 34 so to ensure its stability.
    For this purpose, as illustrated in FIG. 10, at the end of a removal process of the type described above, the immobilization or the transport of the turbomachine 10 is carried out at least one locking step ET5 during which is locked on the one hand the axes 42 forming the pivot means in the yokes 45 and on the other hand the second lower means for fixing the casing of the turbomachine 26 directly with the arm 74 of the corresponding clamping means 56. In this case, the turbomachine 10 not only rests on the frame 55 of the carriage 34, but it is clamped there so that it cannot escape from it if it is subjected to a vertical acceleration which may be caused by a jolt in the in the case of road transport, or through an air hole in the context of air transport.
    A particularly advantageous characteristic of the invention is that, after the removal of the turbomachine 10 and / or from this clamped position, it is possible to carry out maintenance of the turbomachine 10 in a vertical position directly on the carriage 34, without the need to transfer the turbomachine to another carriage or to another frame specially dedicated to this operation.
    It is indeed possible to carry out maintenance of the turbomachine, after a simple removal, or after its clamping 10. As illustrated in FIG. 11, a maintenance method according to the invention thus comprises a first step ET6 during which the fan 24 of the turbomachine 10 is deposited. The purpose of this operation is to limit the vertical size of the turbomachine 10 once its axis A occupies its vertical position. Then in the course of a second step ET7, it is ensured that each second lower fixing means 26 of the casing of the turbomachine is unlocked with the third arm 74 of the corresponding clamping means 56. Then, during a third step ET8, the autonomous tilting means 64 are actuated to tilt the turbomachine from the horizontal position of its axis A to its vertical position, as shown in FIGS. 6 and 8. It will be noted that in this position it is possible, if the carriage 34 is equipped with means for locking the arms 32 in the vertical position, to block the turbomachine 10 in this position.
    Finally, during a fourth step ET9, at least one maintenance operation is carried out in the vertical position of the turbomachine 10, for example the replacement of one or more modules of the turbomachine 10.
    The invention therefore makes it possible to significantly reduce the tools used in the context of the removal, transport and maintenance operations of a turbomachine 10, and in particular makes it possible to route these tools, combined in one, in a less bulky manner than the devices known from the state of the art, near the aircraft which must be maintained.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Body (32) for supporting a turbomachine (10) of an aircraft with a longitudinal axis (A) on a maintenance carriage (34), after lowering and depositing said turbomachine (10) from a aircraft to which the turbomachine (10) is fixed, said member (32) being configured to be fixed to a casing (16) of the turbomachine (10) and comprising at least one fixing means (36, 38) of said member (34) the casing (16) of the turbomachine (10), and at least one support and articulation means (40) configured to allow the support of said member (32) and of the turbomachine (10) on the carriage (34) and the pivoting of said member (32) accompanied by the turbomachine (10) about a substantially horizontal axis (T), between at least one position where the axis (A) is horizontal and a position where the axis (A) is vertical, characterized in that it comprises a first fixing means (36) configured to cooperate with an upper means (14) for fixing the casing (16) of the turbomachine (10) on the aircraft, one of uxth fixing means (38) configured to cooperate with a first lower fixing means (20) of the casing (16) of the turbomachine (10) dedicated to transport, and the support and articulation means (40) which comprises a pivot means (42) configured to cooperate with complementary reception means (44) carried by the carriage (34).
    [2" id="c-fr-0002]
    2. Body (32) according to the preceding claim, characterized in that it is shaped in the form of a first arm (32), configured to be fixed laterally to the turbomachine (10) and to extend in a plane (P) transverse to its axis (A) in an upstream part (22) of the casing of said turbomachine, opposite ends (48, 50) of said first arm (32) comprising respectively, on an internal side (31) of said first arm (32), the first and second fixing means (36, 38), said first arm (32) comprising, on an external side (35) of said first arm (32) opposite to the internal side, an axis (42) forming the pivot means of the support and articulation means (40), said axis (42) being able to cooperate with a yoke (45) of said carriage (34) formed in the complementary receiving means (44) of said carriage ( 34).
    [3" id="c-fr-0003]
    3. Support kit for an aircraft turbomachine with a longitudinal axis A on a substantially symmetrical maintenance carriage (34) along an orientation axis (B) and comprising a pair of receiving means (44) opposite transversely by relative to said axis (B), characterized in that it comprises a pair of members (32) according to claim 2, said members (32) being configured to be fixed by their internal sides (31) in the same plane (P ) transverse to the axis (A) on either side of an upstream part (22) of the casing (16) of the turbomachine (10) and to cooperate complementarily by their external sides (35) with the receiving means (44) carried by the carriage (34).
    [4" id="c-fr-0004]
    4. Maintenance trolley (34) for a turbomachine (10) of an aircraft with a longitudinal axis (A), characterized in that it comprises a chassis (52) extending substantially symmetrically on either side of an orientation axis (B) which comprises:
    - a pair of receiving means (44), transversely opposite with respect to said axis (B,) which are arranged substantially near a first longitudinal end (54) of the carriage, and which are configured to receive between their internal sides ( 43) a support kit according to claim 3 fixed to the upstream part (20) of the casing (16) of said turbomachine (10), and cooperating with said support kit,
    - a pair of clamping means (56) opposite transversely to said axis B, which are arranged substantially near a second longitudinal end (58) of the carriage (34), and which are configured to receive between their internal sides ( 59) a downstream part (28) of the casing (16) of the turbomachine (10) in the horizontal position of the axis A of said turbomachine (10), and to be fixed there,
    rolling means (46), fixed under said chassis (52),
    - at least one autonomous tilting means (64), which is configured to cause the tilting of the support kit between the horizontal position and the vertical position of the axis (A) of the turbomachine (10).
    [5" id="c-fr-0005]
    5. Maintenance trolley (34) according to the preceding claim, characterized in that it is configured to cooperate with members (32) according to claim 2, and in that each receiving means (44) comprises a second arm ( 72) substantially vertical, one free end of which comprises the receiving yoke (45) of the axis (42) forming the pivot means of the corresponding first arm (32).
    [6" id="c-fr-0006]
    6. Maintenance trolley (34) according to one of claims 4 or 5, characterized in that each clamping means (56) comprises a third substantially vertical arm (74) of which a free end comprises a means of attachment to a second lower fixing means (26) of the casing (16) of the turbomachine (10) dedicated to transport, arranged in a downstream part (28) of the turbomachine.
    [7" id="c-fr-0007]
    7. Maintenance trolley (34) according to one of claims 4 to 6, characterized in that the autonomous tilting means (64) is configured to drive in rotation at least one of the members (32) in rotation around the means of pivot (42).
    [8" id="c-fr-0008]
    8. Method for depositing an aircraft turbomachine (10) on a carriage (34) according to one of claims 6 or 7, by means of a kit according to claim 3 comprising members (32) according to claim 2, characterized in that it comprises at least:
    - a first step (ET1) during which the turbomachine (10) is supported relative to the aircraft and then during which it is detached from the aircraft,
    a second step (ET2) during which the first two arms (32) are fixed, forming the components of the kit on the casing (16) of the turbomachine (10),
    - a third step (ET3) during which the carriage (34) is positioned under the turbomachine (10) so that the axis (A) of the turbomachine (10) and the axis of the carriage (B) are arranged in the same vertical plane, and so that the axes (42) of the pivot means of the members (34) are arranged in line with the yokes (45) of the second arms (72) of the receiving means (44) of the carriage 34) ,
    - A fourth step (ET4) during which the turbomachine (10) is lowered with respect to the carriage until the axes (42) of the pivot means of the members (32) penetrate into the yokes (45 ) receiving means (44) of the carriage (34), and that the second lower fixing means (26) of the casing (16) of the turbomachine (10) dedicated to transport comes into contact with the third arm (74) of the corresponding clamping means (56).
    [9" id="c-fr-0009]
    9. Method for immobilizing / transporting in an horizontal position an aircraft turbomachine (10), characterized in that it takes place at the end of a removal process according to the preceding claim and in that it comprises at least one locking step (ET5) during which the axes (42) of the pivot means are locked in the yokes (45) of the second arms (78) and the second lower fixing means (26) of the casing (16 ) of the turbomachine with the third arm (74) of the corresponding clamping means (56).
    [10" id="c-fr-0010]
    10. A method for maintenance in an vertical position of an aircraft turbomachine, characterized in that it is implemented on a carriage (34) according to claim 7, in that it intervenes at the end of a removal process according to claim 8 and / or at the end of an immobilization process according to the preceding claim and in that it comprises at least:
    - a first step (ET6) during which a fan (24) of the turbomachine (10) is deposited,
    - A second step (ET7) during which one ensures the unlocking of the second lower fixing means (26) of the casing (16) of the turbomachine (10) with the arm (74) of the clamping means (56) corresponding,
    - a third step (ET8) during which the autonomous tilting means (64) are actuated to tilt the turbomachine (10) from the horizontal position to the vertical position of its axis (A),
    - A fourth step (ET9) during which at least one maintenance operation is carried out in the vertical position of the turbomachine (10).
    1/4
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    同族专利:
    公开号 | 公开日
    US20180142576A1|2018-05-24|
    FR3058987B1|2019-08-02|
    US10550728B2|2020-02-04|
    引用文献:
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    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-25| PLSC| Publication of the preliminary search report|Effective date: 20180525 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661457|2016-11-24|
    FR1661457A|FR3058987B1|2016-11-24|2016-11-24|ORGAN AND TROLLEY FOR THE REMOVAL, TRANSPORT, AND MAINTENANCE OF A TURBOMACHINE|FR1661457A| FR3058987B1|2016-11-24|2016-11-24|ORGAN AND TROLLEY FOR THE REMOVAL, TRANSPORT, AND MAINTENANCE OF A TURBOMACHINE|
    US15/821,631| US10550728B2|2016-11-24|2017-11-22|Assembly for the removal, transportation, and maintenance of a turbine engine|
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