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) extending over the entire longitudinal dimension of the body (5) and opening into the passage (50), wherein this slot (51) is configured to allow the degassing tube to be inserted into the passage (50) by transationally moving the degassing tube through the slot (51) in the transverse direction, wherein the body (5) comprises a first axial segment (6) and a second axial segment (7) having a different shape from the first axial segment, and wherein the first and second axial segments are formed as a single piece.

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 comprising a first axial section and a second axial section of a shape different from that of the first axial section, the first and second axial sections being made in a single piece.

[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 invention proposes to integrate a major part of the tooling in a single part, which makes it possible to reduce the number of parts and simplify the assembly of the tooling and consequently the assembly of the degassing tube. Indeed, the tubular body of the tooling is produced by integrating, on the one hand, the internal longitudinal passage and the longitudinal slot, and on the other hand, the first and second sections produced in a single part.

[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] The production of the first and second axial sections from a single piece makes it possible to make the tubular body robust, with a reduced mass and difficult to damage when using the tooling. This also avoids the use of bolt and screw type fasteners which, as described above, can unscrew and fall into the turbomachine.

[0019] By "made from a single piece" is meant the first and second axial sections formed in a single piece (or otherwise said to be made from one material) in particular without assembly, joining, bonding, welding or any other method of connecting these axial sections.

[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; - 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;

[0022] - 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;

[0023] - the first axial section has a third free longitudinal end which is beveled and comprises a generally truncated cone shape;

[0024] - the second axial section has a fourth free longitudinal end which comprises fixing lugs and / or holes, preferably guide rollers or pads;

[0025] - the first and second axial sections are made of a metallic material, such as aluminum;

[0026] - the tubular body comprises a coating covering either entirely the first and second axial sections or at least part of the first axial section;

[0027] - the coating is made of a material different from the metallic material;

[0028] -- the coating material has a lower hardness than the metallic material;

[0029] -- the coating is made of plastic material, such as polyethylene (HDPE) or resin;

[0030] - 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:

[0031] - two side walls extending along the axis A and capable of receiving the tubular body between them, and - 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 passed through by the tubular body;

[0033] - 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;

[0034] - 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;

[0035] -- the back wall has a general U or C shape;

[0036] - 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;

[0037] -- the frame also includes two side handles located respectively on the two side walls.

[0038] 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.

[0039] The method includes the following steps:

[0040] - installation of the tooling by aligning it with the hollow shaft,

[0041] - insertion of the degassing tube into the internal longitudinal passage by translation in the transverse direction of the degassing tube through the longitudinal slot, - mounting of the degassing tube in the hollow shaft by a first translation in a first transverse direction of the degassing tube along the axis A, and

[0042] - removal of the tool by a second translation following a second transverse direction opposite to the first translation.

[0043] 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 clipping assembly of the first and second axial sections and the step of inserting the degassing tube into the internal longitudinal passage.

[0044] The method may comprise a step of producing the first and second axial sections in a single piece. This production step may be carried out before the step of installing the tooling at the hollow shaft. The production step may comprise forming the first and second axial sections in a single piece, in particular in a metallic material, by molding, extrusion or additive manufacturing. This production step may comprise depositing a coating so as to cover either the first and second axial sections entirely, or at least partially the first axial section.

[0045] Brief description of the figures

[0046] 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 one embodiment of the invention for mounting the degassing tube in the hollow shaft of Figure 1, Figure 3 schematically represents the materials composing a tubular body of the tool of Figure 2, Figure 4 is a schematic and perspective view of a tool according to another embodiment of the invention for mounting the degassing tube in the hollow shaft of Figure 1, Figure 5 is another partial schematic and perspective view of the tool of Figure 4;Figure 6 is a partial schematic and perspective view of the degassing tube inserted into the tooling of Figure 2, Figure 7 is a partial schematic and perspective view of the degassing tube inserted into the tooling of Figure 4 or 5, Figure 8 is a partial schematic and perspective view of a mounting of the degassing tube in the hollow shaft by the tooling of Figure 4 or 5, Figure 9 is a partial schematic and perspective view of a removal of the tooling of Figure 4 or 5, Figure 10 is a partial schematic and perspective view of the continuation of the removal of the tooling of Figure 9.;

[0047] Elements having the same functions in different implementations have the same references in the figures.

[0048] Detailed description of the invention

[0049] 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.

[0050] 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).

[0051] 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.

[0052] The hollow shaft 2 extends along a longitudinal X which can correspond substantially to a general axis of the turbomachine 1.

[0053] 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.

[0054] 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. 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 can 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 can also ensure its axial locking in the turbomachine.

[0055] 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.

[0056] This application will now describe the different possible configurations of the tool 4, in particular with reference to figures 2 to 5.

[0057] 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.

[0058] The tubular body 5 may have a U or C shape in cross section. The tubular body 5 comprises:

[0059] - 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

[0060] - 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.

[0061] The tubular body 5 comprises a first axial section 6 and a second axial section 7.

[0062] The second axial section 7 has a different shape from that of the first axial section 6.

[0063] The first 6 and second 7 axial sections are made from a single piece (in other words, in a monobloc or integral way).

[0064] The first 6 and second 7 axial sections may be made of a metallic material 52, such as aluminum. This provides sufficient rigidity to the tubular body 5 to support the degassing tube 3. The tubular body 5 may include a coating 54.

[0065] The coating 54 may be made of a material different from the metallic material 52.

[0066] The coating 54 may have a lower hardness than the metallic material 52.

[0067] For example, the coating 54 may be a plastic material, such as polyethylene (HDPE) or resin.

[0068] The coating 54 may completely cover the first 6 and second 7 axial sections. Alternatively, the coating 54 may cover at least a portion of the first 6 and second 7 axial sections. Advantageously, the coating 54 may cover at least a portion of the first axial section 6. This makes it possible in particular not to damage 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.

[0069] Figure 3 very schematically illustrates the tubular body 5 comprising the coating 54 which covers the metallic material 52 for example at the level of the first 6 and second 7 axial sections.

[0070] In the example of Figures 2 to 5, 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. The first passage 60 and slot 61 portions may be aligned along the axis A with, respectively, the second passage 70 and slot 71 portions.

[0071] 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°.

[0072] In the example of the figures, the first opening angle aei can be less than the second opening angle a?i (figure 5).

[0073] The first axial section 6 may comprise a second longitudinal end 62. This second longitudinal end 62 may be connected, in particular directly and in a single piece, to a first longitudinal end 72 of the second axial section 7.

[0074] 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 frustoconical shape.

[0075] The first axial section 6 may extend between the second longitudinal end 62 and the third longitudinal end 64. The first passage portion 60 may be located at the third longitudinal end 64.

[0076] The second axial section 7 may comprise the first longitudinal end 72. This first longitudinal end 72 may be connected, in particular directly and in a single piece, to the second longitudinal end 62 of the first axial section 6.

[0077] 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 5) and / or fixing orifices 79a (figure 2). The fixing lugs 79b may be guide rollers or pads.

[0078] 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.

[0079] 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 (figures 4 and 5).

[0080] 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.

[0081] 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.

[0082] Frame 8 may include:

[0083] - 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

[0084] - 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.

[0085] 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. 9, 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.

[0086] 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.

[0087] 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.

[0088] The present application will now describe a method of mounting the degassing tube 3 in the hollow shaft 2, for example with reference to figures 6 to 10.

[0089] Generally, the process may include the following steps:

[0090] - optionally production of the first 6 and second 7 axial sections in a single piece,

[0091] - installation of tool 4 by aligning it with the hollow shaft 2 (in particular along the X axis),

[0092] - 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,

[0093] - 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

[0094] - 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.

[0095] The step of producing the first 6 and second 7 axial sections can be carried out upstream of the installation of the tooling 4 at the level of the hollow shaft 2. This step of producing the first 6 and second 7 axial sections can be carried out by molding, extrusion or additive manufacturing.

[0096] The tubular body 5 can be produced by forming the first 6 and second 7 axial sections in a single piece, in particular in the metallic material 52, then by depositing the coating 54 so as to cover either the first 6 and second 7 axial sections entirely, or at least in part the first axial section 6.

[0097] The steps of inserting the degassing tube 3 into the internal longitudinal passage 50 and mounting the degassing tube 3 in the hollow shaft 2 can be reversed.

[0098] Figure 6 illustrates an example of insertion of the degassing tube 3 into the internal longitudinal passage 50 of the tubular body 5.

[0099] With reference to Figure 7, 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 may be carried out before the step of inserting the degassing tube 3 into the internal longitudinal passage 50.

[0100] Figure 8 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.

[0101] 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.

[0102] Figures 9 and 10 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.

[0103] 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), and - 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) comprising a first axial section (6) and a second axial section (7) of a shape different from that of the first axial section (6), the first (6) and second (7) axial sections being made in a single piece.

2. Tooling according to claim 1, 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); and 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).

3. Tooling according to claim 2, 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).

4. 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.

5. 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.

6. Tooling according to any one of the preceding claims, in which the first (6) and second (7) axial sections are made of a metallic material (52), such as aluminum.

7. Tooling according to any one of the preceding claims, in which the tubular body (5) comprises a coating (54) covering either entirely the first (6) and second (7) axial sections or at least part of the first axial section (6).

8. Tooling according to claims 6 and 7, in which the coating (54) is made of a material different from the metallic material (52).

9. 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) with respect to the frame (8).

10. Tooling according to claim 9, in which the longitudinal end of the frame (8) comprises a fixing strap (80) capable of being passed through by the tubular body (5).

11. Tooling according to claim 9 or 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: - 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 9, wherein the method 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 clipping 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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