Tool for mounting a degassing tube in a hollow shaft of an aircraft turbine engine, and method using the tool

Abstract

The present invention relates to a tool (4) for mounting a degassing tube in a hollow shaft of an aircraft turbine engine, the tool comprising a tubular body (5) that has an elongate shape along an axis (A), and comprising: - an internal longitudinal passage (50) extending over the entire longitudinal dimension of the body (5) and configured to accommodate the degassing tube; and - a longitudinal slot (51) that extends over the entire longitudinal dimension of the body (5) and which opens into the passage (50), wherein this slot (51) is configured to allow the degassing tube to be inserted into the passage (50) by translationally moving the degassing tube through the slot (51) in the transverse direction, and wherein the body (5) is formed by assembling a first axial segment (6) made of a first material and a second axial segment (7) made of a second material different from the first material.

Description

[0001] DESCRIPTION

[0002] TITLE: TOOLING FOR MOUNTING A DEGASSING TUBE IN A HOLLOW SHAFT OF AN AIRCRAFT TURBOMACHINE, AND METHOD USING THE TOOLING

[0003] Technical field of the invention

[0004] The present invention relates to the field of aircraft turbomachines. More particularly, the present invention relates to a tool for mounting a degassing tube in a hollow shaft of a turbomachine, and a method for mounting a degassing tube in a hollow shaft using such a tool.

[0005] Technical background

[0006] The state of the art includes in particular documents US-A1 -3722058, FR-A1 -3107717 and US-A1 -2013 / 008550.

[0007] Conventionally, an aircraft turbomachine comprises from upstream to downstream (i.e. in the direction of flow of the gas flows), a fan, one or more compressor stages (for example a low pressure compressor and a high pressure compressor), a combustion chamber, one or more turbine stages (for example a high pressure turbine and a low pressure turbine), and a gas exhaust nozzle.

[0008] The turbomachine includes a degassing tube that runs longitudinally through the turbomachine to the exhaust nozzle. The function of this degassing tube is to channel the air discharged from the turbomachine to the exhaust nozzle.

[0009] More particularly, the degassing tube is mounted coaxially inside a hollow drive shaft of the turbomachine (in particular the turbine). The degassing tube can be connected at its upstream end to a lubrication enclosure inside which is housed a guide and centering bearing. The lubricating oil of the bearing mixes with air, and this oil penetrates and circulates inside the degassing tube to be separated from the air and recovered downstream.

[0010] The degassing tube is for example fixed at its downstream end on the hollow shaft and aligned on a longitudinal axis of this shaft. In order to facilitate the assembly of the degassing tube in the hollow shaft, tooling may be necessary which is simple to use and without risk of damaging the tooling, the degassing tube, the hollow shaft and / or more generally the turbomachine. For example, such tooling can be produced by limiting fasteners such as bolts and screws to avoid in particular any risk of unscrewing screws of the tooling during assembly of the degassing tube in the hollow shaft. There is therefore a need to identify a simple and reliable tooling solution for the assembly of a degassing tube in a hollow shaft of an aircraft turbomachine.

[0011] Summary of the invention

[0012] The present invention provides a simple, effective and economical solution to at least some of the above-mentioned problems.

[0013] The invention provides a tool for mounting a degassing tube in a hollow shaft of an aircraft turbomachine, the tool comprising a tubular body which has an elongated shape along an axis, this tubular body comprising:

[0014] - an internal longitudinal passage extending over the entire longitudinal dimension of the tubular body and configured to receive a degassing tube, and

[0015] - a longitudinal slot which extends over the entire longitudinal dimension of the tubular body and which opens into the internal longitudinal passage, this longitudinal slot being configured to allow the insertion of the degassing tube into the passage by translation in the transverse direction of the degassing tube through the longitudinal slot, the tubular body being produced by assembling a first axial section made of a first material and a second axial section made of a second material different from the first material.

[0016] Thus, this solution makes it possible to achieve the aforementioned objective. In general, the tooling according to the invention makes it possible to facilitate and make reliable the assembly of the degassing tube in the hollow shaft. To this end, the tooling proposes to produce the tubular body by integrating, on the one hand, the internal longitudinal passage and the longitudinal slot, and on the other hand, the first and second sections made of separate materials and assembled together.

[0017] The internal longitudinal passage and the longitudinal slot make it possible to simplify the insertion of the degassing tube into the tubular body to facilitate the guiding and centering of the degassing tube in the hollow shaft (in particular with respect to a longitudinal axis of the hollow shaft).

[0018] Advantageously, the tubular body can be produced by screwing or clipping the first axial section and the second axial section together. The screwing or clipping assembly allows axial locking and blocking of the first and second sections together when using the tooling. The screwing assembly is simple to produce, while ensuring an effective and robust connection between the first and second axial sections. The clipping assembly has the advantage of limiting the use of bolt and screw type fasteners which, as described above, can unscrew and fall into the turbomachine. Furthermore, the screwing or clipping assembly can be reversible and thus allow one of the sections to be repaired or replaced in the event of wear. In addition, the first and second sections are made of different materials so as to deform one of these sections and facilitate the screwing or clipping of one into the other.The axial section made of the most flexible material is, for example, capable of bearing on the hollow shaft without damaging it. "Screwing" means an assembly of at least one part of the sections into the other, such as by a threaded portion tightened complementary to a tapped portion (or in other words the complementary portion having internal threads).

[0019] “Clip-on” means an assembly of at least one part of the sections into the other, such as by interlocking.

[0020] The tooling according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in comparison with one another:

[0021] -- the tubular body has a U or C shape in cross section;

[0022] - the first axial section comprises a first part of the internal longitudinal passage and a first part of the longitudinal slot, the second axial section comprises a second part of the internal longitudinal passage and a second part of the longitudinal slot, a first longitudinal end of the second axial section being assembled (for example by screwing or by clipping) in a second longitudinal end of the first axial section by rotation or by translation in the transverse direction of the second axial section in the first part of the internal longitudinal passage through the first part of the longitudinal slot, or vice versa,the second longitudinal end of the first axial section being assembled (for example by screwing or by clipping) in the first longitudinal end of the second axial section by rotation or by translation in the transverse direction of the first axial section in the second part of the internal longitudinal passage through the second longitudinal slot part;,

[0023] - the first longitudinal slot portion of the first axial section has an opening angle which is less than that of the second longitudinal slot portion of the second axial section, this opening angle being measured in a plane perpendicular to the axis A and the center of the opening angle of which is located on this axis A;

[0024] - one of the first and second axial sections comprises a circumferential rim which is engaged in a circumferential groove of the other axial section and which is retained axially in this circumferential groove by axial abutment of the circumferential rim with side walls of the circumferential groove;

[0025] - said axial section which comprises the circumferential rim or the circumferential groove comprises a pair of clipping teeth which are configured respectively with longitudinal edges of the other axial section;

[0026] - the pair of clipping teeth is located at the longitudinal slot portion of the first axial section, and the longitudinal edges are those of the longitudinal slot portion of the second axial section;

[0027] - the first axial section has a third free longitudinal end which is beveled and comprises a generally truncated cone shape;

[0028] - the second axial section has a fourth free longitudinal end which comprises fixing lugs and / or holes, preferably guide rollers or pads;

[0029] - the tooling further comprises a frame for supporting and guiding the tubular body, this frame having a generally elongated shape and comprising a longitudinal end capable of being fixed to a shaft or to a turbomachine element, the frame comprising:

[0030] - two side walls extending along the axis A and capable of receiving the tubular body between them, and

[0031] - two slide rails carried respectively by the side walls and capable of receiving guide rollers or pads carried by the tubular body so as to be able to move the tubular body in translation along its axis A relative to the frame;

[0032] -- the longitudinal end of the frame comprises a fixing strapping capable of being crossed by the tubular body; - the frame further comprises crosspieces for connecting the side walls, which extend between the side walls, two of these crosspieces being separated from each other by a distance greater than a maximum length of the tubular body so as to be able to move the tubular body between these crosspieces, by translation in a transverse direction relative to the axis A of the tubular body;

[0033] - the frame comprises a bottom wall, the lateral ends of which are fixed respectively to the side walls, this bottom wall being located between the two crosspieces and being capable of receiving the tubular body after its translation;

[0034] -- the back wall has a general U or C shape;

[0035] - the rails include windows for the passage of the rollers or guide shoes, in order to allow the tubular body to move between the sleepers and up to the bottom wall;

[0036] -- the frame further includes two side handles located respectively on the two side walls;

[0037] -- the first axial section comprises a circumferential notch located between its circumferential rim and its first circumferential groove;

[0038] -- the first longitudinal end of the second axial section comprises external threads complementary to the internal threads of the second longitudinal end of the first axial section.

[0039] The present invention also relates to a method of mounting a degassing tube in a hollow shaft of an aircraft turbomachine using a device according to one of the features of the invention.

[0040] The method includes the following steps:

[0041] - assembly of the tooling by assembling the first and second axial sections (for example by screwing or clipping),

[0042] - installation of the tooling by aligning it with the hollow shaft, - insertion of the degassing tube into the internal longitudinal passage by translation in the transverse direction of the degassing tube through the longitudinal slot,

[0043] - mounting the degassing tube in the hollow shaft by a first translation along a first transverse direction of the degassing tube along the axis A, and

[0044] - removal of the tool by a second translation following a second transverse direction opposite to the first translation.

[0045] The method may comprise a step of mounting the tubular body to the frame by assembling the slide rails to the rollers or guide pads of the tubular body, which is carried out between the assembly (for example by screwing or by clipping) of the first and second axial sections and the step of inserting the degassing tube into the internal longitudinal passage.

[0046] Brief description of the figures

[0047] The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which: Figure 1 is a partial schematic sectional view of an aircraft turbomachine comprising a degassing tube mounted in a hollow shaft, Figure 2 is a schematic perspective view of a tool according to an embodiment of the invention for mounting the degassing tube in the hollow shaft of Figure 1, Figure 3 is a half schematic top view of a first axial section of the tool of Figure 2, Figure 4 is a partial schematic perspective view of the tool of Figure 2, Figure 5 is another partial schematic perspective view of the tool of Figure 2, Figure 6 is a partial schematic top view of the tool of Figure 2 or Figure 4,Figure 7 is a partial schematic and profile view of a first example of clip-on assembly of the first and second axial sections of the tooling of Figure 2, Figure 8 is a partial schematic and profile view of a second example of clip-on assembly of the first and second axial sections of the tooling of Figure 2, Figure 9 is a partial schematic and perspective view of a third example of screw-on assembly of the first and second axial sections of the tooling of the invention, Figure 10 is a schematic and perspective view of a tooling according to another embodiment of the invention for mounting the degassing tube in the hollow shaft of Figure 1, Figure 11 is a partial schematic and perspective view of the degassing tube inserted in the tooling of Figure 2, Figure 12 is a partial schematic and perspective view of the degassing tube inserted in the tooling of Figure 10,Figure 13 is a partial schematic and perspective view of an assembly of the degassing tube in the hollow shaft by the tooling of Figure 10, Figure 14 is a partial schematic and perspective view of a removal of the tooling of Figure 10, Figure 15 is a partial schematic and perspective view of the continuation of the removal of the tooling of Figure 14.,

[0048] Elements having the same functions in different implementations have the same references in the figures.

[0049] Detailed description of the invention

[0050] Generally speaking, in the description below, the terms "longitudinal" and "axial" describe the orientation of structural elements extending in the direction of a longitudinal axis (such as that of an aircraft turbomachine). This axis may be confused with an axis of rotation of a rotor of a turbomachine. The term "radial" describes an orientation of structural elements extending in a direction perpendicular to the longitudinal axis. The terms "inner" and "outer", and "internal" and "external" are used with reference to a positioning relative to the longitudinal axis. Thus, a structural element extending along the axis has an inner face facing the axis and an outer surface, opposite its inner surface. Similarly, the terms "upstream" and "downstream" are defined with respect to the direction of airflow in the turbomachine.

[0051] With reference to Figure 1, an aircraft turbomachine 1 comprises, in a non-limiting manner, from upstream to downstream, a fan (not illustrated in Figure 1), a low pressure compressor 1 a, a high pressure compressor 1 b, a combustion chamber 1 c, a high pressure turbine 1 d and a low pressure turbine 1 e and a gas exhaust nozzle (not illustrated in Figure 1).

[0052] The high-pressure turbine 1e can drive the high-pressure compressor 1b via a high-pressure shaft (or otherwise called a turbine shaft and referred to in the present application as a hollow shaft 2) and these elements form a high-pressure body. The low-pressure turbine 1d can drive the low-pressure compressor 1a via a low-pressure shaft coaxially inside the high-pressure shaft, and these elements form a low-pressure body.

[0053] The hollow shaft 2 extends along a longitudinal X which can correspond substantially to a general axis of the turbomachine 1.

[0054] The turbomachine 1 may comprise a degassing tube 3. The degassing tube 3 may pass longitudinally through the turbomachine 1 to the gas exhaust nozzle.

[0055] More particularly, the degassing tube 3 may be mounted coaxially inside the hollow shaft 2. The degassing tube 3 may be hollow and cylindrical. The degassing tube 3 may comprise several successive hollow portions: an upstream portion 31, a downstream portion 33 and a central portion 32 connecting the upstream 31 and downstream 33 portions together. The upstream portion 31 may comprise a plurality of holes intended to allow the evacuation of gases in the degassing tube 3, while the downstream portion 33 opens onto a gas evacuation mouth located for example in the exhaust nozzle.

[0056] The downstream portion 33 may comprise at least one annular collar 34, 35. More particularly, the degassing tube 3 may comprise first 34 and second 35 annular collars extending radially outwards, in particular at the end of the downstream portion 33. These first 34 and second 35 annular collars make it possible to hold the degassing tube 3 in position in the hollow shaft 2 by means of a tool 4 as described below. For example, a seal may be positioned around the first collar 34 to ensure the centering of the degassing tube in the hollow shaft without damaging it. The second collar 35 also allows the centering of the degassing tube and may also ensure its axial locking in the turbomachine.

[0057] As described above, this degassing tube 3 has the function of channeling the air discharged from the oil of the turbomachine 1 to the gas exhaust nozzle. The degassing tube 3 can be mounted in the hollow shaft 2 with specific tooling 4.

[0058] This application will now describe the different possible configurations of the tool 4, in particular with reference to figures 3 to 10.

[0059] The tool 4 comprises a tubular body 5 which has an elongated shape along an axis A. This axis A can be substantially in the continuity of the longitudinal axis X of the hollow shaft 2 when the tool 4 is installed in the turbomachine (in particular at the level of the hollow shaft 2) to mount the degassing tube 3.

[0060] The tubular body 5 may have a U or C shape in cross section. The tubular body 5 comprises:

[0061] - an internal longitudinal passage 50 extending over the entire longitudinal dimension of the tubular body 5 and configured to receive the degassing tube 3, and

[0062] - a longitudinal slot 51 which extends over the entire longitudinal dimension of the tubular body 5 and which opens into the internal longitudinal passage 50, this longitudinal slot 51 being configured to allow the insertion of the degassing tube 3 into the internal longitudinal passage 50 by translation in the transverse direction of the degassing tube 3 through the longitudinal slot 51.

[0063] The tubular body 5 is produced by assembling a first axial section 6 made of a first material and a second axial section 7 made of a second material different from the first material. In other words, the tubular body 5 may comprise the first section 6 and a second section 7 which are assembled at least partially into each other.

[0064] Advantageously, the tubular body 5 can be produced by assembly by screwing (figure 9) or by clipping (figures 2 to 8 and 10) of the first axial section 6 and the second axial section 7.

[0065] In the example of Figures 2 to 10, the first axial section 6 may comprise a first portion 60 of the internal longitudinal passage 50, called the first passage portion 60, and a first portion 61 of the longitudinal slot 51, called the first slot portion 61. The second axial section 7 may comprise a second portion 70 of the internal longitudinal passage 50, called the second passage portion 70, and a second portion 71 of the longitudinal slot 51, called the second slot portion 71. The first 60 and second 70 passage portions may form the internal longitudinal passage 50 of the tubular body. Generally, the first 61 and second 71 slot portions may form the longitudinal slot 51 of the tubular body. When the first 6 and second 7 axial sections are mounted together, the first passage 60 and slot 61 portions can be aligned along the axis A with, respectively, the second passage 70 and slot 71 portions.

[0066] Advantageously, the first slot portion 61 may have a first opening angle aei and the second slot portion 71 may have a second opening angle a?i. These opening angles aei, a?i may be measured in a plane perpendicular to the axis A and the center of the opening angle of which is located on this axis A. For example, the first opening angle aei may be between 70° and 180°. The second opening angle a?i may be between 100° and 190°, preferably approximately 180°.

[0067] In the example of the figures, the first opening angle aei can be less than the second opening angle a?i (figure 5).

[0068] The first material for producing the first axial section 6 may be a plastic material, such as polyethylene (HDPE) or resin. Preferably, the first material may be more flexible than the second material. This makes it possible in particular to avoid damaging the surface of the turbomachine 1 (such as that of the hollow shaft 2) on which the first axial section 6 bears when using the tool 4. In addition, assembly by screwing or clipping is facilitated.

[0069] The first axial section 6 may comprise a second longitudinal end 62. This second longitudinal end 62 may be assembled with a first longitudinal end 72 of the second axial section 7.

[0070] The first axial section 6 may comprise a third longitudinal end 64. This third longitudinal end 64 may be free. The third longitudinal end 64 may be beveled and may comprise a generally truncated cone shape.

[0071] With reference to Figure 3, the first axial section 6 can extend between the second longitudinal end 62 and the third longitudinal end 64. The first passage portion 60 can be located at the third longitudinal end 64, while the second longitudinal end 62 can receive at least a portion of the first longitudinal end 72 of the second axial section 7. This also makes it possible not to damage the surface of the turbomachine 1 on which the first axial section 6 comes to bear when using the tool 4.

[0072] Advantageously, the first axial section 6 may comprise a first circumferential rim 66 and a first circumferential groove 68. This first circumferential groove 68 may be located between the first circumferential rim 66 and the third longitudinal end 64.

[0073] The first circumferential rim 66 of the first axial section 6 can be engaged in a second circumferential groove 78 of the second axial section 7. The first circumferential rim 66 can thus be retained axially in this second circumferential groove 78 by axial abutment of the first circumferential rim 66 with side walls of the second circumferential groove 78.

[0074] The first circumferential rim 66 or the first circumferential groove 68 may comprise a first pair of clipping teeth 660. This first pair of teeth 660 may be configured to clip with first longitudinal edges 780 of the second axial section 7. In this configuration, the first pair of clipping teeth 660 may be located at the first slot portion 61, and the first longitudinal edges 780 may be those of the second slot portion 71 of the second axial section 7.

[0075] In the example of Figures 2 to 6, the first pair of teeth 660 may be located at the first circumferential rim 66.

[0076] The first circumferential rim 66 may have a first length Lee measured along the axis A. The first circumferential groove 68 may have a second length Les also measured along the axis A. The first length Lee may be less than the second length Les (figure 6).

[0077] The first axial section 66 may comprise a circumferential notch 69. This circumferential notch 69 may be located between the first circumferential rim 66 and the first circumferential groove 68. This circumferential notch 69 makes it possible to provide flexibility or local deformation of the first axial section 66 which facilitates assembly, in particular by clipping.

[0078] The second material for producing the second axial section 7 may be made of a metallic material, such as aluminum. This provides sufficient rigidity to the tubular body 5 to support the degassing tube 3.

[0079] The second axial section 7 may comprise the first longitudinal end 72. This first longitudinal end 72 may be assembled with the second longitudinal end 62 of the first axial section 6.

[0080] The second axial section 7 may comprise a fourth longitudinal end 74. This fourth longitudinal end 74 may be free. The fourth longitudinal end 74 may comprise fixing members 79 for example to a frame 8 as described below. These fixing members 79 may be fixing lugs 79b (figure 10) and / or fixing orifices 79a (figure 2). The fixing lugs 79b may be guide rollers or pads.

[0081] In the example of the figures, the second axial section 7 can extend between the first longitudinal end 72 and the fourth longitudinal end 74. The second passage portion 70 and the second slot portion 71 can extend between the first 72 and fourth 74 longitudinal ends.

[0082] Advantageously, the second axial section 7 may comprise a second circumferential rim 76 and a second circumferential groove 78. This second circumferential groove 78 may be located between the second circumferential rim 76 and the fourth longitudinal end 74.

[0083] The second circumferential rim 76 of the second axial section 7 can be engaged in the first circumferential groove 68 of the first axial section 6. The second circumferential rim 76 can thus be retained axially in this first circumferential groove 68 by axial abutment of the second circumferential rim 76 with side walls of the first circumferential groove 68.

[0084] The second circumferential rim 76 or the second circumferential groove 78 may comprise a second pair of clipping teeth (not visible in the figures). This second pair of teeth may be configured to clip with second longitudinal edges of the first axial section 6. In this configuration, the second pair of clipping teeth may be located at the second slot portion 71, and the second longitudinal edges may be those of the first slot portion 61 of the first axial section 6.

[0085] The second circumferential rim 76 may have a third length LÏ6 measured along the axis A. The second circumferential groove 68 may have a fourth length Les also measured along the axis A. With reference to FIG. 6, the first length Lee may be less than or equal to the fourth length L?s. The difference in length between the first Lee and fourth L?s lengths makes it possible to form an axial clearance between the first circumferential rim 66 and the second circumferential groove 78 in order in particular to facilitate assembly by clipping. The third length LÏ6 may be substantially identical to the second length Les.

[0086] With reference to Figure 7, the second longitudinal end 62 can be assembled by clipping into the first longitudinal end 72 of the second axial section 7 by translation in the transverse direction T of the first axial section 6 in the second passage part 70 through the second slot part 71.

[0087] With reference to Figure 8, the first longitudinal end 72 can be assembled by clipping into the second longitudinal end 62 of the first axial section 6 by translation in the transverse direction T of the second axial section 7 in the first passage part 60 through the first slot part 61. The transverse direction T of the assembly by clipping of the first 6 and second 7 axial sections together can be carried out in a radial direction (or a perpendicular plane) relative to the axis A.

[0088] With reference to Figure 9, the first longitudinal end 72 of the second axial section 7 may comprise external threads complementary to the internal threads of the second longitudinal end 62 of the first axial section 6.

[0089] Tooling 4 of Figure 9 is distinguished from tooling 4 of Figures 2 to 8 by a screwed assembly of the first 6 and second 7 axial sections.

[0090] In particular, the second longitudinal end 62 can be assembled by screwing into the first longitudinal end 72 by rotating the first axial section 6 in the second passage part 70 through the second slot part 71. Alternatively, the first longitudinal end 72 can be assembled by screwing into the second longitudinal end 62 by rotating the second axial section 7 in the first passage part 60 through the first slot part 61.

[0091] The tool 4 may further comprise a support and guide frame 8 for the tubular body 5, referred to below by the abbreviation frame 8.

[0092] With reference to Figure 10, the frame 8 may have a generally elongated shape and may comprise a fifth longitudinal end 80 capable of being fixed to a shaft or to a turbomachine element 1.

[0093] The fifth longitudinal end 80 of the frame 8 may comprise a fixing ring 800 capable of being passed through by the tubular body 5. By “ring”, it may be an annular frame capable of being fixed to the shaft or the turbomachine element 1 and having an opening through which the tubular body 5 (possibly the degassing tube 3) can pass through and slide towards the hollow shaft 2.

[0094] Frame 8 may include:

[0095] - two side walls 81, 82 (such as first 81 and second 82 side walls) extending along the axis A and capable of receiving the tubular body 5 between them, and - two slide rails 810, 820 (such as first 810 and second 820 rails) carried respectively by the side walls 81, 82 and capable of receiving fixing lugs 79b (such as the guide rollers or pads) carried by the tubular body 5 (in particular carried by the second axial section 7) so as to be able to move the tubular body 5 in translation along its axis A relative to the frame 8.

[0096] The frame 8 may further comprise crosspieces 83 for connecting the side walls 81, 82. These crosspieces 83 may extend between the side walls 81, 82. In the example of FIG. 10, the frame 8 may comprise first 83a, second 83b and third 83c crosspieces 83. Two of these crosspieces 83 (such as the first 83a and third 83c crosspieces) may be separated from each other by a distance greater than a maximum length of the tubular body 5 so as to be able to move the tubular body 5 between these crosspieces 83a, 83c, by translation in the transverse direction relative to the axis A of the tubular body 5.

[0097] The frame 8 may further comprise two lateral handles 812, 822 (such as first 812 and second 822 lateral handles) located respectively on the two lateral walls 81, 82. These lateral handles 812, 822 make it easier to grip and handle the frame 8. The frame 8 may comprise a bottom wall 84. This bottom wall 84 may have a general U-shaped or C-shaped shape, the lateral ends of which are fixed respectively to the lateral walls 81, 82. The bottom wall 84 may be located between the two crosspieces, such as the second 83b and third 83c crosspieces. The bottom wall 84 may be able to receive the tubular body 5 after its translation, for example for its removal at the end of assembly.

[0098] The rails 810, 820 may comprise windows 814, 824 for the passage of the fixing lugs 79b (such as the guide rollers or pads), in order to allow the movement of the tubular body 5 between the crosspieces 83 (such as the second 83b and third 83c crosspieces) and up to the bottom wall 84. The present application will now describe a method of mounting the degassing tube 3 in the hollow shaft 2, for example with reference to FIGS. 11 to 15.

[0099] Generally, the process may include the following steps:

[0100] - assembly of tool 4 by assembling the first 6 and second 7 axial sections,

[0101] - installation of tool 4 by aligning it with the hollow shaft 2 (in particular along the X axis),

[0102] - insertion of the degassing tube 3 into the internal longitudinal passage 50 by translation in the transverse direction of the degassing tube 3 through the longitudinal slot 51,

[0103] - mounting the degassing tube 3 in the hollow shaft 2 by a first translation along a first transverse direction T1 of the degassing tube 3 along the axis A, and

[0104] - removal of the tool 4 (in particular from the degassing tube 3 mounted in the hollow shaft 2) by a second translation following a second transverse direction T2 opposite to the first translation T1.

[0105] As described above, for example with reference to figures 7 to 9, the step of mounting the tool 4 may comprise:

[0106] - the assembly (for example by screwing or by clipping) of the second longitudinal end 62 of the first axial section 6 in the first longitudinal end 72 of the second axial section 7 by rotation or by translation in the transverse direction of the first axial section 6 in the second passage part 70 through the second slot part 71, or

[0107] - the assembly (for example by screwing or by clipping) of the first longitudinal end 72 in the second longitudinal end 62 of the first axial section 6 by rotation or by translation in the transverse direction of the second axial section 7 in the first passage part 60 through the first slot part 61. The steps of inserting the degassing tube 3 into the internal longitudinal passage 50 and of mounting the degassing tube 3 in the hollow shaft 2 can be reversed.

[0108] Figure 11 illustrates an example of insertion of the degassing tube 3 into the internal longitudinal passage 50 of the tubular body 5.

[0109] With reference to Figure 12, the method may also comprise a step of mounting the tubular body 5 to the frame 8 by assembling the slide rails 810, 820 to the fixing lugs 79b (such as rollers or guide pads) of the tubular body 5. This step of mounting the tubular body 5 to the frame 8 is carried out between the assembly (for example by screwing or by clipping) of the first 6 and second 7 axial sections and the step of inserting the degassing tube 3 into the internal longitudinal passage 50.

[0110] Figure 13 illustrates in a non-limiting manner an example of mounting the degassing tube 3 in the hollow shaft 2 by the first translation along the first direction T1.

[0111] The step of mounting the degassing tube 3 in the hollow shaft 2 can be carried out until at least one of the annular collars 34, 35 of the degassing tube 3 is in axial support on the tubular body 5. For example, the first annular collar 34 can move by translation until it is in axial support on the first axial section 6, such as on a circumferential shoulder 67 of this first axial section 6. This circumferential shoulder 67 can be located between the second 62 and third 64 longitudinal ends.

[0112] Figures 14 and 15 illustrate in a non-limiting manner an example of removal of the tool 4, in which the tubular body 5 (in particular alone without the degassing tube 3) first moves by the second translation along the second transverse direction T2. ​​More particularly, the tubular body 5 can move by translation until it is in axial support on the second annular collar 35 of the degassing tube 3. Then, the tubular body 5 can be moved to the bottom wall 84 of the frame 8 when the tool 4 also comprises the frame 8. The movement of the tubular body 5 towards the bottom wall 84 can also be carried out by translation along a third direction T3. This third direction T3 can be carried out along a radial direction (or a perpendicular plane) relative to the axis A (or the first T1 and second T2 directions). Finally, the tubular body 5 and / or the frame 8 can be extracted from the turbomachine 1.

[0113] The first T1 and second T2 transverse directions can be made along an axial direction (or a parallel plane) relative to the axis A and the axis X of the hollow shaft 2.

Claims

CLAIMS 1. Tooling (4) for mounting a degassing tube (3) in a hollow shaft (2) of an aircraft turbomachine (1), the tooling (4) comprising a tubular body (5) which has an elongated shape along an axis (A), this tubular body (5) comprising an internal longitudinal passage (50) extending over the entire longitudinal dimension of the tubular body (5) and configured to receive the degassing tube (3), characterized in that the tubular body (5) comprises a longitudinal slot (51) which extends over the entire longitudinal dimension of the tubular body (5) and which opens into the internal longitudinal passage (50), this longitudinal slot (51) being configured to allow the insertion of the degassing tube (3) into the internal longitudinal passage (50) by translation in the transverse direction of the degassing tube (3) through the longitudinal slot (51),the tubular body (5) being produced by assembling a first axial section (6) made of a first material and a second axial section (7) made of a second material different from the first material., 2. Tooling according to claim 1, in which the tubular body (5) is produced by assembly by screwing or by clipping the first axial section (6) and the second axial section (7).

3. Tooling according to claim 1 or 2, wherein the first axial section (6) comprises a first part (60) of the internal longitudinal passage (50) and a first part (61) of the longitudinal slot (51), the second axial section (7) comprises a second part (70) of the internal longitudinal passage (50) and a second part (71) of the longitudinal slot (51), a first longitudinal end (72) of the second axial section (7) being assembled in a second longitudinal end (62) of the first axial section (6) by rotation or by translation in the transverse direction of the second axial section (7) in the first part (60) of the internal longitudinal passage through the first part (61) of longitudinal slot, or vice versa, the second longitudinal end (62) of the first axial section (6) being assembled in the first longitudinal end (72) of the second axial section (7) by rotation or by translation in the transverse direction of the first axial section (6) in the second part (70) of the internal longitudinal passage through the second part (71) of longitudinal slot.

4. Tooling according to claim 3, in which the first longitudinal slot portion (61) of the first axial section (6) has an opening angle (O6i) which is less than that of the second longitudinal slot portion (71) of the second axial section (7), this opening angle (aei, a?i) being measured in a plane perpendicular to the axis (A) and the center of the opening angle of which is located on this axis (A).

5. Tooling according to any one of claims 1 to 4, in which one of the first (6) and second (7) axial sections comprises a circumferential rim (66, 76) which is engaged in a circumferential groove (68, 78) of the other axial section (6, 7) and which is retained axially in this circumferential groove (68, 78) by axial abutment of the circumferential rim (66, 76) with side walls of the circumferential groove (68, 78).

6. Tooling according to claim 5, wherein said axial section (6) which comprises the circumferential rim (66, 76) or the circumferential groove (68, 78) comprises a pair of clipping teeth (660) which are configured respectively with longitudinal edges (780) of the other axial section (7).

7. Tooling according to claim 6, dependent on claims 2, 3 and 5, or claims 2, 3, 4 and 5, in which the pair of clipping teeth (660) is located at the level of the longitudinal slot portion (61) of the first axial section (6), and the longitudinal edges (780) are those of the longitudinal slot portion (71) of the second axial section (7).

8. Tooling according to any one of the preceding claims, in which the first axial section (6) has a third free longitudinal end (64) which is beveled and comprises a generally frustoconical shape.

9. Tooling according to any one of the preceding claims, in which the second axial section (7) has a fourth free longitudinal end (74) which comprises fixing lugs (79b) and / or holes (79a), preferably guide rollers or pads.

10. Tooling according to any one of the preceding claims, in which it further comprises a support and guide frame (8) for the tubular body (5), this frame (8) having a generally elongated shape and comprising a longitudinal end capable of being fixed to a shaft or to a turbomachine element (1), the frame (8) comprising: - two side walls (81, 82) extending along the axis (A) and capable of receiving the tubular body (5) between them, and - two slide rails (810, 820) carried respectively by the side walls (81, 82) and capable of receiving guide rollers or pads carried by the tubular body (5) so as to be able to move the tubular body (5) in translation along its axis (A) relative to the frame (8).

11. Tooling according to claim 10, wherein the frame (8) further comprises crosspieces (83, 83a, 83b, 83c) for connecting the side walls (81, 82), which extend between the side walls (81, 82), two of these crosspieces (83a, 83c) being separated from each other by a distance greater than a maximum length of the tubular body (5) so as to be able to move the tubular body (5) between these crosspieces (83a, 83c), by translation in the transverse direction relative to the axis (A) of the tubular body (5).

12. Tooling according to claim 11, in which the frame (8) comprises a bottom wall (84) whose lateral ends are fixed respectively to the side walls (81, 82), this bottom wall (84) being located between the two crosspieces (83b, 83c) and being capable of receiving the tubular body (5) after its translation.

13. Tooling according to claim 12, in which the rails (810, 820) comprise windows (814, 824) for the passage of the guide rollers or pads, in order to allow the movement of the tubular body (5) between the crosspieces (83) and up to the bottom wall (84).

14. Method for mounting a degassing tube (3) in a hollow shaft (2) of an aircraft turbomachine, using a tool (4) according to any one of the preceding claims, characterized in that the method comprises the following steps: - assembly of the tool (4) by assembling the first (6) and second (7) axial sections, - installation of the tool (4) by aligning it at the level of the hollow shaft (2), - insertion of the degassing tube (3) into the internal longitudinal passage (50) by translation in the transverse direction of the degassing tube (3) through the longitudinal slot (51), - mounting the degassing tube (3) in the hollow shaft (2) by a first translation along a first transverse direction (T1) of the degassing tube (3) along the axis (A), and - removal of the tool (4) by a second translation following a second transverse direction (T2) opposite to the first translation (T1).

15. Mounting method according to the preceding claim in combination with claim 10, characterized in that it comprises a step of mounting the tubular body (5) to the frame (8) by assembling the slide rails (810, 820) to the guide rollers or pads of the tubular body (5), which is carried out between the assembly of the first (6) and second (7) axial sections and the step of inserting the degassing tube (3) into the internal longitudinal passage (50).

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