FR3112607A1 - TEST BENCH AND ITS IMPLEMENTATION PROCESS - Google Patents

Abstract

The invention relates to a test bench (1) for stressing in torsion a part (100) of an aircraft turbomachine, comprising: - a part (100) to be tested having a vertical elongation axis (Z), - a system (2) for applying a rotational torque to the part (100) around said axis (Z), - at least one guide element (3), and - a torque take-up system (4) characterized in that it comprises: - a lifting beam (20), - a gantry (30) comprising two vertical uprights (31a, 31b) and at least one horizontal beam (32a, 32b), - connecting jacks (40a, 40b) of the lifter (20) to the uprights (31a, 31b). Figure for the abstract: Figure 2

Description

TEST BENCH AND ITS IMPLEMENTATION PROCESS

Technical field of the invention

The present invention relates to a test bench and its method of implementation.

Technical background

When carrying out partial tests with torsion stress on turbojet engine parts, it is often necessary to be able to stress the latter in pure torsion, that is to say a stress with only a moment along the axis of rotation of the the room. For this, it is necessary to minimize the parasitic forces transmitted to the part such as the radial and axial forces.

A test bench for stressing a part in torsion includes an assembly which makes it possible to hold the part to be tested, to provide a torque and a torque recovery as well as a device for measuring the torque. The test bench also includes a structure supporting the assembly and which generally consists of a plate at ground level, vertical uprights and a horizontal gantry at height. The assembly is horizontal and rests on at least some elements of this structure at the level of support points which must support the weight of the assembly parts and involves the use of bearings.

However, the elements of the structure can be of different materials and geometry, resulting in variations in the stiffness of the elements supporting the assembly. During the tests, the elements will thus undergo different bending, traction and compression, thus making the operation of the test bench asymmetrical.

In addition, even in a configuration in which two elements of the structure would be identical, the positioning of the support points of the assembly at different locations of the elements, that is to say at locations of the elements having different stiffnesses, can also lead to the same testbed asymmetry issue.

This asymmetry causes (or at least promotes) the generation of parasitic forces in the assembly and also makes it difficult to control these parasitic forces.

The parasitic forces will then disturb the measurement of the torque object of the tests which can in particular be overestimated, resulting in particular in a minimization of the life of the part obtained during the test.

In addition, in order to reproduce the stresses present on the engine, it is necessary to carry out an assembly which requires a large number of parts, including engine parts, new parts or even parts taken from old assemblies, which require be appraised or remanufactured. It is then sometimes necessary to immobilize engine parts initially intended for the series, see the complete module, which may require the development and manufacture of a frame for the transport of these engine parts and which also requires a complex assembly before carrying out the essay.

The assembly can therefore reach large volumes that can go as far as occupying the entire test bench, or even requiring the design and manufacture of specific frames, which also lengthens the implementation time of the assembly and increases the costs and delays.

For all these reasons, the cost, logistics and assembly implementation times can be very high.

Furthermore, with such a horizontal mounting, the angular deflection during the application of the torsion torque on the part to be tested becomes significant, generating cylinder strokes close to the limit values.

The gantry can also present parasitic displacements when a torque is applied to the part. These parasitic movements pollute the test results and there is a risk of premature failure of test bench elements in the case of fatigue testing.

The object of the present invention is in particular to solve all or part of the aforementioned problems.

The invention proposes for this purpose a test bench for stressing in torsion an aircraft turbomachine part, comprising:

- a part to be tested with a generally elongated shape and having a vertical axis of elongation,

- a system for applying a torque to the part around said axis,

- at least one element for guiding the part in rotation about said axis, and

- a torque recovery system applied to the part around said axis,

According to the invention, said torque take-up system comprises:

- a first connecting element from a lower end of the part to a horizontal plate, said connecting element being integral in rotation with the part and being rigidly fixed to the plate,

According to the invention, said torque application system comprises:

- a lifter connected to an upper end of the part,

- a frame comprising two vertical uprights and at least one horizontal beam, the uprights extending between the plate and the beam and being arranged on each side of the room, and

- connecting cylinders of the lifter to the uprights of the gantry, each cylinder having a first end articulated on the lifter and a second opposite end articulated on one of the uprights, the cylinders being articulated at first diametrically opposite points on the lifter, and extending in a first horizontal plane passing through said rudder.

The invention thus provides for a set of two cylinders pulling on a spreader bar of a vertical assembly to generate the torsion torque on the part. The vertical arrangement of the part coupled with the extension of the cylinders in the same horizontal plane makes it possible to eliminate the parasitic radial forces linked to the weight of the parts and also avoids having to resort to bearings with bearings supporting the weight of the piece. In addition, the operation is thus symmetrical because the cylinders are positioned in the same plane, in the same way on identical uprights. The uprights thus deform by the same amount, avoiding having to know the stiffness of the uprights.

The test bench, according to the invention, may include one or more of the characteristics below, taken separately with each other or in combination with each other:

- the part is a shaft of an aircraft turbine engine;

- the part is tubular and said first connecting element comprises:

- a cylindrical body engaged in the lower end of the part and secured to it by a nut screwed onto the body and bearing axially on the part, and

- a fixing base on the hob;

- the lifter is connected to the upper end of the part by means of a second connecting element which comprises a tubular body in which the upper end of the part is engaged and which is secured thereto by a nut screwed onto the part and resting axially on the body;

- it further comprises a device for measuring a torque applied to the part around said axis;

- the measuring device is interposed between the spreader bar and the second connecting element;

- Said at least one guide element is carried by said beam;

- said at least one guide element comprises a bearing for guiding a vertical tail of the spreader bar;

- the uprights are walls that are arranged opposite each other;

- the uprights and the beams are stiffened by brackets extending between the uprights and the plate, and/or between the uprights and the beam;

- the brackets for connecting the uprights to the beam each comprise first cylindrical holes for passing screws for fixing the bracket to one of the uprights, and second holes for passing screws for fixing the bracket to the beam , these second holes having a cylindrical or elongated shape along an axis of elongation of the beam;

- a first of the brackets for connecting an upright to the beam comprises second cylindrical holes, and a second of the brackets for connecting the other upright to the beam comprises second holes of elongated or oblong shape, the test bench further comprising at least one immobilization block located on the side of this second bracket, which is fixed to the beam by first screws parallel to the upright and which is fixed to the upright by second screws parallel to the beam and which bear respectively on the second bracket and on the upright.

The present invention also relates to a method for implementing a torsional force of an aircraft turbomachine part, such as an aircraft turbomachine shaft, by means of a test bench as described previously.

Brief description of figures

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 very schematic perspective view of part of a test bench according to the invention;

Figure 2 is a schematic perspective view of a test bench according to the invention;

FIG. 3 is a schematic view in vertical section of a torque application system, of a part to be tested and of a torque take-up system of a test bench according to the invention;

Figure 4 is a schematic view in vertical section detailing an upper part of Figure 3;

Figure 5 is a simplified schematic side view of the system of jacks according to the invention;

FIG. 6 is a simplified schematic top view of the jack system according to the invention;

Figure 7 is a schematic perspective view of an upright of the test bench according to the invention;

Figure 8 is a schematic side view of connecting brackets and an immobilization block installed on uprights and beams according to the invention;

Figure 9 is a schematic perspective view of a connecting bracket according to the invention;

FIG. 10 is a schematic side view of a connecting bracket installed on an upright with an immobilization block according to the invention; And

FIG. 11 is a schematic side view of a connecting bracket installed on an upright with an immobilization block according to the invention.

Detailed description of the invention

FIG. 1 represents part of a test bench 1 making it possible to stress a part 100 in torsion. The test bench 1 thus comprises the part 100 to be tested which has a generally elongated shape and a vertical axis of elongation Z. The part 100 is for example an aircraft turbomachine shaft. The part 100 is for example tubular and comprises an upper end 102 and a lower end 101. The adjectives lower and upper are used in reference to the test bench 1 and to the ground so that the lower part of an element is closer ground level than the upper part of the same element along the Z axis.

Workbench 1 also includes a system 2 for applying 5 rotational torque to 100 workpiece around the Z axis.

The test bench 1 further comprises at least one guide element 3 in rotation of the part 100 around the axis Z.

In addition, the test bench 1 also includes a 4 torque pick-up system 5 applied to the part 100 around the Z axis.

Torque Applying System 2 and Torque Taking Up System 4 are at an opposite end of part 100 on the Z axis.

As shown in Figure 2, the torque application system 2 5 comprises a gantry 30. The gantry 30 comprises for example two vertical uprights 31a, 31b called first 31a and second 31b amount. The uprights 31a, 31b are arranged on each side of the part 100. The uprights 31a, 31b are in particular walls 31a, 31b, which are arranged opposite one another. The gantry 30 also includes at least one horizontal beam 32a, 32b. The test bench 1 here comprises two beams 32a, 32b, called first 32a and second 32b beam. The vertical uprights 31a, 31b extend between a plate 34 of the test bench 1 and the beams 32a, 32b respectively. The beams 32a, 32b thus each extend from the first upright 31a to the second upright 31b. The hob 34 extends horizontally and can be placed on the ground or any suitable support.

As shown in Figure 3, the torque recovery system 4 comprises a first connecting element 10, in particular an adapter piece corresponding to a false turbine shaft. This first connecting element 10 is located between the lower end 101 of part 100 and plate 34.

The first element 10 comprises a fixing base 13 which is fixed to the plate 34. The base 13 is bolted in particular to a mounting plate 14, for example by means of screws 13a. The recess plate 14 is for example bolted to the plate 34 by means of screws 14a.

The first connecting element 10 also comprises a cylindrical body 11. This cylindrical body 11 is engaged in the lower tubular end 101 of the part 100. It is secured to the part 100 by a nut 12 which is screwed onto the body 11, at an upper end of the body 11. The nut 12 has a screw pitch along the Z axis and comprises a horizontal lower surface 12a.

Unless otherwise specified, the adjectives interior and exterior are used with reference to a radial direction such that the interior (i.e. radially interior) part of an element is closer to the Z axis than the exterior (i.e. radially exterior) part of the element. same element.

The nut 12, in particular a turbine shaft nut, bears axially along the Z axis on the part 100 at the level of an overhang 15 of the part 100. The overhang 15 is located on the internal circumference of the lower end 101 of part 100 and comprises an upper surface 15b, in particular horizontal. Thus, more specifically, once the nut 12 has been screwed onto the body 11, the lower surface 12a of the nut 12 rests on the upper surface 15b of the overhang 15 of the part 100, so as to secure the part 100 with the connecting element 10, in particular axially.

The body 11 of the first connecting element 10 may also comprise splines arranged on the circumference of the body 11 at the level of the upper end of the body 11. The splines extend parallel to the Z axis.

At the level of the lower end 101 of part 100, the interior of part 100 may also include grooves. The splines of the part 100 are complementary to the splines of the body 11. Thus, when the body 11 is engaged in the lower end 101 of the part 100, the splines of the part 100 mate with the splines of the body 11. The part 100 and the first element 10 are thus secured in rotation around the Z axis by these grooves.

As shown in Figures 3, 4, 5, 6, the torque application system 2 5 comprises a spreader bar 20 extending along a first horizontal plane R. The spreader bar 20 notably comprises two lugs 19 (shown in FIG. 6) which are diametrically opposed and thus form a horizontal axis W. The spreader bar 20 also includes a vertical tail 25, which extends in particular along the Z axis in the direction of the beam(s) 32a, 32b. The lifter 20 is here connected to the upper end 102 of the part 100 via a device 6 for measuring the torque 5 and a second connecting element 22. The lifter 20 is in particular fixed with screws 22a on the measuring device 6, the latter being itself fixed with screws 6a on the second connecting element 22. The measuring device 6 is thus interposed between the spreader bar 20 and the second connecting element 22.

The second connecting element 22 comprises a tubular body 23 and extends along the axis Z. The tubular body 23 is in particular an adaptation part corresponding to a false fan disk. The upper end 102 of part 100 has a thread. The upper end 102 is engaged in the tubular body 23 and a nut 24 is screwed onto the part 100, in particular on the thread of the upper end 102 of the part 100 and resting axially on the body 23.

As shown in Figures 3 and 4, the nut 24 has an axial thread along Z and includes a lower surface 24a horizontal. The nut 24 bears axially along the Z axis on the second connecting element 22, in particular at the level of an overhang 28 of the body 23. The overhang 28 is located on the internal circumference of the tubular body 23 and comprises a horizontal surface upper 28b. Thus, more specifically, once the nut 24 has been screwed onto the upper end 102, the lower surface 24a of the nut 24 bears against the upper surface 28b of the overhang 28 of the body 23. The tubular body 23 is thus secured to the upper end 102 of the part 100 by the nut 24, in particular axially.

The upper end 102 of part 100 includes splines. These splines are distributed over the circumference of part 100 and extend parallel to the Z axis.

The tubular body 23 also includes grooves. The grooves of the tubular body 23 are complementary to the grooves of the upper end 102 of the part 100. When the part 100 is engaged in the tubular body 23, the grooves of the body 23 mate with the grooves of the upper end 102 of the part 100, thus making it possible to produce a coupling. The part 100 and the second connecting element 22 are thus secured in rotation around the Z axis by these grooves.

As shown in particular in Figures 5, 6, the torque application system 2 5 further comprises connecting cylinders 40a, 40b. The test bench 1 here comprises two cylinders 40a, 40b, called first 40a and second 40b cylinders. The connecting jacks 40a, 40b are located between the lifter 20 and the uprights 31a, 31b of the gantry 30. More specifically, the first jack 40a is located between the lifter 20 and the first upright 31a. The second jack 40b is located between the lifter 20 and the second upright 31b.

Each cylinder 40a, 40b has a first end 41a, 41b which is articulated on the lifter 20. More specifically, the cylinders 40a, 40b are articulated at first points 21a, 21b on the lifter 20, for example by means of a pivot connection along the Z axis. These first points 21a, 21b are located diametrically opposite on the crossbar 20 and extend in the first horizontal plane R. The first points 21a, 21b are located in particular on the lugs 19, in particular on the axis W. The cylinders 40a, 40b are in particular parallel and are located on the first plane R. Each cylinder 40a, 40b also comprises a second end 42a , 42b opposite which is articulated respectively on the uprights 31a, 31b. More precisely, the cylinders 40a, 40b are articulated at second points 43a, 43b, for example via a pivot connection along the Z axis. These second points 43a, 43b are located on the first horizontal plane R. They are thus positioned at the same height Ha, Hb on the uprights 31a, 31b.

The cylinders 40a, 40b form an angle α substantially equal to 90º with the uprights 31a, 31b on the first plane R. Also, the cylinders 40a, 40b form an angle γ substantially equal to 90º with the axis W formed by the first points 21a, 21b of the lifter on the first plane R. Thus, the forces in the cylinders 40a, 40b are minimized and the traction/compression effects of the uprights 31a, 31b are also minimized and correspond to an almost pure bending.

Thus, the jacks 40a, 40b, in particular identical, are positioned in the same way on the uprights 31a, 31b, which are themselves identical. They therefore make the uprights 31a, 31b work in the same way. The operation is then symmetrical, which results in an identical deformation of each upright 31a, 31b during the application of a torque 5 to the part 100 and which makes it possible to avoid the drawbacks of the asymmetrical systems of the prior art. In this way, it is not necessary to know the stiffness of the uprights 31a, 31b since they will deform in the same way.

It is in particular the measuring device 6 which makes it possible to control the forces of the cylinders 40a, 40b generating the torque 5.

Furthermore, the test bench 1 here comprises a single guide element 3 which is carried by the beam(s) 32a, 32b. The guide element 3 comprises a bearing 7 for guiding the vertical tail 25 of the lifter 20 allowing the lifter 20 to be guided in rotation.

The invention thus provides for considerably minimizing the number of parts necessary to carry out a test by using adaptation parts, such as the first and second connecting elements, equivalent to a false turbine shaft and a false fan disc, allowing thus to immobilize the fewest possible engine parts initially intended for the series and avoiding a complex assembly before carrying out the test. The use of adaptation parts also makes it possible to use parts much shorter than the real parts, allowing in particular to have a stiffer assembly and thus limit the angular deflection, which in particular makes it possible to limit the risk of generate cylinder strokes approaching their limit values. These optimizations thus make it possible to avoid having to design and manufacture a specific frame for the transport of parts that would have been assembled beforehand. The assembly is thus simplified and more compact, allowing it to be carried out on a test bench of standard dimensions. Notably for these reasons, logistics, cost and assembly times are then optimised.

As shown in Figures 7, 8, the uprights 31a, 31b and the beams 32a, 32b are stiffened by brackets 51, 52. The test bench 1 here comprises eight brackets 51, 52. The brackets 51, 52 allow make the assembly extremely rigid when the two cylinders stress the part in torsion along the Z axis. This rigidity of the assembly makes it possible to avoid parasitic movements of the elements of the test bench which come to pollute the test results.

The brackets 51, called plate brackets 51, here four in number, extend between the uprights 31a, 31b and the plate 34. The brackets 52, called beam brackets 52, here four in number, extend between the uprights 31a, 31b and the beam(s) 32a, 32b. The beam brackets 52 include in particular two first brackets 52a', 52b' and two second brackets 52a'', 52b''.

The first brackets 52a', 52b' are, for example, brackets connecting the first upright 31a to each of the beams 32a, 32b so that one of the first brackets 52a' connects the first upright 31a to the first beam 31a and the other first brackets 52b' bind the first upright 31a to the second beam 32b.

The first brackets 52a', 52b' each comprise first cylindrical holes 53 for passing fixing screws 55' configured to fix the first brackets 52a', 52b' to the first upright 31a. The cylindrical holes 53 are thus found on the same vertical plane and in particular on a side face of the first brackets 52a', 52b'. Each first bracket 52a', 52b' here comprises at least four cylindrical holes 53.

The first brackets 52a', 52b' also each include second holes 54c for passing fixing screws 55'' configured to fix the first brackets 52a', 52b' to the beams 32a, 32b. The second holes 54c have a cylindrical shape. The second holes 54c are thus found on the same horizontal plane, in particular on an upper face of the second brackets 52a', 52b'.

The second brackets 52a'', 52b'' (shown in detail in FIG. 9) are in particular brackets connecting the second upright 31b to each of the beams 32a, 32b so that one of the second brackets 52a'' binds the second upright 31b to the first beam 31a and the other of the second brackets 52b'' binds the second upright 31b to the second beam 32b. The positioning of the brackets 52a', 52b', 52a'', 52b'' could however be different from that described above without departing from the scope of the invention.

The second brackets 52a'', 52b'' each comprise first cylindrical holes 53 for passing fixing screws 55', 62a', configured to fix the second brackets 52a'', 52b'' to the second upright 31b. The cylindrical holes 53 are thus found on the same vertical plane and in particular on a side face of the second brackets 52a'', 52b''. Each second connecting bracket 52a'', 52b'' here comprises at least six cylindrical holes 53.

The second brackets 52a'', 52b'' also each include second holes 54a for passing fixing screws 55'', configured to fix the second brackets 52a'', 52b'' to the beams 32a, 32b respectively. The second holes 54a are thus found on the same horizontal plane, in particular on an upper face of the second brackets 52a'', 52b''.

The second brackets 52a'', 52b'' comprise, in particular here, each two second holes 54a of elongated shape, in particular called oblong holes. The second holes 54a have an elongated shape along an axis of elongation Y' of the beams 32a, 32b. The elongated shape of the second holes 54a makes it possible to leave a margin of adjustment on the position of the second brackets 52a'', 52b'' on the beams 32a, 32b and to ensure that the second holes 54a of elongated shape of the second brackets 52a' ', 52b'' can correspond with holes present on the beam 32a, 32b. Indeed, the beams 32a, 32b already have their own fixing holes distributed regularly over the entire length of the beam(s) 32a, 32b. The position adjustment margin provided by the elongated holes 54a makes it possible to prevent that, once the two uprights have been positioned for assembly purposes, the circular holes of certain beam brackets 52 do not fall opposite.

The second brackets 52a'', 52b'', having elongated holes 54a, they are less rigid than the first brackets 52a', 52b' having cylindrical holes 54c. Moreover, beyond a certain level of effort, in particular generated by the cylinders 40a, 40b, the beams 32a, 32b can slide on the brackets 52a'', 52b'' having second holes 54a of elongated shape or oblong. These parasitic movements on the assembly can pollute the test results. Also, these parasitic movements lead to a risk of premature failure of certain elements of test bench 1 in the case of fatigue tests.

To effectively lock the uprights 31a, 31b together and limit their sliding and movement as much as possible due to the forces of the cylinders 40a, 40b during the test, the test bench 1 further comprises at least one immobilization block 60. The test bench 1 comprises, in particular, two immobilization blocks 60a, 60b, called first 60a and second immobilization block 60b corresponding respectively to each of the second brackets 52a'', 52b'' used as reinforcement at the level of the first and second beams 32a, 32b respectively. The immobilization blocks 60a, 60b make it possible to reproduce the natural locking phenomenon observed on the brackets 52a', 52b' with cylindrical holes 54c. It therefore makes it possible to preserve the integrity of the elements of test bench 1 during fatigue tests. The immobilization blocks 60a, 60b are located on the side of the second brackets 52a'', 52b''. More specifically, they are opposite the second brackets 52a'', 52b'' with respect to the second upright 31b.

When carrying out tests, it is necessary to know precisely the position of an axis or of a direction of force on the assembly in order to be able to readjust its position vis-à-vis other elements, in particular on design computer-aided (CAD). The solution used in the prior art is Laser Tracking, which corresponds to a very precise positioning measurement using a laser. This solution is very expensive and generally requires the intervention of an external company. The test bench 1 of this present invention makes it possible, thanks to the presence of the immobilization blocks, to avoid the displacement of the uprights and therefore to avoid having to resort to expensive Laser Tracking.

The following description relating to Figures 10 and 11 focuses on the part of the assembly comprising one of the second brackets 52a'' connecting the first beam 32a with the second upright 31b and the first block 60a. The test bench 1 here comprises an identical assembly at the level of the second beam 32b. The description below can therefore be extrapolated to the assembly located at the level of the second beam 32b.

The first immobilization block 60a is fixed to the first beam 32a by first screws 61a', 61a'' parallel to the second upright 31b. The first immobilization block 60a notably comprises here two first screws 61a', 61a'' which make it possible to fix the first immobilization block 60a on the first beam 32a. In addition, the first immobilization block 60a is fixed to the second upright 31b by second screws 62a' parallel to the first beam 32a. The test bench includes in particular two second screws 62a' per second bracket 52a'', 52b'' even if only one is represented here. These second screws 62a', notably having threaded rods, will thus pass through the upper cylindrical holes 53 of the second bracket 52a''. Other fixing screws 55' pass through the lower cylindrical holes 53 of the second bracket 52a'' to fix it to the second upright 31b.

Each second screw 62a' rests on the second bracket 52a'' via a nut 66a' and on the second upright 31b via a nut 64a'. The second screw 62a' is fixed to the first block 60a by a nut 65a'.

Thus, when the jacks 40a, 40b generate a torque 5 on the part 100, a force F is created on the second upright 31b in an axis parallel to the axis Y' in the direction of the part 100.

The force F will then be taken up on a zone 64ar' corresponding to the surface of the nut 64a' which rests on the second upright 31b. The force F will also be taken up on a zone 65ar' corresponding to the surface of the nut 65a' which rests on the first immobilization block 60a. The force F will also be taken up on a zone 61ar' and a zone 61ar'' which correspond respectively to the contact surface between the first screws 61a', 61a'' and the first beam 32a. In other words, the barrel of the screw 61a', 61a'' bears against the first beam 32a. The movement of the second upright 31b when the force F is generated by the cylinders 40a, 40b is thus blocked despite the presence of elongated holes 54a on the second bracket 52a''.

The gantry 30 is thus extremely stiffened by the brackets 51, 52 and the immobilization blocks 60 thus avoiding parasitic movements which come to pollute the test results and also avoiding the risks of premature rupture of elements of the test bench 1 in the case of fatigue testing. The use of a few brackets with elongated holes 52a'', 52b'' with an immobilization block 60 makes it possible to leave a margin of adjustment on the position of the reinforcing beams 32 while ensuring that the elements of the bench 1 do not move. during a test. In other words, the invention makes it possible to stiffen the test bench by limiting parasitic movements while retaining a margin of adjustment in position of the bench elements.

The invention can also be used for other types of mounting and other types of parts.

The invention also relates to a method of implementing a torsional force of the part 100, such as an aircraft turbomachine shaft, by means of the test bench 1 as described above.

Claims (12)

Test bench (1) for stressing in torsion a part (100) of an aircraft turbomachine, comprising:
- a part (100) to be tested of generally elongated shape and having a vertical axis of elongation (Z),
- a system (2) for applying a rotation torque (5) to the part (100) around said axis (Z),
- at least one guide element (3) in rotation of the part (100) around said axis (Z), and
- a recovery system (4) of the torque applied to the part (100) around said axis (Z),
characterized in that said torque take-up system (4) comprises:
- a first element (10) connecting a lower end (101) of the part (100) to a horizontal plate (34), said connecting element (10) being fixed in rotation to the part (100) and being rigidly attached to the plate (34),
and in that said torque application system (2) comprises:
- a lifter (20) connected to an upper end (102) of the part (100),
- a gantry (30) comprising two vertical uprights (31a, 31b) and at least one horizontal beam (32a, 32b), the uprights (31a, 31b) extending between the plate (34) and the beam (32a, 32b ) and being arranged on each side of the part (100), and
- connecting cylinders (40a, 40b) of the lifter (20) to the uprights (31a, 31b) of the gantry (30), each cylinder (40a, 40b) comprising a first end (41a, 41b) articulated on the lifter (20 ) and a second opposite end (42a, 42b) articulated on one of the uprights (31a, 31b), the cylinders (40a, 40b) being articulated at first points (21a, 21b) diametrically opposed on the lifter (20), and extending in a first horizontal plane (R) passing through said lifter (20). Test bench (1) according to claim 1, in which the part (100) is a shaft of an aircraft turbine engine. Test bench (1) according to Claim 1 or 2, in which the part (100) is tubular and the said first connecting element (10) comprises:
- a cylindrical body (11) engaged in the lower end (101) of the part (100) and secured thereto by a nut (12) screwed onto the body (11) and bearing axially on the part (100 ), And
- a base (13) for fixing to the plate (34). Test bench (1) according to one of the preceding claims, in which the spreader bar (20) is connected to the upper end (102) of the part (100) via a second connecting element ( 22) which comprises a tubular body (23) in which the upper end (102) of the part (100) is engaged and which is secured thereto by a nut (24) screwed onto the part (100) and taking bearing axially on the body (23). Test bench (1) according to one of the preceding claims, in which it further comprises a device (6) for measuring a torque (5) applied to the part (100) around the said axis (Z). Test bench (1) according to one of the preceding claims, in which the said at least one guide element (3) is carried by the said beam (32a, 32b). Test bench (1) according to the preceding claim, in which said at least one guide element (3) comprises a guide bearing (7) for a vertical tail (25) of the spreader bar (20). Test bench (1) according to one of the preceding claims, in which the uprights (31a, 31b) are walls which are arranged opposite one another. Test bench (1) according to one of the preceding claims, in which the uprights (31a, 31b) and the beams (32a, 32b) are stiffened by brackets (51, 52) extending between the uprights (31a , 31b) and the plate (34), and/or between the uprights (31a, 31b) and the beam (32a, 32b). Test bench (1) according to the preceding claim, in which the brackets (52) connecting the uprights to the beam (32a, 32b) each comprise first cylindrical holes (53) for passing fixing screws (55') of the bracket (52) to one of the uprights (31a, 31b), and second holes (54a, 54c) for passing fixing screws (55'') from the bracket (52) to the beam ( 32a, 32b), these second holes (54a, 54c) having a cylindrical (54c) or elongated (54a) shape along an axis (Y') of elongation of the beam (32a, 32b). Test bench (1) according to the preceding claim, in which a first of the brackets (52a', 52b') connecting an upright (31a) to the beam comprises second cylindrical holes (54c), and a second of the brackets (52a'', 52b'') connecting the other upright (31b) to the beam (32a, 32b) comprises second holes of elongated (54a) or oblong shape, the test bench (1) comprising in addition at least one immobilization block (60a, 60b) located on the side of this second bracket (52a'', 52b''), which is fixed to the beam (32a, 32b) by first screws (61a', 61a'') parallel to the upright (31a, 31b) and which is fixed to the upright (31b) by second screws (62a') parallel to the beam (32a, 32b) and which rest respectively on the second bracket (52a' ', 52b'') and on the upright (31b). Method for applying a torsional force to an aircraft turbomachine part (100), such as an aircraft turbomachine shaft, by means of a test bench (1) according to the any of the preceding claims.