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    • 专利摘要:
    Structure (310) for transporting and hoisting a turbomachine (312), comprising a hoisting interface (328) arranged on a rigid hoisting arm (318) which extends above the turbomachine and which is connected to a rigid transport arm (316) which extends on a lateral side of the turbomachine, this transport arm being connected to at least two engine supports (340) integral with the turbomachine. The transport arm (316), or one of the engine supports connected to this transport arm, comprises a transport interface (324) adapted to be supported by a carrier element (332) of a transport carriage (326). of the turbomachine.
    公开号:FR3017112A1
    申请号:FR1400286
    申请日:2014-02-03
    公开日:2015-08-07
    发明作者:Thierry Kohn；Stephane Baucher；Damien Cesar；Alexandre Dervaux；Franck Dubreucq；Thibaud Mangin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to a transport and hoisting structure for a turbomachine or a turbomachine module, in particular an aircraft. STATE OF THE ART In the current technique, a turbomachine is transported by means of a transport trolley. This transport carriage allows for example to move (horizontally) the turbomachine in a shed, after dismantling the turbomachine of an aircraft or before mounting it on the aircraft. The turbomachine is equipped with dedicated interfaces to cooperate with the transport carriage, these interfaces being called transport interfaces. The mounting of the turbomachine on the aircraft, and in particular on the connecting pylon of the turbomachine to the aircraft, requires a hoisting operation of the turbomachine, that is to say a lifting operation (vertical displacement) the turbomachine to extract it from the transport trolley. For this, the turbomachine is equipped with dedicated interfaces to cooperate with a lifting member, these interfaces being called hoisting interfaces. Conventionally, the transport interfaces are located in a lower or lower part of the turbomachine and the hoisting interfaces are located in an upper or upper part thereof. In general, the transport interfaces are four in number, two upstream and two at the rear of the turbomachine, and the hoist interfaces are also four in number, two in the upstream and two in the back of the turbomachine. A turbomachine is thus equipped with eight distinct interfaces, which must remain free, which considerably constrains the space allocated to certain equipment of the turbomachine, such as in particular electrical harnesses.
    [0002] It has already been proposed to solve this congestion problem by equipping a turbomachine with interfaces serving both for hoisting and transport, that is to say interfaces having a dual function of hoisting and transport. The patent application EP-A1-0 089 866 describes in this regard a combined attachment device for transporting and hoisting a turbomachine, this device comprising means for fixing the transport trolley and hoisting means for hoisting the turbomachine. The fixing and hoisting means are connected to the same interfaces of the turbomachine, which are thus transport and hoisting interfaces.
    [0003] In the current technique, technical transport and hoisting solutions are designed for a turbomachine intended to be mounted under the wing of an aircraft. The turbomachine is suspended from the wing by means of a pylon which is located at 12 o'clock (12 o'clock) by analogy with the dial of a clock. The turbomachine is thus equipped at 12h suspension interfaces dedicated to the connection of the turbine engine to the pylon. These suspension interfaces are distinct from the transport and hoisting interfaces and do not interfere with the hoisting operation. Indeed, the transport and hoisting interfaces, which are located on the sides of the turbomachine (for example at 8 o'clock and 10 o'clock), do not interfere with the attachment of the pylon to the suspension interfaces located at 12 o'clock. However, these solutions are not suitable when the turbomachine is intended to be mounted on one side of the fuselage of the aircraft. Indeed, in this case where the suspension interfaces of the turbomachine are located on one side of the latter, the hoisting operation of the turbomachine is more complex because the hoisting means can interfere with the linkage of the pylon to the suspension interfaces. There is therefore a real need for a technology allowing a turbomachine intended to be fixed on one side of the fuselage of an aircraft to be equipped with interfaces serving both for hoisting and transport, and possibly also for suspension, of this turbomachine.
    [0004] The present invention provides a simple, effective and economical solution to this need. DESCRIPTION OF THE INVENTION The invention proposes a transport and hoisting structure, installed on a turbomachine or on a turbomachine module which has a central longitudinal axis forming an angle between 0 ° and 10 ° relative to the horizontal, the structure comprising: at least two transport interfaces rigidly connected to the turbomachine, located on either side of the turbomachine relative to a median vertical plane P comprising said central longitudinal axis and each adapted to be supported by a carrier element; a carriage for transporting the turbomachine, at least one hoisting interface rigidly connected to the turbomachine, suitable for being connected to a lifting member intended to hoist the turbomachine, and motor supports integral with the turbomachine, characterized in that said at least one hoisting interface is disposed on a rigid hoisting arm which extends at least partly above the turbomachine and that i crosses said median vertical plane P, said hoisting arm being connected to a rigid transport arm which is connected to at least two of said engine supports, the engine supports connected to this transport arm being situated on the same side of the turbomachine relative to the median vertical plane, and in that the transport arm or one of the engine supports connected to this transport arm comprises one of said at least two transport interfaces. The structure according to the invention thus comprises the two transport and hoisting interfaces of the turbomachine, each of which is carried by a rigid arm. The transport interface is carried by the transport arm, which transport arm carries this interface either directly or via a motor support. The hoisting interface is carried by the hauling arm which is connected to the transport arm. The use of such arms allows the mounting of the turbomachine on one side of the fuselage of an aircraft. Indeed, the turbomachine is hoisted by means of the hoist arm which extends above the turbomachine and which does not interfere with the connection of a first side (for example left) of the turbine engine to the pylon of the aircraft. In addition, the hoist arm is connected to a transport arm which is connected to the turbomachine via engine supports which are located on only one side of the turbomachine, namely its second side (right, in the example above). The transport arm can thus extend only at this second side of the turbomachine and not interfere with the connection of the first side of the turbomachine to the pylon of the aircraft. The structure according to the invention is therefore particularly suitable, but not exclusively, for mounting a turbomachine on one side of the fuselage of an aircraft. During its transport, the turbomachine has a central longitudinal axis forming an angle between 0 ° and 10 ° relative to the horizontal, that is to say that the turbomachine is substantially horizontal or slightly inclined relative to the horizontal axis. horizontal. The hauling arm can be formed in one piece with the transport arm. Alternatively, the hauling arm is fixed, preferably removably, to the transport arm. According to one embodiment of the invention, the transport arm 25 comprises a main rectilinear portion connected to a lower rectilinear portion which forms an angle with the main rectilinear portion and which is connected to a lower engine support integral with the turbomachine. This transport arm may comprise an upper rectilinear portion which forms an angle with the main rectilinear portion and which is connected to an upper motor support integral with the turbomachine.
    [0005] Advantageously, the motor supports, the transport interfaces and the said at least one hoisting interface are located substantially in the same transverse plane perpendicular to the median vertical plane P. According to one embodiment of the invention, at least one first hoisting interface is disposed on the hoist arm and at least a second hoist interface is attached to the turbine engine being axially spaced from the first hoist interface, and the structure further comprises a connecting member which connects the first and second interfaces halyard and an attachment member mounted on said connecting member, said latching member being adapted to be connected to the lifting member. The connecting member may comprise a guide rail on which the fastening member is movable in translation. The present invention also relates to a transport and hoisting kit for installing, on a turbomachine or a turbomachine module, a transport and hoisting structure as described above, the kit comprising at least two arms. transport rigid which are each connected or adapted to be connected to at least two engine supports, each transport arm or one of the engine supports connected to each transport arm having a transport interface adapted to be supported by a carrier element a transport carriage, one of the two transport arms being further connected to a rigid hoist arm which comprises a hoisting interface adapted to be connected to a lifting member for hoisting the turbomachine. The hauling arm can be formed in one piece with the transport arm to which it is connected. Alternatively, the hauling arm is attached, preferably removably, to the transport arm to which it is connected.
    [0006] Advantageously, the two transport arms are identical. They are thus interchangeable, and the manufacture of the kit is simplified.
    [0007] According to one embodiment of the invention, each transport arm comprises a main rectilinear portion extended by a lower rectilinear portion which forms an angle with the main rectilinear portion and which is connected or adapted to be connected to a motor support. Each transport arm may comprise an upper rectilinear portion connected to the main rectilinear portion, said rectilinear upper portion forming an angle with the main rectilinear portion and being connected or adapted to be connected to a motor support. According to one embodiment of the invention, the kit comprises a second hoisting interface capable of being fixed to the turbomachine, a connecting member capable of interconnecting the first and second hoisting interfaces, as well as an actuator member. hanging mounted on said connecting member, said latching member being adapted to be connected to a lifting member.
    [0008] The present invention also relates to a rigid transport arm for a transport and hoisting kit as described above, this arm comprising a main rectilinear portion and two rectilinear portions, respectively lower and upper, which extend from a same side of the main rectilinear portion and which each form an angle with this main part, each of these rectilinear lower and upper portions being connected or adapted to be connected to a motor support, the main portion, the lower portion or the motor support connected to this lower portion, having a transport interface adapted to be supported by a carrier member of a transport carriage. The present invention finally relates to a method for transporting and hoisting a turbomachine or a turbomachine module, in order to install it on any side of two lateral sides of the fuselage of an aircraft, the turbomachine comprising attachment bosses of at least four motor supports which are symmetrical two by two with respect to a median vertical plane P comprising a central longitudinal axis of the turbomachine, the method comprising the steps of: a) providing a transport and hoisting kit as described above, bl) fix the engine supports to the fastening means of the turbomachine, b2) connect a first of the two transport arms of the kit to two engine supports located or intended to be located on the same first side of the median vertical plane P, and b3) connect a second of the two carrying arms of the kit to two motor supports located or intended to be located on the same second side of the median vertical plane P, l step b1) being carried out before or after steps b2) and b3), c) setting up the turbomachine on a transport carriage, by supporting the transport interface of each of the two transport arms by a carrier element of the transport trolley, and transporting the trolley to a location from which the turbomachine is to be hoisted, d) connecting a lifting member to the hauling interface of the hauling arm, and hoisting the turbomachine to disengage it from the trolley. transport, e) removing from the turbomachine that of the two transport arms which is not connected to the hoist arm, so as to make available the corresponding bosses 20 of the turbomachine or the two engine supports fixed to these bosses, and f) hoisting the turbomachine using said lifting member, so that the bosses or available engine supports are facing the lateral side of the fuselage of the aircraft on which the turbomachine must be installed. DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example with reference to the appended drawings in which: FIG. 1 is a very schematic view of a turbomachine equipped with a transport and hoisting structure according to the invention, this structure cooperating with a transport carriage of the turbomachine; - Figure 2 is a very schematic view of the structure (forming kit) for transport and hauling of Figure 1; - Figure 3 is a schematic perspective view of a turbomachine equipped with an embodiment of a transport and hoisting structure according to the invention, this structure cooperating with a transport carriage of the turbomachine; FIG. 4 is an enlarged view of part of FIG. 3; - Figure 5 is a schematic perspective view of a turbomachine equipped with an alternative embodiment of a transport and hoisting structure according to the invention, this structure cooperating with a transport carriage of the turbomachine; - Figure 6 is another schematic perspective view of the turbomachine and the transport and hoisting structure of Figure 5, one of the transport arms of this structure having been removed from the turbomachine; FIG. 7 is another schematic perspective view of the turbomachine and of the transport and hoisting structure of FIG. 5, the turbomachine being here connected to a pylon connecting a fuselage of an aircraft; FIG. 8 is a schematic perspective view of a turbomachine equipped with another variant embodiment of a transport and hoisting structure according to the invention, this structure cooperating with a carriage for transporting the turbomachine, and Figure 9 is a schematic perspective view of another alternative embodiment of a transport and hoisting structure according to the invention. DETAILED DESCRIPTION Reference is first made to FIGS. 1 and 2 which very schematically represent a first embodiment of a transport and hoisting structure 10 according to the invention for a turbomachine 12 or a turbomachine module. In a conventional manner, a turbomachine 12 comprises a motor surrounded by a nacelle, the engine comprising from upstream to downstream, in the direction of flow of the gases in the engine, a fan, at least one compression stage, a combustion chamber , at least one turbine stage, and a combustion gas ejection nozzle. The structure 10 according to the invention may be designed to transport and hoist the turbomachine 12 or only a part or a module of this turbomachine, such as its engine for example. FIG. 1 shows the structure 10 installed on the turbomachine 12 and FIG. 2 shows the structure 10 detached from the turbomachine, this detached structure 10 can then be likened to a kit. The structure 10 according to the invention essentially comprises three parts called arms, two transport arms 14, 16 and a hoist arm 18, one of the transport arms 16 being integral with the hauling arm 18. connection between the arms 16, 18 is schematically represented by the dashed lines 20. The transport arms 16 are substantially identical. They comprise each of the interfaces 22, here two in number, for connection to the turbomachine 12 (called engine interfaces 22), and an interface 24 for connecting to a transport carriage 26 (called the transport interface 24). The hauling arm 18 comprises at least one interface 28 for connecting to a lifting member (not shown - called hoisting interface 28). The central longitudinal axis of the turbomachine 12 and P is denoted by the median vertical plane of the turbomachine, passing through this axis A. It can be seen that the engine interfaces 22 are diametrically opposite two-to-two with respect to the axis A and that the interfaces 22 located on one side of the turbomachine 12 are symmetrical with respect to the interfaces 22 located on the other side of the turbomachine 12, relative to the plane P. Two interfaces 22 are located at the bottom and the other two interfaces 22 are located at the top. It can also be seen that the transport interfaces 24 are positioned symmetrically with respect to the plane P. Each transport arm 14, 16 extends on one side only of the turbomachine 12 with respect to the plane P, the two arms 14, 16 being also arranged symmetrically with respect to this plane, when they are installed on the turbomachine 12. The hoist arm 18 extends upwardly and above the turbomachine 12, from an upper end of the transport arm 16, and crosses the plane P. In the case where the hoist arm 18 comprises two hauling interfaces 28, they can be positioned symmetrically with respect to the plane P, as in the example shown. The two motor interfaces 22 of each transport arm 14, 16 are respectively located at the upper and lower ends of the arm. The transport interface 24 of each transport arm 14, 16 is located at the lower end of the arm. The transport carriage 26 is here equipped with wheels 30 to facilitate its movement in a horizontal plane substantially parallel to the axis A. The carriage 26 comprises carrying elements 32 cooperating with the transport interfaces 24 of the transport arms 14, 16. Each carrier member 32 has an elongate rectilinear shape. It extends upwards from the carriage 26 and it is its upper free end which cooperates with the transport interface 24 of a transport arm 14, 16. As will be described in more detail in the following, with reference to more detailed embodiments of the invention, the motor interfaces 22 and the transport interface 24 of each transport arm 14, 16 can be formed directly on this arm or can be carried by a part, called support motor 40, connected to the arm 14, 16 and intended to be integral with the turbomachine 12. The motor supports 40, the transport interfaces 24 and the hoisting interfaces 28 are here located substantially in the same transverse plane perpendicular to the plane P, this transverse plane being the plane of the drawing of FIG. 1. Reference is now made to FIGS. 3 and 4 which represent an alternative to the first embodiment of a transport and hoisting structure according to the invention. The transport and hoisting structure 110 comprises a transport arm 116 formed integrally with a hoist arm 118, similarly to the transport and hoisting arms 16, 18 described above. The transport arm 116 comprises three rectilinear portions respectively main 134, upper 136 and lower 138. This arm 116 here has a general shape in "t". Its main portion 134 extends on one side of the turbomachine 112 and is connected at its lower end to the lower portion 138 which extends from the main portion to the turbomachine 112. The main portion 134 and lower 138 form between them angle, which is here of the order of 70-120 °. The main portion 134 is connected substantially at its middle to the upper portion 136 which extends from the main portion to the turbomachine. The main portions 134 and upper 136 form an angle between them, which is here also of the order of 70-120 °.
    [0009] The portions 134, 136 and 138 of the transport arm 116 are formed in one piece. On the other hand, as described above with respect to the hoist arm 18, the hoist arm 118 extends upwards and above the turbomachine 12, from the upper end of the main portion 134 of the transport arm 116. and crosses the plane P. The arms 116 and 118 may be made from bars or metal sleepers, which may be tubular. The free end of each of the upper portions 136 and lower 138 of the transport arm 116 is connected to an associated motor support 140 which is fixed on the turbomachine 112 (Figure 4). The transport arm 116 is thus connected to two motor supports 140 located on the same side of the turbomachine, here the left side in the example considered. The turbomachine comprises bosses 142, here four in number, on each of which is applied and fixed a motor support 140.
    [0010] These bosses 142 are located at the engine interfaces 22 described above with reference to Figures 1 and 2. For example, a boss 142 may be constituted by a metal block with flanks provided to be fixed by bolts or rivets to a flange of the turbomachine.
    [0011] Each boss 142 comprises a plane outer surface forming an interface on which is fixed the corresponding motor support 140. The motor support 140 comprises a plate 144 applied on this outer surface of the boss 142, the plate 144 having through-holes (not shown) for passing bolts, which are aligned with through or threaded orifices of the boss 142, for fixing the motor support 140 to the turbomachine 112. The plate 144 of the engine support 140 is connected to two yokes 146a, 146b of connection respectively to the transport arm 116 and to a carrier element 132 of the transport trolley 126, which is similar to that described in FIG. in the foregoing with reference to Figure 1. The yokes 146a, 146b are here formed by a lug projecting from the plate 144 and substantially perpendicular to the plate, this lug having two holes for mounting pivots (not shown) d articulation of the transport arm 116 and the carrier member 132 of the carriage 126, respectively. The transport arm 116, and in particular the free end of its lower portion 138, comprises a through hole for mounting a first of these pivots, and the upper end of the carrying member 132 comprises a mounting through hole. the second pivot. The axes B, C of the pivots are substantially parallel to each other and are here substantially parallel to the axis A.
    [0012] The plate 140 attached to the turbomachine 112 forms a motor interface 122 and the yoke 146b connected to the carrier member 132 forms a transport interface 124, the engine interface 122 and the transport 124 being similar to those described in the foregoing reference Figures 1 and 2. The transport arm 116 as such therefore does not include a transport interface 124. In the present invention, a transport arm generally comprises either an integrated transport interface to the arm or is connected to a member such as a motor support which comprises a transport interface.
    [0013] Alternatively, it is the yoke 146a connected to the transport arm 116, or the free end of the lower portion 138 of the transport arm which could be considered as forming a motor interface. This is particularly the case in an embodiment variant of the invention, not shown, in which the engine supports 140 would be formed in one piece with the bosses 142 of the turbomachine. These bosses 142 would then be formed in one piece with the yokes 146a, 146b of connection to the support arm 116 and the carrier member 132 of the transport trolley 126. In the example shown, the transport arm 116 is connected by the engine supports 140 at an upstream longitudinal end of a turbomachine module 112, which here comprises a substantially cylindrical housing. The transport arm 116 extends on one side only of the turbomachine module 112 with respect to the plane P. The transport carriage 126 comprises two carrying elements 132 at the front and two carrying elements 132 at the rear. The two front support elements 132 cooperate with the two lower front engine supports 140, that is to say located upstream of the turbomachine module and at a height less than that of the axis A, and therefore support the upstream end of the turbomachine module 112. It should be noted that a second lower engine support 140, not visible in Figure 3 but identical to that shown in Figure 4, is provided on the non-visible side of the module (here the side law). The two lower motor supports 140 are symmetrical with each other with respect to the plane P. The rear support elements 132 cooperate with the downstream end of the turbomachine module 112 and thus support this downstream end.
    [0014] Furthermore, the two upper engine mounts 140 upstream, that is to say located upstream of the turbomachine module and at a height greater than that of the axis A, are not necessarily identical to a motor support 140 inferior. In particular, an upper engine support 140 may comprise only one yoke 146a or 146b, adapted for connection to a suspension member connecting the turbomachine to the pylon of the aircraft, the suspension member being for example such as that shown in reference 245 in Figure 7. In fact, the upper engine supports 140 are not used to connect the carrier elements 132 of the transport carriage 126.
    [0015] The hauling arm 118 here comprises an upper rectilinear portion which extends above the turbomachine module 112 and comprises the hoisting interface or interfaces 128 described in the foregoing (and referenced 28 in FIGS. 1 and 2). As an alternative to the embodiment of Figures 3 and 4, it is possible to provide a second transport arm 114, not shown but similar to the transport arm 14 of Figure 1. The second transport arm 114 then extends to the side Opposite the module, symmetrically with respect to the plane P. By providing the two transport interfaces 124 on the transport arms 114, 116 and no longer on the engine supports 140, the embodiment obtained according to this variant becomes similar to that of the Figure 1. The alternative embodiment of the structure 210 according to the invention shown in Figures 5 to 7 differs from the embodiment of Figures 3 and 4 essentially on three points.
    [0016] In the first place, the hauling arm 218 is not here formed in one piece with the transport arm 216 but is instead fixed to the latter removably or detachably. The support arms 216 and hoist 218 can thus be dissociated from one another. Advantageously, the two transport arms 214, 216 of the structure 210 are identical, each transport arm 214, 216 comprising (at the upper ends of their main portions 234) removable attachment means configured to cooperate with means of complementary attachment of the hauling arm 218. The hauling arm 218 can thus be fixed indifferently on one or the other of the transport arms 214, 216 of the structure 210.
    [0017] The other difference concerns the transport interfaces 224 which are no longer carried by the motor supports 240 but by the transport arms 214, 216. The transport interface 224 of each transport arm 214, 216 is here located in the zone connecting the main portions 234 and lower 238 of this arm, and comprises a through hole housing a pivot pivot of an upper end of a carrier member 232 of the carriage 226, as described above. The engine supports 240 always carry the motor interfaces 222. Another difference concerns the shape of the hoist arm 218, which here is substantially L-shaped and comprises a substantially horizontal rectilinear portion, one longitudinal end of which is detachably connected to the support arm 216. and whose opposite longitudinal end is connected to the lower end of a substantially vertical rectilinear portion. The upper end of this substantially vertical portion may comprise the hoisting interface or interfaces 228 described in the foregoing. The structure 210 is here intended to transport a turbomachine module 212 which comprises, in addition to the casing shown in FIGS. 3 and 4, an additional casing mounted upstream of the first casing. The structure 210 installed on this module is remote from the longitudinal ends of the module, unlike Figures 3 and 4 in which the structure 110 is located at the upstream end of the module. A method for transporting and hoisting a turbomachine 212, in order to install it on one of the lateral sides of the fuselage of an aircraft, will now be described with reference to FIGS. 5 to 7. Although this method is described with reference to the structure 210, it applies naturally to each of the structures 10, 110 described in the foregoing. A first step of the method consists in providing a transport and hoisting kit, this kit comprising the two transport arms 214, 216 of which one 216 is connected to the hauling arm 218. In the case where the engine supports 240 are not already integral with the turbomachine module, they are applied and fixed on the bosses of this module as described above. Each transport arm 214, 216 is then connected to two motor supports 240 located on one side of the plane P, then the turbomachine module 212 is positioned on the support carriage 226. The carrier elements 232 before the carriage 226 cooperate with the transport arm 214, 216 and its rear support members 232 cooperate with corresponding supports provided on a flange attached to the downstream end of the turbomachine module 212. The structure 210 is thus installed on the turbomachine module 212 which is supported by the transport carriage 226, as shown in Figure 5. The carriage 226 is then moved to a desired location from which the turbomachine module 212 must be hoisted to a given height. A lifting member is then connected to the hauling interface of the hauling arm 218 and the turbomachine module 212 is hoisted to disengage it from the transport trolley 226.
    [0018] The transport arm 214, which is not connected to the hauling arm 218, is then removed and removed from the turbomachine module 212, as shown in FIG. 6. This operation makes available the two engine supports 240 which were connected to the 214. These two engine supports 240 may be provided to remain attached to the module bosses after the arm 214 has been withdrawn.
    [0019] The turbomachine module 212 is then hoisted using the lifting member, so that the available engine supports are facing the lateral side of the fuselage of the aircraft on which the turbomachine must be installed. As shown in FIG. 7, the fuselage of the aircraft comprises a pylon 250 which is connected by appropriate means of suspension and attachment 245 to the engine supports 240 located on the lateral side of the module where the transport arm 214 was located. These supports motor 240, which form motor interfaces 222, thus also form suspension interfaces capable of cooperating with suspension means 245 of the module or of the turbine engine to the pylon 250. The suspension means 245 may for example be similar to those described. in the patent application published under the number FR-A1-2 965 796. Once the turbomachine module 212 is attached to the pylon 250, the lifting member is detached from the hoisting interface, and the assembly formed by the transport arm 216 and the haul arm 218 can be disassembled and removed from the module 212. The two engine supports 240 which were connected to the arm 216 can be removed from the module if their design n allows it, which lighten somewhat the module and reuse these motor brackets for another module. Of course, it is conceivable to provide motor brackets integrated in the module so that they can not be disassembled. For example, the engine mounts can be permanently attached to a flange of the turbomachine. Alternatively, the two motor supports 240 may be provided each incorporated in a transport arm 214, 216, and therefore do not remain attached to the module bosses after removal of the transport arms. Such a configuration corresponds to a transport arm for example such as that shown in Figure 9, where the two engine supports remain fixed on the arm. In this configuration, a boss of the turbomachine such as the boss 142 described above in FIG. 4 can be considered as forming a motor interface. In addition, the suspension means 245 are then provided to be connected to the two corresponding bosses either directly or via appropriate support and fixing members. Referring now to Figure 8 which shows another alternative embodiment of the structure 310 for transport and hoisting according to the invention. Although only the transport arm 316 associated with the hauling arm 318 is shown here, the structure further comprises a second transport arm 314 identical to the first transport arm 316, as described above. Each transport arm 314, 316 has a substantially rectilinear main portion 334 whose upper and lower ends are connected to cylindrical bars, upper 336 and lower 338, respectively. The main portion 334 of each arm 314, 316 extends on one side. the turbomachine 312, substantially parallel to the plane P. The bars 336, 338 extend from the same side of the main portion 334 to the turbine engine 312 and each form an angle of approximately 90 ° with the main portion 334. The bars 336 , 338 are thus substantially parallel and extend substantially perpendicularly to the plane P. They are similar to the aforementioned lower and upper rectilinear portions of the support arms in the embodiments described in the foregoing. The longitudinal end of each bar 336, 338, opposite to the main portion 334 of the arm 314, 316, is connected to a motor support 340 which is fixed on the turbine engine 312. The turbine engine 312 may comprise bosses for fixing these supports. motor 340, as described above. These motor supports 340 are located in the connection areas of the transport arms of the structure 310 to the turbomachine 312, that is to say at the motor interfaces 322 described above. The transport carriage 326 comprises two carrier members 332 at the front and two carrier members 332 at the rear. Each carrier element 332 before cooperates with a cylindrical bar 339a of a transport arm. This bar 339a is situated on one side of the main portion 334 of the transport arm, opposite to that on which are located the bars 336, 338. The bar 339a forms an angle of approximately 90 ° with the main portion 334 and is thus substantially parallel to the bars 336, 338.
    [0020] This bar forms a transport interface 324. Each rear carrier member 332 of the carriage 326 cooperates with another cylindrical bar 339b which is fixed for example detachably to the turbine engine 312, and which also forms a transport interface.
    [0021] The hauling arm 318 is detachably attached to the transport arm 316 and comprises a substantially rectilinear portion which extends above the turbomachine 312, from the upper end of the main portion 334 of the transport arm 316, and passes through the plane P. The hoist arm 318 is integral with a first arch 352 which extends in a substantially vertical plane and whose concavity is oriented downwards, that is to say towards the turbine engine 312. The arch 352 is for example formed in one piece with the rectilinear portion of the hoist arm 318, or is formed by a piece bolted to said rectilinear portion as in the example shown. This arch 352 carries fingers 354 which are oriented parallel to the axis A and which are guided in curved grooves 356 of a first end element of a connecting member 358. A second arch 362 is furthermore fixed to the turbomachine 312, and extends in a substantially vertical plane with its concavity oriented downwards. The hoops 352, 362 are at an axial distance from one another and form hoisting interfaces 328. The hoop 362 also carries fingers 354 which are oriented parallel to the axis A and which are guided in grooves 356. curved of a second end member of the connecting member 358. The grooves 356 of the end pieces of the connecting member 358 are preferably identical and their radius of curvature is preferably centered on the axis A The connecting member 358 comprises a longitudinal rail 364 which extends between the two aforementioned end pieces and which is integral with these end pieces. The rail 364 extends parallel to the axis A, above the turbomachine 312. A hooking member 366 is mounted on the rail 364 so as to be movable along the latter, this attachment member 366 comprising means of connection to a lifting member adapted for hoisting the turbomachine 312. The method described in the foregoing, with reference to Figures 5 to 7, applies to the structure 310 of Figure 8. It can be seen that the turbine engine 312 of Figure 8 is almost complete, only an outer cylindrical cowling of the nacelle having been removed to allow the connection of the pylon to a structural element of the turbine engine 312.
    [0022] In addition to the steps of the method presented above, it is understood that the method can here comprise stages of adjustment of the position of the turbine engine 312 vis-à-vis the tower on which is intended to be fixed the turbine engine 312. L hooking member 366, which is displaceable on the rail 364 of the connecting member 358, thus makes it possible to position a ring of the fastening member 366 with a possible shift more or less important in the longitudinal direction relative to at the position of the center of gravity of the turbine engine 312, which makes it possible to adjust the inclination of the axis A of the turbomachine relative to the horizontal. This property can be useful if the axis A is provided to form an angle relative to the horizontal once the turbine engine mounted on the pylon of the aircraft. Furthermore, the end pieces of the connecting member 358, which are movable in rotation vis-à-vis the arches 352, 362 (by guiding the fingers 354 of the arches in the grooves 356 of the end pieces), makes it possible to adjust the angular position of the turbomachine 312 around the axis A. The freedom of adjustment of both the inclination of the axis A and the angular position of the turbomachine around this axis allow a positioning precise turbomachine for fixing the suspension elements of the turbomachine on the pylon of the aircraft. Referring now to Figure 9 which shows another alternative embodiment of a transport arm and an associated hauling arm in a transport and hoisting structure 410 according to the invention. The transport arm 416 comprises a main portion 434 that is substantially rectilinear, as well as two relatively short rectilinear portions, respectively 438 and 436, which form portions of tubes parallel to each other which extend on one and the same side of the main rectilinear portion and which each form a substantially right angle with this main part. Alternatively, a different angle can be envisaged so that the axes of the two rectilinear portions converge on the side of the turbomachine.
    [0023] These two rectilinear lower portions 438 and upper 436 are each connected to a motor support 440 adapted to be secured to the turbomachine. Each engine support 440 comprises a cylindrical bar bent a portion of which is fixed to the lower rectilinear portion 438 or greater 436 and another portion of which is formed by a cylindrical portion 441 which has an end secured to a plate 444 for attachment to a boss of the turbomachine. Each plate 444 forms a motor interface 422. In mounting position on the turbomachine, the main portion 434 of each arm 416 extends on one side of the turbomachine, substantially parallel to the plane P supra. The engine supports 440 extend from the same side of the main portion 434 to the turbomachine. The axes of the cylindrical portions 441 of the motor supports 440 form an angle between them, for example less than or equal to 90 °, and converge at the same point typically located on the central longitudinal axis A of the turbomachine once the engine supports 440 fixed to the turbomachine. The main portion 434 of each arm 416 is here formed by two tubular sections engaged one inside the other, a lower section 436a (of smaller section), of which an upper end portion is engaged in a lower end portion. an upper profile 436b (larger section). The lower profile 436a carries the lower motor support 440 at its lower end. The upper profile 436b carries the upper motor support 440 near its lower end. This upper profile 436b carries at its lower end a hook 439 which forms a transport interface 424, intended to cooperate with a carrier member of a transport carriage, as described above. The hook 439 is generally L-shaped or U-shaped and defines an opening that faces downward. This hook 439 is located on one side of the main portion 434 of the transport arm 416, opposite that on which the motor supports 440 are located.
    [0024] The hauling arm 418 is detachably attached to the transport arm 416 and comprises a substantially rectilinear portion which is intended to extend above the turbomachine, from the upper end of the main portion 434 of the transport arm 416. The hoist arm 418 comprises at its upper end holes 480 for fixing a hoop of the aforementioned type, for example identical to the hoop 352 described with reference to FIG. 8, and which is intended to form a hoisting interface 428 (not shown) This arch is intended to extend in a substantially vertical plane, its concavity being oriented downwards, that is to say towards the turbomachine.
    [0025] The transport and haulage structure 410 advantageously furthermore comprises a second transport arm 414 identical to the first transport arm 416, as described in the foregoing with reference to FIG. 8, and which comprises the second transport interface 424 of the structure. Alternatively, similarly to the embodiment described with reference to FIG. 3, it is possible to dispense with the second transport arm 414, in which case a lower engine support may be provided instead which comprises a suitable transport interface. to be connected to a carrier element corresponding to the front of the transport carriage. The process described in the foregoing, with reference to FIGS. 5 to 8, applies to the structure 410 of FIG. 9. In the embodiments described herein, the number of motor supports connected to a transport arm is equal to two. The invention is however not limited to this configuration. For example, it is not excluded to provide three or more engine supports on each lateral side of the turbomachine, with a transport arm adapted to be connected to all the engine supports on the same lateral side.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. Transport and hoisting structure (10, 110, 210, 310, 410), installed on a turbomachine (12, 112, 212, 312) or on a turbomachine module which has a central longitudinal axis (A) forming an angle between 0 ° and 10 ° relative to the horizontal, the structure comprising: - at least two transport interfaces (24, 124, 224, 324, 424) rigidly connected to the turbomachine, located on either side of the turbomachine relative to a median vertical plane (P) comprising said central longitudinal axis (A) and each adapted to be supported by a carrier member (32, 132, 232, 332) of a transport carriage (26, 126, 226, 326) of the turbomachine, - at least one hoisting interface (28, 128, 228, 328) rigidly connected to the turbomachine, adapted to be connected to a lifting member for hoisting the turbomachine, and - motor supports (40 , 140, 240, 340, 440) integral with the turbomachine, characterized in that said at least one interface of hoist is arranged on a rigid hoist arm (18, 118, 218, 318, 418) which extends at least partly above the turbomachine and which crosses said median vertical plane (P), said hoist arm being connected to a rigid transport arm (16, 116, 216, 316, 416) which is connected to at least two of said engine supports, the motor supports connected to this transport arm being located on the same side of the turbomachine relative to the vertical median plane (P), and in that the transport arm or one of the engine supports connected to this transport arm comprises one of said at least two transport interfaces.
    [0002]
    The structure (10, 110, 210, 310, 410) according to claim 1, wherein the hauling arm (18, 118) is integrally formed with the carrying arm (16, 116), or the arm hoist (218, 318, 418) is attached, preferably removably, to the transport arm (216, 316, 416).
    [0003]
    The structure (110, 210, 310) according to claim 1 or 2, wherein the transport arm (116, 216, 316) comprises a main rectilinear portion (134, 234, 334) connected to a lower rectilinear portion (138, 216, 316). , 238, 338) which forms an angle with the main rectilinear portion and which is connected to a lower motor support (140, 240, 340) integral with the turbomachine (112, 212, 312).
    [0004]
    The structure (110, 210, 310) according to claim 3, wherein the transport arm (116, 216, 316) comprises an upper rectilinear portion (136, 236, 336) which forms an angle with the main rectilinear portion and which is connected to an upper engine support (140, 240, 340) integral with the turbomachine (112, 212, 312).
    [0005]
    5. Structure (10, 110, 210, 310, 410) according to one of the preceding claims, wherein the motor supports (40, 140, 240, 340, 440), the transport interfaces (24, 124, 224, 324, 424) and said at least one hoisting interface (28, 128, 228, 328) are located substantially in the same transverse plane perpendicular to the median vertical plane (P).
    [0006]
    6. Structure (310) according to one of the preceding claims, wherein at least a first hoist interface (328) is disposed on the hoist arm (318) and at least a second hoist interface (328) is fixed to the turbine engine (312) being axially spaced from the first hauling interface, and the structure further comprises a connecting member (358) which connects between them the first and second hoist interfaces and a fastening member (366). ) mounted on said connecting member, said latching member being adapted to be connected to the lifting member.
    [0007]
    7. Structure (310) according to claim 6, wherein the connecting member (358) comprises a guide rail (364) on which the fastening member (366) is movable in translation.
    [0008]
    8. Transport and hoisting kit for installing, on a turbomachine (12, 112, 212, 312) or on a turbomachine module, a transport structure (10, 110, 210, 310, 410) and hoist according to one of the preceding claims, the kit comprising at least two rigid transport arms (14, 16, 114, 116, 214, 216, 314, 316, 416) which are each connected or connectable to each other. at least two engine supports (40, 140, 240, 340, 440), each transport arm or one of the engine supports connected to each transport arm having a transport interface (24, 124, 224, 324, 424) adapted to be supported by a carrier member (32, 132, 232, 332) of a transport carriage (26, 126, 226, 326), one of the two transport arms being further connected to a rigid arm of hoisting (18, 118, 218, 318, 418) which comprises a hoisting interface (28, 128, 228, 328, 428) adapted to be connected to a lifting member for hoisting the turbomachine.
    [0009]
    A kit according to claim 8, wherein the hauling arm (118) is formed integrally with the transport arm (116) to which it is connected, or the hauling arm (218, 318, 418) is fixed, preferably removably, to the transport arm (216, 316, 416) to which it is connected.
    [0010]
    Kit according to claim 8 or 9, wherein the two transport arms (14, 16, 114, 116, 214, 216, 314, 316, 416) are identical.
    [0011]
    11. Kit according to one of claims 8 to 10, wherein each transport arm (114, 116, 214, 216, 314, 316, 416) comprises a main rectilinear portion (134, 234, 334, 434) extended by a lower rectilinear portion (138, 238, 338, 438) which forms an angle with the main rectilinear portion and which is connected to or connectable to a motor support (140, 240, 340, 440).
    [0012]
    Kit according to claim 11, wherein each transport arm (114, 116, 214, 216, 314, 316, 416) comprises an upper rectilinear portion (136, 236, 336, 436) connected to the main rectilinear portion (134, 236, 336, 436). , 234, 334, 434), this upper rectilinear portion forming an angle with the main rectilinear portion and being connected to or connectable to a motor support (140, 240, 340, 440).
    [0013]
    13. Kit according to one of claims 8 to 12, further comprising a second hoist interface (328) adapted to be fixed to the turbomachine (312), a connecting member (358) adapted to connect the first and second hoist interfaces, and a hooking member (366) mounted on said connecting member, said hooking member being adapted to be connected to a lifting member.
    [0014]
    14. Rigid transport arm (114, 116, 214, 216, 314, 316, 416) for a carrying and hoisting kit according to one of claims 8 to 12, said arm comprising a main rectilinear portion (134, 234, 334, 434) and two rectilinear portions, respectively lower (138, 238, 338, 438) and upper (136, 236, 336, 436), which extend on the same side of the main rectilinear portion and which each form an angle with this main part, each of these lower and upper rectilinear portions being connected or adapted to be connected to a motor support (140, 240, 340, 440), the main portion, the lower portion or the motor support connected to this lower portion, having a transport interface (124, 224, 324, 424) adapted to be supported by a carrier member (132, 232, 332) of a transport carriage (126, 226, 326).
    [0015]
    15. A method for transporting and hoisting a turbomachine (12, 112, 212, 312) or a turbomachine module, in order to install it on any side of two lateral sides of the fuselage of an aircraft, the turbomachine comprising bosses ( 142) for fixing at least four motor supports (40, 140, 240, 340, 440) which are symmetrical in pairs relative to a median vertical plane (P) comprising a central longitudinal axis (A) of the turbomachine, the method comprising the steps of: a) providing a transport and hoisting kit according to one of claims 8 to 13, b1) fixing the engine supports to the bosses of the turbomachine, b2) connecting a first (16) , 116, 216, 316, 416) of the two rigid transport arms of the kit with two engine supports located or intended to be located on the same first side of the median vertical plane (P), the rigid hoisting arm (18, 118 , 218, 318, 418) already being connected or intended to be connected to said first rigid transport arm and b3) connecting the second (14, 114, 214, 314, 414) of the two rigid transport arms of the kit to two engine supports located or intended to be situated on the same second side of the median vertical plane ( P), the step b1) being carried out before or after the steps b2) and b3), c) setting up the turbomachine on a transport carriage (26, 126, 226, 326), by supporting the interface of transporting (24, 124, 224, 324, 424) each of the two transport arms by a carrier member (32, 132, 232, 332) of the transport carriage, and transporting the carriage to a location from which the turbomachine must be hoisted, d) connect a lifting member to the hoist interface (28, 128, 228, 328) of the hoist arm (18, 118, 218, 318, 418), and hoist the turbomachine to release it of the transport carriage, e) removing from the turbomachine the second rigid transport arm (14, 114, 214, 314, 414), so as to make the bosses available corresponding to the turbomachine or the two engine supports attached to these bosses, and f) hoist the turbomachine with the aid of said lifting member, so that the bosses or available engine supports are facing the lateral side of the fuselage of the engine. aircraft on which the turbomachine must be installed.
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    同族专利:
    公开号 | 公开日
    WO2015114276A1|2015-08-06|
    US20170166331A1|2017-06-15|
    FR3017112B1|2017-09-29|
    US10906667B2|2021-02-02|
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    法律状态:
    2015-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-03| PLFP| Fee payment|Year of fee payment: 3 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2017-02-07| PLFP| Fee payment|Year of fee payment: 4 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-01-23| PLFP| Fee payment|Year of fee payment: 6 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 8 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1400286A|FR3017112B1|2014-02-03|2014-02-03|TRANSPORT AND HINGING STRUCTURE FOR TURBOMACHINE|FR1400286A| FR3017112B1|2014-02-03|2014-02-03|TRANSPORT AND HINGING STRUCTURE FOR TURBOMACHINE|
    US15/115,837| US10906667B2|2014-02-03|2015-02-02|Transport and hoisting structure for a turbomachine|
    PCT/FR2015/050228| WO2015114276A1|2014-02-03|2015-02-02|Transport and hoisting structure for a turbomachine|
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