TOOLING FOR MOUNTING A DEGASING TUBE IN A HOLLOW SHAFT OF AN AIRCRAFT TURBOMACHINE, AND A METHOD USING THE TOOLING

Abstract

The present invention relates to a tool (4) for mounting a degassing tube in a hollow shaft of an aircraft turbomachine. The tool comprises a tubular body (5) having an elongated 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 receive the degassing tube, and - a longitudinal slot (51) extending over the entire longitudinal dimension of the body (5) and opening into the passage (50). This slot (51) is configured to allow the insertion of the degassing tube into the passage (50) by transverse translation of the degassing tube through the slot (51). The body (5) is made by snap-fitting a first axial section (6) of a first material and a second axial section (7) of a second material different from the first material. (See Figure 2 for abbreviations.)

Description

Title of the invention: TOOLING FOR MOUNTING A DEGASING TUBE IN A HOLLOW SHAFT OF AN AIRCRAFT TURBO MACHINE, AND METHOD USING THE TOOLING Technical field of the invention

[0001] The present invention relates to the field of aircraft turbomachinery. 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. Technical background

[0002] In a conventional manner, an aircraft turbomachine comprises, from upstream to downstream (i.e. in the direction of gas flow), 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.

[0003] The turbomachine includes a degassing tube which runs longitudinally through the turbomachine to the exhaust nozzle. The function of this degassing tube is to channel the oil-free air from the turbomachine to the exhaust nozzle.

[0004] More specifically, 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 chamber inside which a guide and centering bearing is housed. The bearing's lubricating oil mixes with air, and this oil enters and circulates inside the degassing tube to be separated from the air and recovered downstream.

[0005] The degassing tube is, for example, fixed at its downstream end to the hollow shaft and aligned with a longitudinal axis of this shaft. To facilitate the mounting of the degassing tube in the hollow shaft, tooling may be required that is simple to use and does not risk damaging the tooling, the degassing tube, the hollow shaft, and / or, more generally, the turbomachine. For example, such tooling can be designed with a limited number of bolts and screws to avoid, in particular, any risk of the tooling screws loosening during the mounting of the degassing tube in the hollow shaft.

[0006] There is therefore a need to identify a simple and reliable tooling solution for the Installation of a degassing tube in a hollow shaft of an aircraft turbomachine. Summary of the invention

[0007] The present invention proposes a simple, effective and economical solution to at least some of the aforementioned problems.

[0008] The invention provides tooling for mounting a degassing tube in a hollow shaft of an aircraft turbomachine, Tooling comprising a tubular body which has an elongated shape along an axis, this tubular body comprising: - an internal longitudinal passage extending along the entire longitudinal dimension of the tubular body and configured to receive a degassing tube, and - a longitudinal slot extending along the entire longitudinal dimension of the tubular body and opening 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 made by clipping together a first axial section in a first material and a second axial section in a second material different from the first material.

[0009] Thus, this solution makes it possible to achieve the aforementioned objective. In general, the tooling according to the invention facilitates and makes reliable the mounting of the degassing tube in the hollow shaft. To this end, the tooling proposes to manufacture 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 different materials and assembled by clipping.

[0010] The internal longitudinal passage and the longitudinal slot make it easier to insert the degassing tube into the tubular body to facilitate the guidance and centering of the degassing tube in the hollow shaft (in particular with respect to a longitudinal axis of the hollow shaft).

[0011] The clip-on assembly allows for axial locking and securing of the first and second sections together during tooling use. This also eliminates the need for bolts and screws, which, as described above, can loosen and fall into the turbomachine. Furthermore, the clip-on assembly can be reversible, allowing for the repair or replacement of one of the sections in case of wear. In addition, the first and second sections are made of different materials to allow for deformation of one section and facilitate clipping them into the other. The axial section made of the more flexible material, for example, is suitable for bearing against the hollow shaft without damaging it.

[0012] The term "clipping" means an assembly of at least one part of the sections into the other, such as by interlocking.

[0013] The tooling according to the invention may comprise one or more of the following features, taken individually or in comparison with each other:

[0014] — the tubular body has a U or C shape in cross-section;

[0015] - the first axial section comprises a first part of the longitudinal passage internal 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 by clipping into a second longitudinal end of the first axial section 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 conversely, the second longitudinal end of the first axial section being assembled by clipping into the first longitudinal end of the second axial section by translation in the transverse direction of the first axial section in the second part of the internal longitudinal passage through the second part of the longitudinal slot;

[0016] - the first longitudinal slot portion of the first axial section has an angle opening angle which is less than that of the second part of the longitudinal slot of the second axial section, this opening angle being measured in a plane perpendicular to the axis A and whose center of the opening angle is located on this axis A;

[0017] - 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 held axially in this circumferential groove by axial abutment of the circumferential rim with lateral walls of the circumferential groove;

[0018] - said axial section which includes the circumferential rim or the circumferential groove rential includes a pair of clipping teeth which are configured respectively with longitudinal edges of the other axial section;

[0019] - the pair of clipping teeth is located at the level of the longitudinal slot portion of the first axial section, and the longitudinal edges are those of the longitudinal slot part of the second axial section;

[0020] - the first axial section has a third free longitudinal end which is beveled and includes a general truncated conical shape;

[0021] - the second axial section has a fourth free longitudinal end which includes feet and / or fixing holes, preferably for rollers or guide pads;

[0022] - the tooling further comprises a support and guide frame for the tubular body, This frame has a generally elongated shape and includes a longitudinal end. The frame, suitable for attachment to a shaft or turbomachine element, comprises: - two lateral walls extending along axis A and suitable for receiving the tubular body between them, and - two slide rails supported respectively by the side walls and suitable for 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 vis-à-vis the frame;

[0023] - the longitudinal end of the frame includes a fixing ring suitable for being traversed by the tubular body;

[0024] - the frame further includes connecting cross members of the side walls, which extend between the side walls, two of these crossbeams 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 crossbeams, by translation in the transverse direction with respect to the axis A of the tubular body;

[0025] - the frame comprises a back wall, the lateral ends of which are fixed res relative to the side walls, this bottom wall being located between the two crossbeams and being able to collect the tubular body after its translation;

[0026] — the bottom wall has a general U or C shape;

[0027] - the rails include openings for the passage of the guide rollers or pads, in order to to allow the movement of the tubular body between the crossbeams and up to the bottom wall;

[0028] — the frame further includes two side handles located respectively on the two side walls;

[0029] — the first axial section includes a circumferential notch located between its circumferential rim and its first circumferential groove.

[0030] The present invention further 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.

[0031] The process comprises the following steps: - Tooling assembly by clipping the first and second axial sections together, - Installation of the tooling, 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, - mounting the degassing tube in the hollow shaft by a first translation along a first transverse direction of the degassing tube along axis A, and - removal of the tooling by a second translation along a second transverse direction opposite to the first translation.

[0032] The method may include a step of mounting the tubular body to the frame by assembly of the slide rails to the rollers or guide pads of the tubular body, which is carried out between the clip-on assembly of the first and second axial sections and the step of inserting the degassing tube into the internal longitudinal passage. Brief description of the figures

[0033] The invention will be better understood and other details, features and advantages of the invention will become more apparent upon reading the following description, given by way of non-limiting example and with reference to the accompanying drawings in which:

[0034] [Fig. 1] is a partial schematic cross-sectional view of an aircraft turbomachine comprising a degassing tube mounted in a hollow shaft,

[0035] [Fig.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 [Fig.1],

[0036] [Fig.3] is a schematic top half view of a first axial section of the tooling of [Fig.2],

[0037] [Fig.4] is a partial schematic and perspective view of the tooling of [Fig.2],

[0038] [Fig.5] is another partial schematic and perspective view of the tooling of [Fig.2],

[0039] [Fig.6] is a partial schematic top view of the tooling of [Fig.2] or [Fig.4],

[0040] [Fig.7] is a partial schematic and profile view of a first example of assembly by clipping the first and second axial sections of the tooling of [Fig.2],

[0041] [Fig.8] is a partial schematic and profile view of a second example of assembly by clipping the first and second axial sections of the tooling of [Fig.2],

[0042] [Fig.9] 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 [Fig.1],

[0043] Fig. 10 is a partial schematic perspective view of the degassing tube inserted into the tooling of [Fig.2],

[0044] [Fig. 1 1] is a partial schematic perspective view of the degassing tube inserted into the tooling of [Fig.9],

[0045] [Fig. 12] is a partial schematic and perspective view of mounting the degassing tube in the hollow shaft using the tooling of [Fig. 9],

[0046] [Fig. 13] is a partial schematic and perspective view of a removal of the tooling from [Fig. 9],

[0047] [Fig. 14] is a partial schematic and perspective view of the continuation of the removal of the tooling from [Fig. 13].

[0048] Elements having the same functions in the different implementations have the same references in the figures. Detailed description of the invention

[0049] Generally, in the following description, the terms "longitudinal" and "axial" refer to the orientation of structural elements extending along a longitudinal axis (such as that of an aircraft turbomachine). This axis can be considered the same as the axis of rotation of a turbomachine rotor. The term "radial" refers to the 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 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 [Fig.1], an aircraft turbomachine 1 comprises, without limitation, from upstream to downstream, a fan (not shown in [Fig.1]), a low pressure compressor 1a, a high pressure compressor 1b, a combustion chamber 1, a high pressure turbine 1d and a low pressure turbine 1 and an exhaust gas nozzle (not shown in [Fig.1]).

[0051] The high-pressure turbine le can drive the high-pressure compressor 1b via a high-pressure shaft (also called a turbine shaft and referred to in this application as a hollow shaft 2), and these elements form a high-pressure body. The low-pressure turbine Id can drive the low-pressure compressor la via a low-pressure shaft coaxially with the high-pressure shaft, and these elements form a low-pressure body.

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

[0053] The turbomachine 1 may include a degassing tube 3. The degassing tube 3 may run longitudinally through the turbomachine 1 to the exhaust gas nozzle.

[0054] More specifically, the degassing tube 3 can be mounted coaxially inside the hollow shaft 2. The degassing tube 3 can be hollow and cylindrical. The degassing tube 3 can 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. The upstream portion 31 can 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 outlet located for example in the exhaust nozzle.

[0055] The downstream portion 33 may include at least one annular flange 34, 35. More specifically, the degassing tube 3 may include first 34 and second 35 annular flanges extending radially outwards, particularly at the end of the downstream portion 33. These first 34 and second 35 annular flanges allow the degassing tube 3 to be held in position within the hollow shaft 2 by means of a tool 4 as described below. For example, a seal may be positioned around the first flange 34 to ensure the centering of the degassing tube in the hollow shaft without damaging it. The second flange 35 also allows the centering of the degassing tube and may also ensure its axial locking within the turbine.

[0056] As described above, this degassing tube 3 serves to channel the oil-free air from the turbomachine 1 to the exhaust nozzle. The degassing tube 3 can be mounted in the hollow shaft 2 using specific tooling 4.

[0057] The present application will now describe the different possible configurations of the tooling 4, in particular with reference to figures 3 to 9.

[0058] The tooling 4 comprises a tubular body 5 which has an elongated shape along an axis A. This axis A can be substantially in continuity with the longitudinal axis X of the hollow shaft 2 when the tooling 4 is installed in the turbomachine (in particular at the level of the hollow shaft 2) to mount the degassing tube 3.

[0059] The tubular body 5 can have a U or C shape in cross-section.

[0060] The tubular body 5 comprises: - 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.

[0061] The tubular body 5 is formed by snap-fitting 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 at least partially snap-fitted together.

[0062] In the example of Figures 2 to 9, the first axial section 6 may comprise a first part 60 of the internal longitudinal passage 50, called the first part of passage 60, and a first portion 61 of the longitudinal slot 51, called the first portion of the slot 61. The second axial section 7 may include a second portion 70 of the internal longitudinal passage 50, called the second portion of the passage 70, and a second portion 71 of the longitudinal slot 51, called the second portion of the slot 71. The first 60 and second 70 portions of the passage can form the internal longitudinal passage 50 of the tubular body. In general, the first 61 and second 71 portions of the slot can form the longitudinal slot 51 of the tubular body. When the first 6 and second 7 axial sections are mounted together, the first portions of the passage 60 and slot 61 can be aligned along axis A with, respectively, the second portions of the passage 70 and slot 71.

[0063] Advantageously, the first slot portion 61 may have a first opening angle a6i and the second slot portion 71 may have a second opening angle a7i. These opening angles a6i and a7i may be measured in a plane perpendicular to axis A and whose center of the opening angle is located on this axis A. By way of example, the first opening angle a6i may be between 70° and 180°. The second opening angle a7i may be between 100° and 190°, preferably approximately 180°.

[0064] In the example of the figures, the first opening angle a6i can be less than the second opening angle a6i ([Fig.5]).

[0065] The first material for making the first axial section 6 can be a plastic material, such as polyethylene (HDPE) or resin. Preferably, the first material can 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) against which the first axial section 6 bears during the use of the tooling 4. In addition, clip-on assembly is facilitated.

[0066] The first axial section 6 may include 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.

[0067] The first axial section 6 may include a third longitudinal end 64. This third longitudinal end 64 may be free. The third longitudinal end 64 may be beveled and may have a generally frustoconical shape.

[0068] With reference to [Fig. 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 prevents damage to the surface of the turbomachine 1 on which the The first axial section 6 comes into contact with the support when using tooling 4.

[0069] Advantageously, the first axial section 6 may include 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.

[0070] 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 lateral walls of the second circumferential groove 78.

[0071] The first circumferential rim 66 or the first circumferential groove 68 may include a first pair of clipping teeth 660. This first pair of teeth 660 may be configured to clip with the 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.

[0072] In the example of figures 2 to 6, the first pair of teeth 660 can be located at the level of the first circumferential rim 66.

[0073] The first circumferential rim 66 may have a first length L66 measured along the axis A. The first circumferential groove 68 may have a second length L68 also measured along the axis A. The first length L66 may be less than the second length L68 ([Fig.6]).

[0074] The first axial section 66 may include 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 allows for local flexibility or deformation of the first axial section 66 which facilitates assembly by clipping.

[0075] The second material for the second axial section 7 can be made of a metallic material, such as aluminum. This provides sufficient rigidity to the tubular body 5 to support the degassing tube 3.

[0076] The second axial section 7 may include 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.

[0077] The second axial section 7 may include a fourth longitudinal end 74. This fourth longitudinal end 74 may be free. The fourth longitudinal end 74 may include fastening members 79, for example, to a frame 8 as described below. These fastening members 79 may be fastening tabs 79b ([Fig.9]) and / or fixing holes 79a ([Fig.2]). The fixing tabs 79b can be rollers or guide pads.

[0078] As shown in the figures, the second axial section 7 can extend between the first longitudinal end 72 and the fourth longitudinal end 74. The second passage part 70 and the second slot part 71 can extend between the first 72 and fourth 74 longitudinal ends.

[0079] Advantageously, the second axial section 7 can include a second circumferential rim 76 and a second circumferential groove 78. This second circumferential groove 78 can be located between the second circumferential rim 76 and the fourth longitudinal end 74.

[0080] 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 lateral walls of the first circumferential groove 68.

[0081] The second circumferential rim 76 or the second circumferential groove 78 may include 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.

[0082] The second circumferential rim 76 may have a third length L76 measured along axis A. The second circumferential groove 68 may have a fourth length L68 also measured along axis A.

[0083] With reference to [Fig. 6], the first length L66 may be less than or equal to the fourth length L78. The difference in length between the first L66 and fourth L78 lengths allows for axial play between the first circumferential rim 66 and the second circumferential groove 78, notably to facilitate assembly by clipping. The third length L76 may be substantially identical to the second length L68.

[0084] With reference to [Fig.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 part of passage 70 through the second part of slot 71.

[0085] With reference to [Fig. 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 into the first part of passage 60 through the first part of slot 61.

[0086] The transverse direction T of the assembly by clipping the first 6 and second 7 axial sections together can be carried out along a radial direction (or a plane perpendicular) with respect to the axis A.

[0087] The tooling 4 may further include a support and guide frame 8 for the tubular body 5, referred to below by the abbreviation frame 8.

[0088] With reference to [Fig.9], the frame 8 may have a generally elongated shape and may include a fifth longitudinal end 80 suitable for being fixed to a shaft or to a turbomachine element 1.

[0089] The fifth longitudinal end 80 of the frame 5 may include a fixing ring 800 suitable for the tubular body 5 to pass through. By "ring", it may mean an annular frame that can be fixed on the shaft or turbomachine element 1 and having an opening through which the tubular body 5 (optionally the degassing tube 3) can pass and slide towards the hollow shaft 2.

[0090] Frame 8 may include: - two lateral walls 81, 82 (such as the first 81 and second 82 lateral walls) extending along the axis A and adapted to receive between them the tubular body 5, and - two slide rails 810, 820 (such as first 810 and second 820 rails) carried respectively by the side walls 81, 82 and suitable for receiving fixing tabs 79b (such as rollers or guide 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 vis-à-vis the frame 8.

[0091] The frame 8 may further include cross members 83 for connecting the side walls 81, 82. These cross members 83 may extend between the side walls 81, 82. In the example of [Fig. 9], the frame 8 may include first 83a, second 83b and third 83c cross members 83. Two of these cross members 83 (such as the first 83a and third 83c cross members) 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 cross members 83a, 83c, by translation in the transverse direction with respect to the axis A of the tubular body 5.

[0092] The frame 8 may further include two side handles 812, 822 (such as first 812 and second 822 side handles) located respectively on the two side walls 81, 82. These side handles 812, 822 make it easier to grip and handle the frame 8.

[0093] The frame 8 may include a bottom wall 84. This bottom wall 84 may have a general U- or C-shaped form, the lateral ends of which are fixed respectively to the side walls 81, 82. The bottom wall 84 may be located between the two crossbeams, such as the second 83b and third 83c crossbeams. The bottom wall 84 may be suitable for receiving the tubular body 5 after its translation, for example for its removal at the end of assembly.

[0094] The rails 810, 820 may include windows 814, 824 for the passage of the fixing lugs 79b (such as the rollers or guide pads), in order to allow the movement of the tubular body 5 between the sleepers 83 (such as the second 83b and third 83c sleepers) and up to the bottom wall 84.

[0095] 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 10 to 14.

[0096] In general, the process may include the following steps: - assembly of tooling 4 by clipping together the first 6 and second 7 axial sections, - installation of tooling 4 by aligning it with the hollow shaft 2 (particularly along the X axis), - 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 Tl of the degassing tube 3 along the axis A, and - Removal of tooling 4 (in particular from the degassing tube 3 mounted in the hollow shaft 2) by a second translation along a second transverse direction T2 opposite to the first translation TL

[0097] As described above, for example with reference to Figures 7 and 8, the tooling assembly step 4 may include: - the assembly by clipping the second longitudinal end 62 of the first axial section 6 into the first longitudinal end 72 of the second axial section 7 by translation in the transverse direction of the first axial section 6 in the second part of the passage 70 through the second part of the slot 71, or - the assembly by clipping the first longitudinal end 72 into the second longitudinal end 62 of the first axial section 6 by translation in the transverse direction of the second axial section 7 in the first part of passage 60 through the first part of slot 61.

[0098] The steps of inserting the degassing tube 3 into the internal longitudinal passage 50 and of mounting the degassing tube 3 into the hollow shaft 2 can be reversed.

[0099] Fig. 10 illustrates an example of insertion of the degassing tube 3 into the internal longitudinal passage 50 of the tubular body 5.

[0100] With reference to [Fig. 11], the process may also include a step of assembly of the tubular body 5 to the frame 8 by assembling the slide rails 810, 820 to the fixing tabs 79b (such as rollers or guide pads) of the tubular body 5. This step of assembling the tubular body 5 to the frame 8 is carried out between the assembly 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.

[0101] Fig. 12 illustrates in a non-limiting way an example of mounting the degassing tube 3 in the hollow shaft 2 by the first translation along the first direction Tl.

[0102] The step of mounting the degassing tube 3 in the hollow shaft 2 can be carried out until at least one of the annular flanges 34, 35 of the degassing tube 3 is axially supported on the tubular body 5. For example, the first annular flange 34 can move by translation until it is axially supported 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.

[0103] Figures 13 and 14 illustrate, by way of non-limiting example, a removal of the tooling 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 specifically, the tubular body 5 can move by translation until it is axially supported on the second annular flange 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 tooling 4 also includes the frame 8. The movement of the tubular body 5 towards the bottom wall 84 can also be achieved by translation along a third direction T3. This third direction T3 can be radial (or perpendicular) 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.

[0104] The first T1 and second T2 transverse directions can be made along an axial direction (or a parallel plane) with respect to the axis A and the axis X of the hollow shaft 2.

Claims

Demands

1. Tooling (4) for mounting a vent 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 vent 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 vent tube (3) into the internal longitudinal passage (50) by translation in the transverse direction of the vent tube (3) through the longitudinal slot (51),the tubular body (5) being made by clipping together 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, 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 (50), 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 by clipping into a second longitudinal end (62) of the first axial section (6) 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 the longitudinal slot, or vice versa,the second longitudinal end (62) of the first axial section (6) being assembled by clipping into the first longitudinal end (72) of the second axial section (7) 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 the longitudinal slot.

3. Tooling according to claim 2, wherein the first longitudinal slotted portion (61) of the first axial section (6) has an opening angle (a6i) which is less than that of the second part (71) of longitudinal slot of the second axial section (7), this opening angle (a6i, a7i) being measured in a plane perpendicular to the axis (A) and whose center of the opening angle is located on this axis (A).

4. Tooling according to any one of claims 1 to 3, wherein 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 axially retained in this circumferential groove (68, 78) by axial abutment of the circumferential rim (66, 76) with lateral walls of the circumferential groove (68, 78).

5. Tooling according to claim 4, wherein said axial section (6) which includes the circumferential rim (66, 76) or the circumferential groove (68, 78) includes a pair of clipping teeth (660) which are configured respectively with longitudinal edges (780) of the other axial section (7).

6. Tooling according to claim 5, depending on claims 2 and 4, or claims 2, 3 and 4, wherein the pair of clipping teeth (660) is located at 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).

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

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

9. Tooling according to any one of the preceding claims, wherein it further comprises a support and guide frame (8) for the tubular body (5), said frame (8) having a generally elongated shape and having a longitudinal end adapted to be fixed to a shaft or a turbomachine element (1), the frame (8) comprising: - two lateral walls (81, 82) extending along the axis (A) and adapted to receive the tubular body (5) between them, and - two slide rails (810, 820) carried respectively by the lateral walls (81, 82) and adapted to receive guide rollers or pads supported 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, wherein the longitudinal end of the frame (8) comprises a fastening band (80) suitable for being passed through by the tubular body (5).

11. Tooling according to claim 9 or 10, wherein the frame (8) further comprises cross members (83, 83a, 83b, 83c) for connecting the side walls (81, 82), which extend between the side walls (81, 82), two of these cross members (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 cross members (83a, 83c), by translation in the transverse direction with respect to the axis (A) of the tubular body (5).

12. Tooling according to claim 11, wherein the frame (8) comprises a bottom wall (84) whose lateral ends are fixed respectively to the lateral walls (81, 82), this bottom wall (84) being located between the two cross members (83b, 83c) and being able to collect the tubular body (5) after its translation.

13. Tooling according to claim 12, wherein the rails (810, 820) include 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 sleepers (83) and up to the bottom wall (84).

14. A method for mounting a vent tube (3) in a hollow shaft (2) of an aircraft turbomachine, using tooling (4) according to any one of the preceding claims, characterized in that the method comprises the following steps: - mounting the tooling (4) by snapping the first (6) and second (7) axial sections together, - installing the tooling (4) by aligning it with the hollow shaft (2), - inserting the vent tube (3) into the internal longitudinal passage (50) by translating the vent tube (3) in the transverse direction through the longitudinal slot (51), - mounting the vent tube (3) in the hollow shaft (2) by a first translation along a first transverse direction (T1) of the vent tube (3) along the axis (A), and - removing the tooling (4) by a second translation along a second transverse direction (T2) opposite to the first translation

15. (T1). Assembly method according to the preceding claim in combination with claim 9, 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 clip-on 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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