FR3039824A1 - KIT FOR GUIDING AN AIRCRAFT TURBOMACHINE DURING ITS INSTALLATION / REMOVAL ALONG A CRIB - Google Patents

Abstract

The invention relates to a kit (62) for guiding a longitudinally oriented aircraft turbine engine (10), such as a turboprop engine (10), during the raising or lowering of said turbomachine along a cradle (18) axially of said aircraft (16) to which it is suspended, characterized in that it comprises guide means in a substantially vertical direction of the turbomachine (10) in said cradle (18) forming a transverse stop for said turbomachine (10) in said cradle (18), which are configured to be interposed between said cradle (18) and said turbomachine (10) substantially at the longitudinal ends of said turbomachine (10). The invention also relates to a method of laying / removing an aircraft turbomachine (10), in particular a turboprop engine, from a cradle (18), by means of a kit (62) according to the invention.

Description

Kit for guiding an aircraft turbomachine during its installation / removal along a cradle

Technical Field of the Invention

The present invention relates to the attachment of power units on aircraft. It relates more particularly to a guide kit, and a method for the installation / removal of a turbomachine along a suspension cradle of an aircraft.

State of the art :

A turbomachine is located in an air flow stream when the aircraft is moving. Moreover, when the turbomachine is a turboprop, it is also located in the current of the propeller which is driven by said turboprop. In both cases, the suspension system must represent the minimum of space around the engine to minimize the size of the obstacle that represents the engine block in the air flows, whether air flows caused by the displacement of the aircraft, or air flows caused by the propeller.

FIG. 1 represents a turboprop 10 carried by a cradle 18 according to the state of the art, which forms for this purpose a suspension system for the turboprop 10. The cradle 18 is composed for example of two arches 20, 22 front and rear in inverted U-shape, interconnected by a connecting rod lattice 19 shown in Figure 2. The cradle 18 envelops the turboprop 10 while leaving free its lower part, whether for maintenance or installation / removal.

This configuration has been shown in the context of the suspension of a turboprop 10 but it will be understood that it could be applied to any type of turbomachine.

The cradle 18 is conventionally arranged closer to the turboprop 10 to limit its size, which reduces the aerodynamic drag of said cradle 18. The turboprop 10 is also attached to the cradle 18 via suspensions 36 to the front and suspensions 40 at the rear (Figure 2).

When it is desired to deposit a turbomachine such as turboprop 10, for example for maintenance purposes in the workshop or for its replacement, it is necessary to support the turbomachine, for example using hoists 60 (FIG. 3), then remove the suspensions 36 and 40 of the turbomachine 10, and then down to its support.

This last operation is particularly delicate, since the turbomachine must descend between the arches 20, 22 of the cradle 18 without touching them, in order to avoid that elements of the turbomachine 10 such as pipes or equipment, such as a computer, are damaged.

In the case where the turbomachine is suspended on hoists, this operation is all the more delicate as the turbomachine often tends to swing and is therefore more inclined to come into contact with the cradle than when it is supported by means support of another type.

Once extracted from the cradle, the turbomachine is then deposited on a receiving means such as a frame or a carriage.

There is therefore a need for a solution for ensuring a rapid descent of the turbomachine out of the cradle by guiding it in the cradle to avoid interference with said cradle.

The object of the present invention is to propose such a solution.

Presentation of the invention: For this purpose, the invention relates to a kit for guiding an aircraft turbomachine on a frame, comprising guide means in a substantially vertical direction of the turbomachine in said cradle, and forming a stop transverse for said turbomachine in said cradle, which allow the guidance of the turbomachine in the cradle during its rise in the cradle or its descent out of the cradle.

For this purpose, the invention proposes a kit for guiding an aircraft turbomachine of longitudinal orientation A, such as a turboprop, during the raising or lowering of said turbomachine from an axial cradle of said aircraft. which it is suspended, characterized in that it comprises guide means in a substantially vertical direction of the turbomachine in said cradle, said guide means forming a transverse stop for said turbomachine in said cradle, and being configured to be interposed between said cradle and said turbomachine substantially at the longitudinal ends of said turbomachine.

According to other features of the kit: - the guide means are adapted to a cradle having a front bow and a rear bow connected by connecting rods and said guide means are interposed between said arches and the turbomachine, - the guide means comprise at least two first members configured to be fixed transversely on either side of an end of a casing of the turbomachine and having at their free ends sliding or rolling means configured to cooperate with vertical rails carried by vertical branches of the hoop, the kit is associated with a turbomachine comprising a turboprop propeller hub which extends axially out of the cradle, and the guide means comprise at least two frames, which are fixed to vertical branches of the front bow, which extend to a transverse plane of said hub, and which have vertical sliding pads configured to applied on either side of said hub, the pads are carried by transversely adjustable supports relative to the frames to allow adaptation of the spacing of said pads relative to the hub, the guide means comprise at least one second member configured to be fixed to an upper part of a casing of the turbomachine and comprising a vertical slide configured to be received between two vertical rails carried by a transverse branch of the hoop, - the kit is associated with a turbomachine configured to to be fixed to the rear arch of the cradle by means of a suspension ring encircling a casing of the turbomachine, and the guide means comprise two transversely opposed ear-shaped elements made of a material of a hardness lower than that of the rear arch which are configured to be fixed to said suspension ring and to be received with clearance between faces i In addition to the vertical branches of the rear arch, each ear-shaped element has a pair of plates made of plastic material (or other material but with a hardness less than that of the cradle hoops) which are configured to take the ring. sandwich suspension, which are joined by a fixing pin passing through an ear of the suspension ring, and by at least two axes which bear on the periphery of the ring to prevent rotation of said ear-shaped element . each ear-shaped element comprises at least one plate which is configured to be fixed to the suspension ring by means of at least two axial elements passing through said plate and two corresponding ears of the suspension ring. The invention also relates to an assembly comprising an aircraft turbomachine, such as a turboprop, and a support cradle of the turbomachine, which is equipped with at least one kit of the type previously described. The invention finally relates to a method for laying / removing an aircraft turbomachine, in particular a turboprop engine, from a cradle, by means of a kit of the type previously described, characterized in that it comprises: the operation of removing the engine) - a step during which the turbomachine is supported; - A step during which is deposited connecting elements connecting the turbomachine to the cradle and during which the kit is interposed between the turbomachine and the cradle; a step during which a means for receiving the turbomachine under the cradle is positioned, and a step during which the turbomachine is lowered with respect to the cradle until it is received on said means of reception.

These steps are performed in reverse order when mounting the motor in the cradle. More exactly, the laying method would comprise: a step during which the turbomachine is mounted relative to a reception means until it is received in the cradle, a step during the means for receiving the turbomachine under the cradle are removed, and a step during which connecting elements of the turbomachine are mounted to the cradle and during which the kit is removed, and a step in the course of which the support or the suspension of the turbomachine is canceled.

According to another characteristic of the method, during the second step, there is at least one element of the kit instead of a connecting element of the turbine engine to the cradle. The invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings, in which: Figure 1 is a perspective view of a turboprop received in a nacelle of an aircraft, according to the prior art; FIG. 2 is a perspective view of a naked aircraft cradle according to the prior art; FIG. 3 is a perspective view showing a turboprop engine being dismantled from its cradle; - Figure 4 is a perspective view of a member for a guide kit according to a first embodiment of the invention; - Figure 5 is a perspective view of the guide kit according to the first embodiment of the invention interposed between a turboprop and a bow before its cradle; - Figure 6 is a detail sectional view through a horizontal plane of a guide kit according to the first embodiment of the invention interposed between the turboprop and the bow before its cradle; - Figure 7 is a perspective view of a guide kit according to a second embodiment of the invention interposed between a turboprop and a bow before its cradle; FIG. 8 is a detailed perspective view of a frame for the guide kit according to the second embodiment of the invention; FIG. 9 is a detailed perspective view of a pad for the kit of FIG. guidance according to the second embodiment of the invention; - Figure 10 is a perspective view of a guide kit according to a third embodiment of the invention interposed between a turboprop engine and a rear bow of its cradle; - Figure 11 is a perspective view of a vertical slide for the guide kit according to the third embodiment of the invention; - Figure 12 is a perspective view of a vertical guide fixed to the rear arch of the cradle according to the third embodiment of the invention; FIG. 13 is an end view of the rear end of a turboprop received in a rear bow of its cradle; FIG. 14 is an axial end view of the rear end of a turboprop engine and a rear rollbar of its cradle, between which is interposed a guide kit according to a fourth embodiment of the invention; FIG. 15 is a detailed axial view of the mounting on a turboprop suspension ring of an ear-shaped element for the fourth embodiment of the guide kit according to the invention; FIG. 16 is a detailed perspective view of the mounting on the suspension ring of the ear-shaped element for the fourth embodiment of the guide kit according to the invention; - Figure 17 is an end view of the rear end of a turboprop engine and a rear arch of its cradle between which is interposed a guide kit according to a fifth embodiment of the invention; FIG. 18 is an axial view of a suspension ring associated with an ear-shaped element for the fifth embodiment of the guide kit according to the invention; FIG. 19 is a detailed perspective view of the mounting on the suspension ring of the ear-shaped element for the fifth embodiment of the guide kit according to the invention.

In the following description, like reference numerals designate like parts or having similar functions.

FIG. 1 shows a turboprop engine 10 of general orientation A carried by a nacelle 12 suspended under the wing 14 of an aircraft 16. The nacelle essentially comprises a cradle 18 which is composed for example of two arches 20, 22 front and rear open towards the bottom of Figure 1, and interconnected by a mesh of connecting rods 19 of Figure 2. The cradle 18 envelops the turboprop 10 while leaving free its lower part 24, especially for purposes The turboprop is coupled to a propeller 26.

As illustrated more particularly in Figure 2, the cradle 18 comprises two arches 20, 22 which each have an inverted U-shape. The front arch 20 thus has a transverse branch 28 and two vertical branches 30, and likewise the rear arch 22 has a transverse branch 32 and two vertical branches 34.

The turboprop 10 is fixed to the front bow 20 by means of suspensions 36 which are intended for example to be interposed between the turboprop and the vertical branches 30 of the front bow 20. In FIG. 3, for example shown a suspension 36 interposed between a casing 44 of a turboprop reduction gear and the front bow 20 of the cradle 18.

The turboprop 10 is fixed to the rear bow 22 by means of a suspension ring 38 which is intended to surround a rear part of the turboprop 10 and which is suspended between the vertical branches 34 of the rear bow by the intermediate suspensions 40 consist of flexible pads which are intended to be interposed inter alia between the suspension ring 38 and the vertical branches 34 of the rear bow 22.

As can be seen in FIG. 3, the turboprop 10 also comprises rings 46, 50 intended to allow its lifting and suspension in order to allow it to rise / descend along the cradle 18. For example, the gearbox housing 44 of the turboprop 10 comprises a front ring 46, and an exhaust casing 48 of the turboprop 10 comprises a rear ring 50.

In known manner, it is customary to arrange the cradle 18 as close as possible to the turboprop 10 in order to reduce the aerodynamic drag of said cradle 18.

This proximity may be problematic when it is necessary to mount or remove the turboprop 10.

Indeed, when it is desired for example to deposit the turboprop 10, it is necessary to support it, then to disassemble the suspensions 36, 40 linking the turboprop 10 to the hoops 20, 22 of the cradle 18, then finally down the turboprop 10 .

There are several ways to support the turboprop 10. This operation can be carried out by means of lifting platforms, scissor bridges, or props, or more simply, as illustrated in FIG. chains and hoists. FIG. 3 represents carrying means 52 known by the English acronym of "bootstrap" which make it possible to support the turboprop 10. These carrying means essentially comprise a carrying structure 54 which is capable of being fixed or to rest on an upper portion 56 of the cradle 18 and which carries a longitudinal beam 58 adapted to be disposed above the turboprop 10, the ends of said beam 58 carrying chain hoists, which have been shown in Figure 3 under the form of simple chains 60, whose ends are fixed to the rings 46, 50 of the turboprop 10.

The turboprop 10 is adapted to be lowered and removed from the cradle 18 to be deposited on a frame or a carriage (not shown).

In this configuration, it is understood that during the raising or lowering of the turboprop 10, when the suspensions 36, 40 are dismounted and the turboprop 10 is not yet supported by any frame or trolley, said turboprop 10 is able to swing transversely to the axial direction A, thus risking to come into contact with the vertical arms 30, 34 of the arches 20, 22 of the cradle 18, or with the rods 19 of the cradle 18. The invention remedies to this disadvantage by proposing a solution of vertical guidance and transverse thrust of the turboprop 10 in the cradle 18 during its rise or descent.

For this purpose, the invention proposes a kit 62 for guiding an axially oriented aircraft turbine engine A, such as a turboprop 10, during the raising or lowering of the turboprop 10 along the cradle 18 to which it is suspended, which comprises guide means in a substantially vertical direction of the turboprop 10 in said cradle 18, also forming a transverse stop for said turboprop 10 in said cradle 18, which are configured to be interposed between said cradle 18 and said turboprop 10 substantially at the longitudinal ends of the turboprop 10.

The embodiments which will now be described in the following description apply to a guide kit 62 for the installation / removal of a turboprop 10, but it will be understood that these examples of guide kits can also be used. be used for the installation / removal of another type of turbomachine, without limitation of the invention.

In all the embodiments of the invention which have been represented in FIGS. 4 to 6, the vertical guide and transverse stop means are adapted to a cradle 18 of the type described above, that is to say having a hoop before 20 and a rear arch 22 connected by connecting rods 19. The vertical guide means and transverse holding are interposed between said arches 20, 22 and the turbomachine 10.

According to a first embodiment which has been represented in FIGS. 4 to 6, the vertical guide and transverse stop means comprise at least two first members 64 configured to be fixed transversely on either side of an end of a the casing of the turbomachine 10 instead of the suspensions 36, for example the housing 44 of the turboprop reducer 10. As illustrated in Figures 4 and 6, these first members 64 having at their free ends means 66 for sliding or bearing configured to cooperate with vertical rails 68 carried by the vertical legs 30 of the front bow 20.

As illustrated in FIG. 4, each member 64 comprises a fixing plate 70 configured to cooperate with the casing 44 of the turboprop 10.

In the nonlimiting embodiment which has been shown here, the member 64 is shaped in the form of an arm extending substantially transversely relative to the plate 70 which is fixed by means of screws on the housing 44 of the turbomachine 10. For this purpose, the plate 70 has holes 72 for the passage of fixing screws, studs, or any other fastening means coaxial with the bores 72. The holes 72 are for example four in number .

The plate 70 is preferably intended to be fixed to the casing 44 in place of the suspensions 36 of the turboprop 10 as soon as the turboprop 10 is suspended. The member 64 comprises at least one arm 74 projecting from said plate 70. The arm 74 extends substantially perpendicularly from the plate 70, that is to say also substantially transversely to the axial direction A of the turboprop 10 as shown in FIGS. 1 to 3. The rolling or sliding means 66 are arranged at the free end of the arm 74.

It will be understood that this configuration is not limiting of the invention, and that the arm 74 could extend inclined or even parallel to the axis A, and that the rolling or sliding means 66 could be arranged in an intermediate portion of the arm 74 without changing the nature of the invention.

There are several ways to achieve the means 66 rolling or sliding. In the preferred embodiment of the invention, the rolling means 66 comprise at least one guide roller 76 which is carried by the arm 74 and whose axis is perpendicular to a vertical direction V. This configuration makes it possible to ensure a rolling of the at least one roller 76 on any vertical orientation track 68.

Preferably, the rolling means 66 comprise two superimposed guide rollers 76, which are mounted in a yoke 78 formed at the end of the arm 74. With respect to an assembly comprising a single roller 76, this configuration makes it possible to ensure contact of the two rollers 76 along two bearing points, and to prevent the arm 74 from pivoting about the axis of a roller 76, and that consequently the turboprop 10 can not pivot about its axis A of one side or another and risk being unbalanced.

It will be noted that the rollers 76 could advantageously be replaced by a sliding element made of a material with a low coefficient of friction, such as a Teflon pad.

As illustrated in Figures 5 and 6, each member 64 is configured, as has been seen, to cooperate with a substantially vertical guide rail 68 oriented in the direction V and adapted to be carried by the cradle 18. Preferably each rail 68 is configured to be carried by a vertical leg 30 of the front bow 20 of the cradle 18.

Thus, the guide kit 62 comprises at least two members 64 and two guide rails 68, each member 64 being intended to be selectively mounted or disassembled from the housing 44 and each rail 68 being intended to be mounted on one of the branches 30 of the front arch 20 of the cradle 18. Figures 5 and 6 show the kit 62 in place, interposed between the turboprop 10 and the cradle 18.

As has been seen, the members 64 are configured to be fixed instead of suspensions 36 of the turboprop 10 to the cradle 18, via their plates 70.

This configuration is not limiting of the invention, since the members 64 could be fixed to the casing 44 of the turboprop 10 while the suspensions 36 would still be in place on the casing 44, although necessarily disengaged from the cradle 18 to allow the descent of the However, the surface available on the surface of a casing 44 of turboprop 10 being generally reduced, the replacement of each suspension 36 by a member 64 optimizes the number of fixing points to be provided on the casing 44 when its design, without multiplying the number of machining for the attachment of organs 64 which are used relatively rarely, ie during the installation / removal of the turboprop 10.

As illustrated in FIGS. 5 and 6, each guide rail 68 has a plate extending vertically and it comprises at least a first vertical wall 80 configured to form a track cooperating with the rolling or sliding means 66 and at least a second wall 82 configured to be fastened to one of the arms 30 of the arch 20 of the cradle 18. Each rail 68 is preferably made from a T or L-section section section also called angle iron, but it will be understood that it could take other forms, in particular that of a U-section section.

More particularly, in the case where the rolling or sliding means 66 comprise rollers 76, the first vertical wall 80 may comprise a groove 84 adapted to receive the rollers 76, as shown in FIG.

The second vertical wall 82 of the profile constituting the rail 68 is intended to be fixed to a vertical arm 30 of the arch 20. For this purpose, it comprises at least two bores 150 in the figure which are configured to receive fixing screws (not shown) at the vertical arm 30 of the arch 20.

In the preferred embodiment of the invention, the first vertical wall 80 is oriented parallel to the axis A of the cradle 18 and the turboprop 10, and the second vertical wall 82 is oriented transversely to the axis A of the cradle 18 and turboprop 10, as shown in FIG.

According to a second embodiment which has been shown in FIG. 7, the kit 62 is more particularly suitable for being associated with a turbomachine 10 comprising a turboprop propeller hub 86 which extends axially out of the cradle 18. The means vertical guide and transverse support comprise at least two frames 88, which are fixed to vertical branches 30 of the front bow 20, which extend to a transverse plane of said hub 86, and which carry vertical pads 90 sliding members configured to be applied on either side of said hub 86.

More particularly, as illustrated in FIG. 8, each frame 88 is shaped in the form of an armature 92 which extends in a plane parallel to the axial direction and which comprises plates 104 for fastening to the vertical branches 30 of the frame. For example, the plates 94 comprise holes 96 intended to receive fastening screws to the vertical branches 30 of the arch 20. Opposite the plates 94, each frame 88 comprises tubular guides 98 for receiving sliding the rods 100 of a support 102 of the shoe 90 shown in Figure 9, so as to allow the transverse adjustment of the support 102 relative to the frame 88 to allow the adaptation of the spacing of the pad 90 relative to the hub 86.

In the preferred embodiment of the invention, each frame 88 has three tubular transverse guides 98, but it will be understood that this feature is not limiting of the invention.

Preferably, the pads 90 are adapted to be inserted into a groove 104 shown in Figure 7 of the hub 86. The pads 90 are made of a low coefficient of friction material, for example a Teflon type material.

Advantageously, the supports 102 of the pads 90 diverge from each other in their lower part 103 (FIG. 7), so as to propose a flared introduction zone 105 facilitating the vertical introduction of the hub 86 during its ascent when the turboprop 10 is raised in the cradle 18.

As is illustrated in FIGS. 10 to 12, according to a third embodiment of the invention which is more particularly devoted to guiding a rear end 145 of the turboprop 10, the vertical guiding and transverse holding means of the kit 62 comprise at least one second member 106 which is configured to be fixed to an upper part of a casing of the rear end 145 of the turbomachine 10, in particular to the exhaust casing 48 of the turbomachine 10. The second member 106 comprises a vertical slider 108 which is configured to be received between two vertical rails 110 carried by the transverse branch 32 of the rear bow 22.

More particularly, as shown in Figure 11, the second member 106 has a fastening portion 112 in the form of a circular arc which is adapted to fit the shape of the exhaust casing 48 and to be fixed thereto.

The vertical slide 108 extends vertically from this attachment portion 112.

As illustrated in FIG. 12, the rails 110 between which the slider 108 is received extend vertically. They comprise in their upper parts fastening plates 114 provided for example with holes 116 intended to receive fastening screws to the transverse branch 32 of the rear arch 22. In their lower parts, the rails 110 are connected to each other. the other by a bar 118 which prevents their spacing.

The rails 110 are preferably made in the form of profiles from which extend transversely towards each other of the yokes 120 in which are received a plurality of rollers 122 superimposed horizontal axes, intended to receive the slide 108 .

It will be understood that this configuration is not limiting of the invention, and that the yokes 120 and the rollers 122 could be replaced by sliding pads of low friction material, similarly to the second embodiment of the invention. invention.

As illustrated in FIGS. 13 to 19, according to fourth and fifth embodiments of the invention which are also devoted to guiding the rear end 145 of the turboprop 10, the kit 62 is associated with a turbomachine 10 which is configured to be fixed to the rear arch 22 of the cradle 18 by means of a suspension ring 38 surrounding the casing 48 of the turbomachine. Such a ring 38 has been shown in FIGS. 2 and 13.

In these embodiments, the transverse guiding and holding means comprise two elements 124 (shown in particular in FIG. 15) in the form of a transversely opposed ear and made of a material of a hardness lower than that of the arch 18. These elements 124, of substantially triangular shape, are configured to be fixed to the suspension ring 38 and to be received with a set "J" determined, as shown in Figure 15, between inner faces 126 (Figure 14) of Vertical branches 34 of the rear arch 22. The material of the elements 124, of a hardness lower than that of the arch 22, makes it possible to absorb the possible transverse shocks induced by a possible rocking of the rear engine without degrading the arch 22.

The ear-shaped elements 124 can be made in two different ways. According to the fourth embodiment of the invention, as shown in Figure 16, each ear-shaped element 124 comprises a pair of plates 128 of plastic material (or other but whose hardness is less than that of the hoops of the cradle ) which are configured to take the suspension ring 38 sandwiched, which are joined by an attachment pin 130 passing through an ear 132 of the suspension ring 38 and by at least two pins 134 which bear on the periphery of the ring 38 to prevent rotation of said element 124 in the form of an ear.

In this case, each element 124 can be mounted very simply on a pre-existing ear 132 of the suspension ring 38.

According to the fifth embodiment of the invention, as shown in FIG. 19, each ear-shaped element 124 comprises at least one plate 140 which is configured to be fixed to the suspension ring 38 via at least two axial members 142 passing through said plate 140 and two corresponding lugs 132, 144 of the suspension ring 38 (FIG. 18).

In this case, it will be understood that the turboprop 10 is preferably provided with a specific suspension ring 38 having a specific additional lug 144 for receiving one of the axial members 142, as shown in FIGS. 18 and 19.

Whatever the embodiment of the kit 62 envisaged, the turboprop 10 may be deposited using the kit or kits 62 according to a dispensing process which comprises firstly a first step during which the turboprop engine 10 is supported. using the carrying means 52. Then, during a second step is deposited the connecting elements connecting the turboprop 10 to the cradle 18, including the suspensions 20 and 40. During this step, is interposed or the kits 62 between the turboprop 10 and the cradle 18.

Then, during a fourth step during which a turbo-propeller receiving means 10 is positioned, such as a support frame or a carriage under the cradle 18. Finally, during a fifth step, it is lowered the turboprop 10 vis-à-vis the cradle 18 until it is received on the receiving means.

And conversely, for a motor mounting operation in the cradle.

It will be understood that preferably, during the second step, there is at least one element of the kit 62 in place of a connecting element or suspension 20, 40 of the turboprop 10 to the cradle 18. Indeed, in the as the suspension elements 20, 40 must be disconnected from the cradle 18, it is advantageous to also remove them from the turboprop 10 so as to release anchors for fixing certain elements of the kit 62. This solution makes it possible to have no bosses or other on the turbomachine used only for hoisting the engine (gain mass). The invention makes it possible to considerably simplify and make reliable the operations of laying / removing a turboprop engine 10 in particular or a turbomachine in general with respect to a cradle.

Claims (12)

1. Kit (62) for guiding a longitudinally oriented aircraft turbine engine (10), such as a turboprop (10), during the raising or lowering of said turbomachine from a cradle ( 18) of said aircraft (16) to which it is suspended, characterized in that it comprises guide means in a substantially vertical direction of the turbomachine (10) in said cradle (18), said guide means forming a transverse stop for said turbomachine (10) in said cradle (18), and being configured to be interposed between said cradle (18) and said turbomachine (10) substantially at the longitudinal ends of said turbomachine (10). 2. Kit (62) according to the preceding claim, characterized in that the guide means are adapted to a cradle (18) having a front bow (20) and a rear bow (22) connected by connecting rods (19) and said guide means are interposed between said arches (20, 22) and the turbomachine (10). 3. Kit (62) according to the preceding claim, characterized in that the guide means comprise at least two first members (64) configured to be fixed transversely on either side of an end of a housing (44). the turbomachine and having at their free ends sliding or rolling means (66) configured to cooperate with vertical rails (68) carried by vertical branches (30) of the bow (20). 4. Kit (62) according to one of claims 2 and 3, characterized in that it is adapted to be associated with a turbomachine (10) having a hub (86) turboprop propeller which extends axially out of the cradle (18) and in that the guide means comprise at least two frames (88), which are fixed to vertical branches (30) of the front bow (20), which extend to a plane transverse of said hub (86), and which carry vertical sliding pads (90) configured to be applied on either side of said hub (86). 5. Kit (62) according to the preceding claim, characterized in that the pads (90) are carried by supports (102) adjustable transversely relative to the frames (88) to allow the adaptation of the spacing of said pads (90). ) relative to the hub (86). 6. Kit (62) according to one of claims 2 to 5, characterized in that the guide means comprise at least a second member (106) configured to be fixed to an upper portion of a housing (48) of the turbomachine and comprising a vertical slider (108) configured to be received between two vertical rails (110) carried by a transverse branch (32) of the bow (22). 7. Kit (62) according to one of claims 2 to 6, characterized in that it is adapted to be associated with a turbomachine (10) configured to be fixed to the rear bow (22) of the cradle (18) by means of a suspension ring (38) surrounding a casing (44) of the turbomachine, and in that the transverse guiding and holding means comprise two ear-shaped elements (124) transversely opposed and made in a material of a hardness less than that of the rear bow (22) which are configured to be fixed to said suspension ring (38) and to be received with play between inner faces (126) of the vertical legs (34) said rear arch (22). 8. Kit (62) according to the preceding claim, characterized in that each element (124) in the form of an ear comprises a pair of plates (128) of plastic material which are configured to take the ring (38) suspension in sandwiching, which are joined by a fixing pin (130) passing through an ear (132) of the suspension ring (38) and by at least two pins (134) bearing on the periphery of the ring (38) to prevent rotation of said ear-shaped member (124). 9. Kit according to claim 7, characterized in that each element (124) in the form of an ear comprises at least one plate (140) which is configured to be fixed to the ring (38) of suspension via at least two axial elements (142) passing through said plate and two corresponding lugs (132, 144) of the suspension ring (38). 10. An assembly comprising an aircraft turbomachine (10), in particular a turboprop engine, and a support cradle (18) of said turbomachine, characterized in that it is equipped with at least one kit (62) according to one of Claims 1 to 9. 11. A method of laying / removing an aircraft turbomachine (10), in particular a turboprop, a cradle (18), by means of a kit (62) according to one of claims 1 to 9, characterized in that it comprises: a step during which the turbomachine (10) is supported; a step during which connection elements (20, 40) are deposited connecting the turbomachine (10) to the cradle (18) and during which the kit (62) is interposed between the turbomachine (10) and the cradle (18); a step during which a means for receiving the turbomachine (10) is positioned under the cradle (18), and a step during which the turbomachine (10) is lowered with respect to the cradle (18); ) until it is received on said receiving means. 12. A method of removing an aircraft turbomachine according to the preceding claim, characterized in that during the second step, there is at least one element of the kit (62) in place of a connecting element (20, 40) of the turbomachine (10) to the cradle (18).